A turbine engine has a combustor in a core air flow path that generates combustion gases and a fuel and steam system fluidly coupled to the combustor. The fuel and steam system has a steam system to provide a steam flow to the combustor and a fuel system to provide a primary fuel flow and a secondary fuel flow to the combustor. The fuel system has a first state in which there is a first flow rate of the secondary fuel flow to the combustor and a second state in which there is a second flow rate of the secondary fuel flow to the combustor. The first flow rate and the second flow rate are different. The first state and the second state are based on a condition of the steam system.
A method of forming a composite airfoil assembly. The method includes forming an inner support structure with at least a first core and a second core each having a core material with at least one of fibers, yarns, braids, or tows. The method includes applying a laminate overlay to surround at least a portion of the inner support structure.
A system for in-situ monitoring an additive manufacturing build includes a recoater and an eddy current array probe (ECAP) coupled to the recoater. The ECAP includes three rows of sensor elements, and a drive line arranged in a semi-circular wave pattern extending through each of the three rows of sensor elements. The semi-circular wave pattern is defined by a wavelength, and the semi-circular wave pattern of the drive line extending through a particular row of sensor elements is offset by a fraction of the wavelength relative to the semi-circular wave pattern of the drive line extending through an adjacent row of sensor elements.
G01N 27/904 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents with two or more sensors
B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
G01N 27/90 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.
A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:
A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:
0.1
(
r
′
)
-
1
<
Δ
r
r
<
K
(
r
′
)
-
4
/
3
,
A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:
0.1
(
r
′
)
-
1
<
Δ
r
r
<
K
(
r
′
)
-
4
/
3
,
wherein the normalized radius (r′) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K is equal to 65%.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
F23R 3/06 - Arrangement of apertures along the flame tube
F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
A test system to conduct a sequence of electrical tests of an electrical cable is disclosed. The system includes a testing unit, a set of sensors, and two circuits. The two circuits are switchably coupled to a common voltage source and selectively electrically coupleable to the electric cable to enable the testing unit to conduct a respective test of the electrical cable.
A turbine engine includes a cooling air duct for cooling air positioned radially between a core air flow path for core air and a bypass airflow passage for bypass air. A heat exchanger is positioned in the cooling air duct to transfer heat from a heat source from within the turbine engine. The heat exchanger may be a condenser. The turbine engine may further include a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flow path, the steam system including the condenser to transfer heat from the combustion gases to the cooling air and to condense the water from the combustion gases. The turbine engine may further include a booster fan to increase the pressure of the cooling air and the core air.
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.
A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
A backing film removal system comprises a separating mechanism configured to separate a first portion of a first backing film on a first side of a material segment and a second portion of a second backing film on a second side of the material segment from a material layer of the material segment, wherein the second side is opposite the first side. The backing film removal system also includes a clamping mechanism that is actuatable to apply a clamping force to secure the material layer and the second portion together. A separator assembly includes a gripping mechanism configured to grip the first portion. At least one of the gripping mechanism or the clamping mechanism is movable to draw the first portion gripped by the gripping mechanism away from the material layer to remove a remaining portion of the first backing film from the material layer.
A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct, a primary fan driven by the turbomachine, a secondary fan located downstream of the primary fan within the inlet duct, and a booster located downstream of the secondary fan and comprising a booster rotor blade, an inlet guide vane, and booster cowl, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet, the inlet guide vane located forward of the booster rotor blade.
F02K 3/065 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front and aft fans
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B29C 70/84 - Moulding material on preformed parts to be joined
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23C 7/00 - Combustion apparatus characterised by arrangements for air supply
F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
15.
GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined by
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined by
V
G
V
G
B
.
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined by
V
G
V
G
B
.
VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly, a fan, a combustor that generates combustion gases, a turbine, a nacelle that surrounds the fan, and a steam system. The combustor and the turbine define a core air flowpath. Core air flows through the core air flowpath. The steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the core air. A bypass ratio of the gas turbine engine is in a range of 18:1 to 100:1.
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by
V
G
V
GB
.
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by
V
G
V
GB
.
VG is a gutter volume of the gutter and VGB is a gearbox volume of the gearbox. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a tank that stores a lubricant therein, one or more lubricant pumps for generating a flow of lubricant from the tank to the gearbox assembly, and a flow rate control valve. The flow rate control valve has a flow inlet and a flow outlet and defines a variable throughput from the flow inlet to the flow outlet for controlling a flowrate of the lubricant to the gearbox assembly.
A water-based binder solution comprises a thermoplastic binder, greater than or equal to 4 wt % to less than or equal to 20 wt % of a non-aqueous solvent having a boiling point greater than or equal to 100° C. and less than or equal to 175° C., and water. The thermoplastic binder comprises a first polymer strand having a weight average molecular weight (Mw) of from 5,000 g/mol to 15,000 g/mol; and at least one of a second polymer strand having a weight average molecular weight (Mw) of from 10,000 g/mol to 50,000 g/mol and a third polymer strand having a weight average molecular weight (Mw) of from 1,000 g/mol to 5,000 g/mol. A method of monitoring a print head of an additive manufacture process comprises depositing a water-based binder solution on the thermal paper.
C09D 139/06 - Homopolymers or copolymers of N-vinyl-pyrrolidones
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
A method of forming a build platform for a powder bed fusion additive manufacturing process. The method incudes directing a high-energy beam at a first energy level to irradiate a bed of fusible powder and to form a first layer of the build platform. The method also includes forming subsequent initial layers of the build platform, each subsequent layer being formed by directing the high-energy beam to irradiate a distributed layer of the fusible powder to form one of the subsequent initial layers of the build platform. The energy level of the high-energy beam is increased from the first energy level for successive layers of the subsequent initial layers. The build platform may be a sintered build platform where the degree of sintering increases from the bottom layer toward the top layer.
B22F 10/366 - Scanning parameters, e.g. hatch distance or scanning strategy
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 12/00 - Apparatus or devices specially adapted for additive manufacturingAuxiliary means for additive manufacturingCombinations of additive manufacturing apparatus or devices with other processing apparatus or devices
A closed-loop thermal management system includes a thermal transport bus configured to circulate a thermal working fluid therethrough, a thermal transport bus including a plurality of fluid conduits configured to circulate a thermal working fluid therethrough; an accumulator including a shell defining a multiphase fluid volume therein configured to contain a multiphase fluid. The shell defines an opening. The accumulator is fluidly coupled to the thermal transport bus in a closed-loop fluid circuit. A temperature regulator is configured to control a temperature of the multiphase fluid inside the multiphase fluid volume.
An automated fiber placement assembly forms a component by the placement of separate or multiple layers of fiber tows. The automated fiber placement assembly comprises a cutter assembly defining a cut shape. A backplate is spaced from the first cutter assembly against which cutter assembly can cut the fiber tows. The fiber tows define a longitudinal axis and are fed between the first cutter assembly and the backplate in a feed direction. The cutter head assembly is rotatable and movable to vary the orientation of the cutter assembly in order to define different cut shapes non-orthogonal to the longitudinal axis.
A method and aircraft power distribution system includes a power distribution bus supplying power along an electrical line, a primary communication module including a primary transceiver and a primary controller, and a plurality of secondary communication modules including a secondary transceiver communicatively coupled to the primary transceiver and a secondary controller communicatively coupled to the secondary transceiver.
H02J 3/38 - Arrangements for parallelly feeding a single network by two or more generators, converters or transformers
H02J 3/14 - Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
22.
AIR FLOW EJECTOR NOZZLE WITH A CONSTANT OUTLET CROSS-SECTION AND TURBINE ENGINE PROVIDED WITH SUCH A NOZZLE
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section (20) and an outlet cross-section (21) along the longitudinal axis (X), the ejector nozzle being delimited at least in part by a radially outer shroud (24) and a radially inner shroud (25) at least partially forming a flow path (18, 15). According to the invention, a plurality of struts (45) extend radially between the radially outer shroud (24) and the radially inner shroud (25), and the struts (45) are arranged regularly around the longitudinal axis (X) and have a predetermined height (H1) configured such that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
23.
AIRFLOW EJECTION NOZZLE WITH CONSTANT OUTLET SECTION AND TURBINE ENGINE EQUIPPED WITH SUCH A NOZZLE
The invention relates to a turbine engine airflow ejection nozzle, in particular for an aircraft, the ejection nozzle extending about a longitudinal axis (X) and between an inlet section (20) and an outlet section (21) along the longitudinal axis (X), the ejection nozzle being at least partially delimited by a radially outer shroud (24) and a radially inner shroud (25) at least partially forming a flow path (18, 15). According to the invention, a plurality of struts (45) extend radially between the radially outer shroud (24) and the radially inner shroud (25), and the struts (45) are arranged evenly about the longitudinal axis (X) and have a predetermined height (H1) configured so that a radial height (H2) of the outlet section (21), during operation, is fixed and constant.
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
24.
AUTOMATED STRATEGY PLANNING FOR SEVERE WEATHER-DRIVEN PROACTIVE OUTAGE AND RESTORATION EVENTS IN A POWER GRID
Provided is a system and method that can determine the timing and sequence of transmission assets on a power grid to be outaged and/or restored based on severe weather. In one example, the method may include selecting a group of transmission assets of a power grid for outage, receiving forecasted weather conditions for a geospatial area that includes the group of transmission assets, determining an outage time and priority among the group of transmission assets based on geospatial locations of the forecasted weather conditions and geospatial locations of the group of transmission assets, and generating a sequence of instructions for powering down the group of transmission assets based on the determined outage time and priority among the group of transmission assets and storing the sequence of instructions in memory.
General Electric Company Polska Sp. z o.o. (Poland)
Inventor
Sibbach, Arthur William
Pazinski, Adam Tomasz
Abstract
An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
General Electric Company Polska Sp. z o.o. (Poland)
Inventor
Sibbach, Arthur William
Pazinski, Adam Tomasz
Abstract
An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
27.
REVERSE FLOW GAS TURBINE ENGINE HAVING ELECTRIC MACHINE
General Electric Company Polska Sp. z o.o. (Poland)
Inventor
Sibbach, Arthur William
Pazinski, Adam Tomasz
Abstract
An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: VG/VGB. VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by
V
G
V
G
B
.
A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by
V
G
V
G
B
.
VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.
A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10. The thrust to power airflow ratio is a ratio of airflow through a bypass passage over the turbomachine plus airflow through the fan duct to airflow through the core duct. The core bypass ratio is a ratio of airflow through the fan duct to airflow through the core duct. The fan duct includes an exhaust nozzle having a plurality of chevrons disposed at its aft end to define an exhaust outlet.
F02K 3/065 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front and aft fans
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
A heat exchanger is provided that can include furcating unit cells coupled with each other. Each of the unit cells can be elongated along an axis and include a sidewall that defines annular ring openings on opposite ends of the unit cell along the axis. The sidewall also can define undulating annular rings between the annular ring openings and axially separated from each other along the axis. The sidewall can further define angled openings into the unit cell both above and below each of the undulating annular rings. At least a first opening of the annular ring openings and the angled openings can be configured to be an inlet to receive a first fluid into the unit cell and at least a second opening of the annular ring openings and the angled openings configured to be an outlet through which the first fluid exits the unit cell.
F28D 7/16 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
F28F 1/02 - Tubular elements of cross-section which is non-circular
32.
BEARING LUBRICATION SYSTEMS AND METHODS FOR OPERATING THE SAME
Example bearing lubrication system and methods of operating the same are disclosed herein. An example closed loop system to provide a lubricant to a fluid pump includes a lubrication flow network disposed within the fluid pump; a sensor fluidly coupled to the fluid pump to measure a condition of a fluid that is to enter the lubrication flow network; a first transport bus fluidly coupled to the lubrication flow network, the first transport bus to transport an inert gas; a controller to actuate a valve fluidly coupled to the first transport bus, the controller to transmit signals to the valve based on the condition of the fluid to cause the valve to open or close; and a separator fluidly coupled between an outlet of the fluid pump and the first transport bus, the separator to separate the fluid and the inert gas.
F16N 7/40 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pumpCentral lubrication systems in a closed circulation system
F16N 29/00 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditionsUse of devices responsive to conditions in lubricating arrangements or systems
F16N 39/02 - Arrangements for conditioning of lubricants in the lubricating system by cooling
A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct. The primary fan is driven by the turbomachine, and a secondary fan is located downstream of the primary fan within the inlet duct. One or more actuation devices operably associated with the fan duct, the one or more actuation devices actuable to increase or decrease an exit area of the fan duct.
F02K 3/065 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front and aft fans
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
Seals for a gas turbine engine are disclosed herein. An example sealing apparatus for a gas turbine engine includes a first end having a first contact surface to contact a first component of a rotating machine, a second end having a second contact surface to contact a second component of the rotating machine, the second component positioned in proximity to the first component such that a cavity is formed therebetween, the apparatus dividing the cavity into a first cavity portion and a second cavity portion, and a central portion extending the first end from the second end, the central portion defining a first chamber and a second chamber, the first chamber in fluid communication with the first cavity portion, the second chamber in fluid communication with the second cavity portion, the first chamber is fluidly isolated from the second chamber.
A method for removing ultrafine particles from an atomized powder includes contacting the atomized powder with a removal liquid to form a mixture of the atomized powder and the removal liquid, the atomized powder comprising fine particles and ultrafine particles, adding energy to the mixture of the atomized powder and the removal liquid with a liquid classifier system to detach the ultrafine particles from the fine particles, and separating, with the liquid classifier system, the removal liquid and the detached ultrafine particles from the fine particles.
B03B 5/32 - Washing granular, powdered or lumpy materialsWet separating by sink-float separation using heavy liquids or suspensions using centrifugal force
B03B 5/48 - Washing granular, powdered or lumpy materialsWet separating by mechanical classifiers
36.
Fuel Nozzle/Swirler Assembly for a Gas Turbine Engine
A fuel nozzle/swirler assembly includes a venturi including a heat shield retaining wall. A backplate is connected to the venturi and includes a plurality of purge orifices extending through the backplate. A ceramic matrix composite (CMC) heat shield includes a heat shield attachment wall engaged between the heat shield retaining wall of the venturi and the backplate, and a seal member is arranged between the backplate and the CMC heat shield. The plurality of purge orifices are arranged between the seal member and the venturi and provide a flow of purge air therethrough to flow through a radial gap. The seal member provides a force against the CMC heat shield to axially engage the heat shield attachment wall of the CMC heat shield against the heat shield retaining wall of the venturi.
A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.
A method of forming a composite component includes laying up a plurality of composite plies around a mandrel assembly to form a composite ply core. The mandrel assembly includes a mandrel having an inner structural body and an outer release layer. The mandrel is configured to form a cavity in the composite ply core. The method also includes processing the composite ply core containing the mandrel assembly to compact the plurality of composite plies together. Further, the method includes removing the mandrel assembly from the composite ply core to form the cavity. Further, removing the mandrel assembly from the composite ply core includes melting out the inner structural body and removing the outer release layer after melting out the inner structural body.
Combustor systems are provided that include rotating detonation combustors (RDCs) arranged in series. In some embodiments, a combustor system includes a volume that receives a core oxidizer-fuel mixture. The combustor system includes a first RDC having a first detonation chamber. The first detonation chamber receives a first pilot oxidizer-fuel mixture and is bounded by a first channel formed in a peripheral wall. The combustor system further includes at least one additional RDC having a second detonation chamber. The second detonation chamber receives a second pilot oxidizer-fuel mixture and is bounded by a second channel formed in the peripheral wall. The first pilot oxidizer-fuel mixture reacts in the first detonation chamber and the second pilot oxidizer-fuel mixture reacts in the second detonation chamber to generate rotating detonation combustion waves that are guided by the first channel and the second channel to support a reaction that consumes the core oxidizer-fuel mixture.
05 - Pharmaceutical, veterinary and sanitary products
09 - Scientific and electric apparatus and instruments
10 - Medical apparatus and instruments
36 - Financial, insurance and real estate services
37 - Construction and mining; installation and repair services
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
44 - Medical, veterinary, hygienic and cosmetic services; agriculture, horticulture and forestry services
Goods & Services
Business management services to manage healthcare clinical and non-clinical assets and operations of healthcare facilities; Asset management services, namely, reporting on service histories, utilization of the medical assets, end of product life information and replacement costs, all related to medical diagnostic and clinical equipment; Business consulting services in the field of improving clinical and hospital dataflow, workflow and business practices Diagnostic substances for medical purposes; Contrast media for use with imaging medical equipment; Contrast media for in-vivo imaging; Diagnostic imaging agents for magnetic resonance imaging; Diagnostic radiopharmaceutical preparations Downloadable computer software for collecting and analyzing data in the field of healthcare; Computer hardware, downloadable computer software and downloadable computer firmware for automating control of medical equipment; Downloadable computer software for information management, data collection and data analysis in the fields of asset optimization, machine diagnostics, and optimization of healthcare and hospital processes; Computer hardware and downloadable computer software for medical imaging and for analysis of data gathered from a medical diagnostic apparatus to enhance clinical decision making; Computer hardware and downloadable computer software for use with medical patient monitoring equipment, for receiving, processing, transmitting and displaying data; Downloadable computer software for analyzing medical diagnostic information; Downloadable computer software for controlling and managing patient medical information; Downloadable computer software for automating and analyzing the administrative, financial, billing, and clinical records of healthcare organizations, for capturing, distributing, managing and viewing electronic documents, for electronic data interchange (EDI) of healthcare transaction information, and for managing workflow in the delivery of healthcare; Downloadable computer software used to capture, store, track, report and monitor radiation levels delivered by medical devices and instruments Medical imaging apparatus for screening and diagnostic use and for use in planning intervention and surgery; Medical devices, namely, bone mineral densitometer machines; Patient monitoring systems, namely, gas monitors, pulse oximeters, multi-parameter monitors, ECG monitors, invasive and non-invasive blood pressure monitors, neuromuscular transmission monitors, metabolic monitors, and spirometers for anesthesia, intensive care, and diagnostic applications; Medical apparatus, namely, fetal and maternal vital sign and physical distress monitors; Wearable monitors used to measure biometric data for medical use; Medical ventilators; Anesthesia machines for use in patient care; Phototherapeutic apparatus for medical purposes for infant care; Replacement parts for medical diagnostic and medical imaging equipment; incubators and baby warmers Financing loans for medical equipment Refurbishing of pre-owned medical equipment; Maintenance and repair of medical equipment Providing training services in the field of medical data analysis and software development; Educational services, namely, conducting training courses and workshops in the field of healthcare Software as a service (SAAS) services featuring software for data collection and data analytics, for use in the field of healthcare; Software as a service (SAAS) services featuring software for use in asset optimization, machine diagnostics, and optimization of healthcare processes; Technical support services, namely, troubleshooting of computer software problems; Remote diagnosis of medical and clinical equipment for determining the need for repair; Providing real time monitoring of networked medical and internet of things (IoT) devices installed in a hospital or other healthcare facilities for detecting unauthorized access or data breach Leasing of medical equipment
A gas turbine engine oil flow control system can include a variable flow oil pump useful to provide oil at varying rates to a variety of oil consumers, such as, power gearboxes, engine shaft bearings, electrical generators, etc. Oil flow control valves that have an ability to provide a variable flow of oil can be used in conjunction with the variable flow oil pump. Flow sensors can be used along with an oil flow controller to measure a flow of oil at various points in the gas turbine engine oil flow control system. The oil flow controller can use information from the flow sensors along with a variable consumption demand association with one or more of the oil consumers (either provided to the oil controller or calculated based upon an operational need of the oil consumer) to change operation of the variable flow oil pump and/or oil flow control valve.
F16N 29/00 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditionsUse of devices responsive to conditions in lubricating arrangements or systems
A thermal management system includes a thermal circuit having a thermal transport bus with a thermal fluid flowing therethrough. The thermal transport bus includes first and second bus segments. First and second thermal loads are on the first and second bus segments, respectively, and have different first and second inlet temperature requirements. The thermal management system includes a plurality of heat exchangers in thermal communication with the first and second thermal loads. The heat exchangers include a first heat exchanger and one or more second heat exchangers. The first heat exchanger is on one of the first or second bus segments for rejecting heat to engine fuel. The thermal fluid is split between each of the first and second bus segments such that only a portion of the thermal fluid flows through the first heat exchanger to accommodate the different first and second inlet temperature requirements.
A gas turbine engine including a catalytic reactor and a combustor. The catalytic reactor is configured (i) to receive hydrogen fuel, (ii) to receive air containing oxygen, (iii) to catalytically react at least a portion of the oxygen in the air with at least a portion of the hydrogen in the hydrogen fuel to produce water, and (iv) to output diluent comprising the catalytically produced water. The combustor includes (a) a combustion chamber and (b) at least one nozzle that is fluidly coupled to the catalytic reactor to receive the diluent output by the catalytic reactor and configured to inject the diluent into the combustion chamber.
F23R 3/40 - Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/232 - Fuel valvesDraining valves or systems
45.
COMBUSTION SECTION WITH A PRIMARY COMBUSTOR AND A SET OF SECONDARY COMBUSTORS
A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section includes a primary combustor liner including an inner liner and an outer liner. A dome wall and a primary dome inlet are located in the dome wall. The outer liner defines at least one opening downstream from the primary dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.
A gas turbine engine includes a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, and defining an engine centerline extending between a forward direction and an aft direction. A disk includes a slot for mounting a composite airfoil to the disk. An axial retainer couples to the disk and secures the composite airfoil to the disk. A compliant portion positioned at the composite airfoil abuts the composite airfoil during operation of the gas turbine engine to secure the composite airfoil to the disk.
An airfoil assembly and engine component for a turbine engine having an engine core extending along an engine centerline, the airfoil assembly having an airfoil extending between a root and a tip in a radial direction, away from the engine centerline, to define a span length. The airfoil comprising a composite core and a set of skins defining at least a portion of an exterior surface of the airfoil. A shank extending in the radial direction from the root toward the engine centerline and having a flared cross-section.
An engine includes a gearbox coupled to a first element and a second element. The engine may include a first speed sensor positioned on an input side of the gearbox, the first speed sensor operable to detect a first speed of the first element. The engine may further include a second speed sensor positioned on an output side of the gearbox, the second speed sensor operable to detect a second speed of the second element. The engine includes a controller comprising a processor and a memory coupled to the processor. The processor may be configured to receive data from the first speed sensor and the second speed sensor. The processor is also configured to detect a trigger event based on the data from the first speed sensor and the data from the second speed sensor. Upon detecting the trigger event, the processor communicates a command to an engine operational system.
Method of repairing a Ni-based alloy component are provided, along with the resulting repaired coated component. The method may include: spraying a plurality of particles onto a surface of the Ni-based alloy component to form a coating thereon. The plurality of particles comprises a mixture of Ni-based superalloy particles and Co-based superalloy particles. The particles are sprayed at a spray temperature that is less than a melting point of both the Ni-based superalloy particles and the Co-based superalloy particles. A repaired coated component may include: a Ni-based alloy component having a surface and a coating on the surface of the Ni-based alloy component. The coating comprises a plurality of deformed particles therein, with the plurality of deformed particles comprises 5% by weight to 80% by weight of a Ni-based superalloy and 20% by weight to 95% by weight of a Co-based superalloy.
C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
C23C 24/10 - Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
An aircraft monitoring system includes an avionics communication bus structure, at least one network member user device that transmits a broadcast message onto the avionics communication bus structure, and at least one non-member user device that receives the broadcast message transmitted onto the avionics communication bus, processes the received broadcast message, and transmits output data to a monitoring device. The at least one non-member user device includes a bus interface, and a field programmable gate array (FPGA) that communicates with the bus interface. The FPGA is programmed to function as a main finite state machine that processes the broadcast message from the bus interface, and a transfer finite state machine that generates output data and transfers the generated output data to an output processor that communicates with the monitoring device. The monitoring device outputs a monitored data report.
A light-off detector (LOD) instrumentation translator for use with an LOD used to detect an afterburning condition of a gas turbine engine having an afterburner. The LOD translator is configured to receive an excitation signal useful to provide power for capturing light-off data detected from an LOD. The excitation signal can originate from an engine controller. The LOD instrumentation translator includes the ability to transduce light-off data generated from the LOD to afterburner condition data used by the engine controller. The LOD can be reconfigurable such that a variety of LODs can be coupled with the LOD instrumentation translator to transduce light-off data from a plurality of types of LODs to afterburner condition data for use in the engine controller.
A cleaning solution for a turbine engine includes water; a first organic acidic component that comprises citric acid; a second organic acidic component that comprises glycolic acid; isopropylamine sulphonate; alcohol ethoxylate; triethanol amine; and sodium lauriminodipropionate. The cleaning solution has a pH value between about 2.5 and about 7.0.
A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.
A fault detection system for detecting an electrical fault in a component includes an optical conductor with a first end and a second end, and configured to optically face the component. A first sensor and a second sensor can be operably coupled to the first end and the second end, respectively. The first sensor and the second sensor are each configured to detect electromagnetic radiation propagating through the optical conductor.
G01R 31/08 - Locating faults in cables, transmission lines, or networks
G01R 31/58 - Testing of lines, cables or conductors
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
Methods of protecting a surface of a Ni-based alloy component are provided, along with the wear strip utilized and the repaired Ni-based alloy component. The method may include: spraying a plurality of particles to form a wear strip. The plurality of particles includes a mixture of Ni-based superalloy particles and Co-based superalloy particles. The plurality of particles is sprayed at a spray temperature that is less than a melting point of the Ni-based superalloy particles and less than a melting point of the Co-based superalloy particles. The wear strip may be attached onto a surface of the Ni-based alloy component, either during the spraying of the particles (when wear strip formed on the surface of the Ni-based alloy component) or after a standalone wear strip is formed.
C23C 24/04 - Impact or kinetic deposition of particles
B22F 10/25 - Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
B22F 10/50 - Treatment of workpieces or articles during build-up, e.g. treatments applied to fused layers during build-up
B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
C22C 19/03 - Alloys based on nickel or cobalt based on nickel
C22C 19/07 - Alloys based on nickel or cobalt based on cobalt
C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
C22C 1/04 - Making non-ferrous alloys by powder metallurgy
A thrust link for an aircraft engine includes a forward end coupled to the aircraft engine, the forward end having a first diameter, and an aft end coupled to the aircraft engine or a pylon, the aft end having the first diameter, wherein the thrust link defines a thrust link span that extends from the forward end to the aft end, wherein a second diameter greater than the first diameter is defined between the forward end and the aft end, wherein the second diameter spans a center diameter span that is equivalent to or between 60% and 90% of the thrust link span.
Viscous damper apparatus and associated methods to control a response to a resonant vibration frequency are disclosed. An apparatus to support an aircraft engine includes a thrust link including a forward end and an aft end, the forward end of the thrust link coupled to the aircraft engine, and a damper including a piston rod coupled to the aft end of the thrust link, the piston rod including a piston, and a chamber including a fluid, the piston to move within the chamber.
A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:
A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:
V
G
V
G
B
·
V
G
A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:
V
G
V
G
B
·
V
G
is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.
F16H 57/04 - Features relating to lubrication or cooling
F16N 7/38 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pumpCentral lubrication systems
59.
GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO
A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:
A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:
V
G
V
G
B
·
V
G
A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:
V
G
V
G
B
·
V
G
is a gutter volume of the gutter and VGB is a gearbox volume.
A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:
A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:
(
T
OUT
A
DTExit
)
2
*
EGT
A
HPCExit
*
1
0
-
1
1
;
A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:
(
T
OUT
A
DTExit
)
2
*
EGT
A
HPCExit
*
1
0
-
1
1
;
wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
F02C 6/06 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Systems and methods for operating systems are provided. For example, a system comprises a heat source for providing a flow of a hot fluid and a fuel flowpath for a flow of a fuel. The fuel flowpath includes a fuel accumulator and a heat exchanger for heat transfer between the hot fluid and fuel. The heat exchanger includes a hot fluid inlet for receipt of the hot fluid at an inlet temperature and a fuel inlet for receipt of the fuel at an inlet temperature. The hot fluid inlet temperature is greater than the fuel inlet temperature such that the fuel is heated through heat transfer with the hot fluid in the heat exchanger. The fuel accumulator accumulates at least a portion of the heated fuel. An exemplary system is selectively operated to heat and circulate the fuel through the fuel flowpath for consumption and/or accumulation in the fuel accumulator.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F02C 7/232 - Fuel valvesDraining valves or systems
Systems, apparatus, articles of manufacture, and methods for leak detection and mitigation for hydrogen fueled aircraft are disclosed. An example apparatus disclosed herein includes machine readable instructions, and programmable circuitry to at least one of instantiate or execute the machine readable instructions to determine a hydrogen concentration threshold for a location within an undercowl of an engine of an aircraft, based on an engine condition of the aircraft, determine, based on an output of a hydrogen concentration sensor within the undercowl, a hydrogen concentration at the location, compare the hydrogen concentration to the hydrogen concentration threshold, and conduct a mitigation action in the hydrogen fuel distribution system based on the comparison of the hydrogen concentration and the hydrogen concentration threshold.
G01M 3/16 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using electric detection means
63.
SYSTEM AND METHOD FOR GENERATING A TIME-SENSITIVE NETWORK SCHEDULE
Systems, methods, and other embodiments described herein relate to generating a time-sensitive network schedule for a time-sensitive network (TSN). In one embodiment, a method includes receiving a measured value of at least one environmental condition from at least one sensor. The method includes determining an impact of the measured value of the at least one environmental condition on at least one component of the TSN. The method includes programming a switching node based on at least the determined impact. The TSN includes a first end node, a second end node, and the switching node. The switching node is communicatively linked between the first end node and the second end node.
A vehicle having a body extending between a nose section and a tail section. The nose section terminating at a tip. The body having a centerline axis extending from the tip. The nose section having an outer wall terminating at the tip. The outer wall including an outer wall centerline axis, an inner surface and an outer surface.
Method of repairing a Ni-based alloy component are provided, along with the resulting repaired coated component. The method may include: spraying a plurality of particles onto a surface of the Ni-based alloy component to form a coating thereon. The plurality of particles comprises a mixture of Ni-based superalloy particles and Co-based superalloy particles. The particles are sprayed at a spray temperature that is less than a melting point of both the Ni-based superalloy particles and the Co-based superalloy particles. A repaired coated component may include: a Ni-based alloy component having a surface and a coating on the surface of the Ni-based alloy component. The coating comprises a plurality of deformed particles therein, with the plurality of deformed particles comprises 5% by weight to 80% by weight of a Ni-based superalloy and 20% by weight to 95% by weight of a Co-based superalloy.
Methods of protecting a surface of a Ni-based alloy component are provided, along with the wear strip utilized and the repaired Ni-based alloy component. The method may include: spraying a plurality of particles to form a wear strip. The plurality of particles includes a mixture of Ni-based superalloy particles and Co-based superalloy particles. The plurality of particles is sprayed at a spray temperature that is less than a melting point of the Ni-based superalloy particles and less than a melting point of the Co-based superalloy particles. The wear strip may be attached onto a surface of the Ni-based alloy component, either during the spraying of the particles (when wear strip formed on the surface of the Ni-based alloy component) or after a standalone wear strip is formed.
C23C 24/04 - Impact or kinetic deposition of particles
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
C22C 19/07 - Alloys based on nickel or cobalt based on cobalt
C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
A power system is provided. The power system includes: an electric machine comprising a first multiphase winding and a second multiphase winding, the first multiphase winding and the second multiphase winding being electrically opposite in phase with respect to one another; and a power converter system having: first switching elements in electric connection with the first multiphase winding and having a DC side and an AC side; second switching elements in electric connection with the second multiphase winding and having a DC side and an AC side; a plurality of capacitors coupled to the first switching elements on the DC side of the first switching elements and to the second switching elements on the DC side of the second switching elements; and a means for reducing common mode currents on the AC side of the first switching elements and on the AC side of the second switching elements.
General Electric Deutschland Holding GmbH (Germany)
Inventor
Chaudhari, Pushkar Chandrakant
Osama, Mohamed
Abstract
A method for operating an electric machine assembly is provided. The electric machine assembly includes an electric machine having a first set of windings and a second set of windings. The method includes: operating the electric machine in a partial phase mode, wherein operating the electric machine in the partial phase mode comprises: powering a first set of windings to provide a net zero current in the first set of windings while maintaining one phase of the first set of windings in a non-conducting condition; and powering a second set of windings to provide a net zero current in the second set of windings while maintaining one phase of the second set of windings in a non-conducting condition.
H02P 29/028 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the motor continuing operation despite the fault condition, e.g. eliminating, compensating for or remedying the fault
A system may include a sensor comprising a sensor configured to capture data from a part of an engine. The system being configured to form a three-dimensional (3D) surface model of the part of the engine based on signals received from the sensor system, determine a nonplanar reference surface based on the 3D surface model of the part, and measure a characteristic of a damaged portion of the part of the engine based on the 3D surface model and the nonplanar reference surface.
Variable diameter thrust link apparatus are disclosed. A thrust link for an aircraft engine includes a forward end coupled to the aircraft engine, the forward end having a first diameter, and an aft end coupled to the aircraft engine or a pylon, the aft end having the first diameter, wherein the thrust link defines a thrust link span that extends from the forward end to the aft end, wherein a second diameter greater than the first diameter is defined between the forward end and the aft end, wherein the second diameter spans a center diameter span that is equivalent to or between 60% and 90% of the thrust link span.
Fluid-filled thrust link apparatus and associated method are disclosed. A thrust link for an aircraft engine includes a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine, and a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.
F15B 21/00 - Common features of fluid actuator systemsFluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
73.
GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO
A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by
A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by
V
G
V
GB
.
A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by
V
G
V
GB
.
VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a sump that is a primary reservoir having a first lubricant level and a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level. The lubrication system fills the secondary reservoir with a lubricant between the first lubricant level and the second lubricant level. The gear assembly collects the lubricant in the secondary reservoir to supply the lubricant to the gear assembly.
General Electric Company Polska Sp. z o.o. (Poland)
Inventor
Sibbach, Arthur William
Pazinski, Adam Tomasz
Abstract
An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
Methods are provided for repairing a defect on a silicon-containing substrate. The method may include applying a powder mixture into the defect of an existing coating on a surface of the silicon-containing substrate, wherein the powder mixture comprises silicon and germanium at a Ge mole fraction of 0.01 to 0.3; and heat treating the powder mixture within the defect at a sintering temperature that is 1150° C. to 1400° C. to form a repaired bondcoat within the defect. Repaired components are also provided that include a repaired bondcoat formed within the defect on the silicon-containing substrate, wherein the repaired bondcoat comprises a silicon-germanium phase comprising a Ge mole fraction of germanium of 0.01 to 0.3 and a Si mole fraction of silicon of 0.7 to 0.99.
A neuroactivity monitoring system includes a camera configured to acquire image data of a patient positioned on the patient support and a monitoring device in communication with the camera. The monitoring device uses the acquired image data of the camera to identify and track patient landmarks, such as facial and/or posture landmarks, and, based on the tracked movement, characterize patient neuroactivity.
A radiation hardened semiconductor device including a heavily doped substrate of a semiconductor device, a drift layer having a substantially uniform doping concentration and a thickness is provided. The doping concentration and the thickness of the drift layer are such that when the semiconductor device is operating at a maximum voltage rating, an electrical field profile in the drift layer extends less than 80% of the thickness of the drift layer, providing the radiation hardened nature of the device.
An electrodialysis cell includes a housing defining an internal chamber, a core positioned within the internal chamber, a first electrode positioned in the internal chamber adjacent the housing, a second electrode coupled to the core and spaced from the first electrode, and a membrane assembly positioned between the first and second electrodes in a spiral wound configuration. The housing includes an inlet end for receiving a feed fluid and an outlet end in fluid communication with the inlet end. The membrane assembly includes a plurality of ion exchange membranes spaced from each other to define a plurality of fluid channels between the inlet and outlet ends.
C02F 1/469 - Treatment of water, waste water, or sewage by electrochemical methods by electrochemical separation, e.g. by electro-osmosis, electrodialysis, electrophoresis
A turbine engine for an aircraft. The turbine engine includes a core turbine engine and a steam system. The steam system extracts water from combustion gases, vaporizes the water to generate steam, and injects the steam into a core air flow path of the core engine to add mass flow to core air. A core hot gas path component may be fluidly connected to a hot gas path that routes combustion gasses from the combustor. The core turbine engine may also include a turbine fluidly connected to the hot gas path to receive the combustion gases. The turbine may include a turbine airfoil. Each of the core hot gas path component and the turbine airfoil includes a combustion-gas-facing surface facing the hot gas path. A hydrophobic coating is formed on the combustion-gas-facing surface, reducing wetting of water vapor within the combustion gases on the core hot gas path component.
GE Marmara Technology Center Muhendislik Hizmetleri Ltd (Turkey)
GENERAL ELECTRIC COMPANY (USA)
Inventor
Ataman, Volkan
Yasar, Fatih
Deniz, Emrah
Bucaro, Michael T.
Abstract
A gas turbine engine comprising a combustion section enshrouded by a casing having at least one through passage, the combustion section comprising a dome wall and a liner at least partially defining a combustion chamber; a fuel nozzle connected to the dome wall and having a nozzle tube; and a coupling securing the fuel nozzle with casing and disposed at least partially in the at least one through passage.
GE Marmara Technology Center Muhendislik Hizmetleri Ltd (Turkey)
GE Aerospace Poland sp. z o.o. (Poland)
Inventor
Deniz, Emrah
Yasar, Fatih
Mikolajczyk, Katarzyna Anna
Bucaro, Michael T.
Kacar, Ahmet
Wang, Anquan
Li, Hejie
Gonyou, Craig Alan
Brady, Aaron C.
Abstract
A gas turbine engine comprises a compressor section, a combustion section, and a turbine section in a serial flow arrangement and enshrouded by a casing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; a plurality of combustor cups circumferentially arranged on the dome wall; a fuel supply connected to the casing; and a fuel nozzle passing through the casing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two combustor cups of the plurality of combustor cups; wherein the fuel nozzle is fixed to the at least two combustor cups.
A method for predicting distortion of a part during sintering in an additive process includes receiving a computerized representation of a complex geometric part, discretizing the computerized representation of the complex geometric part into a plurality of elements, processing the plurality of elements of the computerized representation of the complex geometric part with a machine-learning model configured to predict a distorted geometry of the complex geometric part in response to a sintering process, wherein the machine-learning model is trained to predict distortion of a set of primitive geometric coupons represented by image data fed into the machine-learning model during training, the set of primitive geometric coupons having fewer geometries than the complex geometric part, the complex geometric part comprises a plurality of geometries corresponding to geometries associated with the set of primitive geometric coupons, and generating a computerized representation of the predicted distorted geometry of the complex geometric part.
A method for forming an object includes moving a recoat assembly over a build material, where the recoat assembly includes a first roller and a second roller that is spaced apart from the first roller, moving the second roller above the first roller in a vertical direction, rotating the first roller of the recoat assembly in a counter-rotation direction, such that a bottom of the first roller moves in a coating direction, contacting the build material with the first roller of the recoat assembly, thereby fluidizing at least a portion of the build material, while the second roller is spaced apart from the build material in the vertical direction, and moving the fluidized build material with the first roller, thereby depositing a second layer of the build material over an initial layer of build material positioned in a build area.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B22F 10/14 - Formation of a green body by jetting of binder onto a bed of metal powder
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 12/00 - Apparatus or devices specially adapted for additive manufacturingAuxiliary means for additive manufacturingCombinations of additive manufacturing apparatus or devices with other processing apparatus or devices
A cleaning system for an additively manufactured component includes a tank storing a cleaning fluid. A fluid circuit is operably coupled with the tank. A pump is coupled with the fluid circuit. A manifold is configured to receive fluid from the fluid circuit through the pump. At least one of a coupler defined by the manifold or a hose is coupled with the manifold. The at least one of the coupler defined by the manifold or the hose is further configured to couple with said additively manufactured component.
B08B 3/02 - Cleaning by the force of jets or sprays
B08B 3/10 - Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration
B08B 3/12 - Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration by sonic or ultrasonic vibrations
B08B 5/02 - Cleaning by the force of jets, e.g. blowing-out cavities
B08B 5/04 - Cleaning by suction, with or without auxiliary action
An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to:
An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to:
h
L
.
A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
A turbine engine for an aircraft. The turbine engine includes a combustor and a steam system. Fuel and steam are injected into the combustor to mix with compressed air to generate a fuel and air mixture. The fuel and air mixture is combusted in the combustor to generate combustion gases. The steam system is fluidly coupled to the combustor as the steam source to provide steam to the combustor. The steam system includes a hot gas path and a steam hot gas path component. The hot gas path is fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system. The steam hot gas path component includes a wall having a combustion-gas-facing surface facing the hot gas path and a hydrophobic coating formed on the combustion-gas-facing surface.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
A turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order and together defining a working gas flow path; a thermal system operable with the turbomachine; a heat exchanger in fluid communication with the thermal system; and a plurality of elongated delivery devices in fluid communication with the compressor section of the turbomachine. The plurality of elongated delivery devices are configured to deliver a fluid from the compressor section to a surface of the heat exchanger.
B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F02C 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02K 3/10 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluidControl thereof by after-burners
89.
PROBABILISTIC FATIGUE AND BLEND LIMIT ASSESSMENT AND VISUALIZATION METHODS FOR AIRFOILS
A method of analyzing a blended airfoil that includes generating a plurality of simulated blended airfoil designs each including one of a plurality of blend geometries, training surrogate models representing the plurality of simulated blended airfoil designs based on natural frequency, modal force, and Goodman scale factors, determining a likelihood of operation failure of each of the plurality of blended airfoil designs in response to one or more vibratory modes, determining which of the plurality of simulated blended airfoil designs violate at least one aeromechanical constraint and generating, a blend parameter visualization including a blend design space, where the blend design space includes one or more restricted regions indicating blended airfoil designs where at least one aeromechanical constraint is violates and one or more permitted regions indicating blended airfoil designs where no aeromechanical constraints are violated.
90.
ADDITIVE MANUFACTURING USING SOLID STATE OPTICAL DEFLECTORS
An additive manufacturing apparatus comprises a laser beam source emitting a laser beam, a build platform, a powder source depositing a layer of powder onto the build platform, and a scanning assembly disposed along an optical path between the laser beam source and the build platform. The scanning assembly comprises at least one solid state optical deflector that modifies at least one of a size or an impingement location of the laser beam on the layer of powder at a scanning position of the laser beam. The at least one solid state optical deflector may be used to heat treat the layer of powder either before or after the powder is melted.
B29C 64/273 - Arrangements for irradiation using laser beamsArrangements for irradiation using electron beams [EB] pulsedArrangements for irradiation using laser beamsArrangements for irradiation using electron beams [EB] frequency modulated
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
92.
SYSTEM AND METHOD FOR DETECTING AND REDUCING TORQUE IN A TURBINE ENGINE
A gas turbine engine includes a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox, a grounded structure coupled to and supporting the power gearbox, and a torque monitoring system. The torque monitoring system includes a gearbox sensor. The gearbox sensor is coupled to the grounded structure and the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor.
F02C 9/58 - Control of fuel supply conjointly with another control of the plant with power transmission control with control of a variable-pitch propeller
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
A turbine engine for an aircraft. The turbine engine includes a combustor fluidly coupled to a fuel delivery assembly to receive fuel from the fuel delivery assembly. The fuel is injected into the combustor and combusted in the combustor to generate combustion gases. A condenser is located downstream of the combustor to receive the combustion gases and to condense water. A fuel heat exchanger is thermally coupled to the condenser by at least one heat transfer loop to receive heat from the condenser.
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
F02C 7/16 - Cooling of plants characterised by cooling medium
A turbine engine for an aircraft. The turbine engine includes a combustor fluidly coupled to a fuel delivery assembly to receive fuel from the fuel delivery assembly. The fuel is injected into the combustor and combusted in the combustor to generate combustion gases. A condenser is located downstream of a turbine to receive the combustion gases and to condense water. The fuel heat exchanger is thermally coupled to the condenser to receive heat from the water condensed by the condenser. The fuel heat exchanger is located in the fuel delivery assembly to receive the fuel and to transfer the heat received from the water to the fuel. The boiler is located downstream of the fuel heat exchanger. The boiler receives the water and is fluidly connected to the combustor to receive the combustion gases and to boil the water to generate steam.
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
95.
Method of operating a turbine engine having a bleed system
A method of operating a turbine engine. The turbine engine includes a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages, and a bleed system. The bleed system includes a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages. The method includes directing compressed air through the high-pressure compressor flowpath, directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow, directing a second portion of the compressed air through the second bleed flowpath, determining an altitude of the turbine engine, and changing the first mass flow of the first portion of the compressed air through the first bleed flowpath based on the altitude of the turbine engine.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
96.
TURBINE ENGINE HAVING A VARIABLE PITCH AIRFOIL ASSEMBLY
A turbine engine comprising a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement and defining a stator portion and a rotor portion, which rotates about an engine centerline. The rotor portion comprising a variable pitch airfoil assembly. The variable pitch airfoil assembly having an airfoil and a balancing insert.
A control circuit accesses three-dimensional image information for a given three-dimensional object. The control circuit accesses a selection corresponding to a feature of the three-dimensional object, and then automatically generates a plurality of synthetic images of the three-dimensional object as a function of the three-dimensional and the selection of the aforementioned feature. By one approach, these synthetic images include supplemental visual emphasis corresponding to the aforementioned feature. The generated plurality of synthetic images can then be used as a training corpus when training a machine learning model.
On-cable pressure barrier device (6) fitted on a cable comprising an insulating sheath (3 d) around a plurality of wires (3 e) individually insulated, a part of said cable within the on-cable pressure barrier device is stripped of all insulation in order to expose the conducting core (6d1,6d2) of each wire -(6c1,6c2) of the plurality of wires, the on-cable pressure barrier device (6) comprising a resin part (6f) extending over, a first part (6d1) of the exposed conducting core of each wire connected to a first part (3c1) of the cable through a first part (6d1) of said wire, a second part (6d2) of the exposed conducting core of each wire connected to a second part (3c2) of the cable through a second part (6c2) of said wire extends outside said resin part (6f), the exposed conducting core of each wire and the resin part (6f) being able to stop the diffusion of gas incoming from the first part of the cable.
09 - Scientific and electric apparatus and instruments
10 - Medical apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Computer software for collecting and analyzing data in the field of healthcare; hardware, computer software and firmware for automating control of medical equipment; software for information management, data collection and data analysis in the fields of asset optimization, machine diagnostics, and optimization of healthcare and hospital processes; computer hardware and software for medical imaging and for analysis of data gathered from a medical diagnostic apparatus to enhance clinical decision making; computer hardware and software for use with medical patient monitoring equipment, for receiving, processing, transmitting and displaying data; computer software for analyzing medical diagnostic information; computer software for controlling and managing patient medical information; computer software for electrical signaling in a patient to diagnose and/or treat medical conditions; computer software for automating and analyzing the administrative, financial, billing, and clinical records of healthcare organizations, providing healthcare regulatory compliance information, for capturing, distributing, managing and viewing electronic documents, for electronic data interchange (EDI) of healthcare transaction information, and for managing workflow in the delivery of healthcare; Computer software used to capture, store, track, report and monitor radiation levels delivered by medical devices and instruments. Medical imaging apparatus for screening and diagnostic use and for use in planning intervention and surgery; medical devices, namely, bone densitometer machines; patient monitoring equipment, namely patient monitors for monitoring patient physiological data; fetal and neonatal monitoring systems comprised of instruments for monitoring and measuring fetal and human body reactions; medical equipment namely wireless patient monitoring platform and wearable sensors for gathering data from patients to be viewed remotely on monitors and mobile devices, namely, smart phones and tablets; medical ventilators; anesthesia machines for use in patient care; electrocardiographs; apparatus for monitoring and recording electrocardiographic data from patients; incubators for babies; warming device for stabilizing infant body temperature for medical purposes; phototherapeutic apparatus for medical purposes for infant care; replacement parts for medical diagnostic and medical imaging equipment. Software as a service SaaS services featuring software for data collection and data analytics, for use in the field of healthcare; software as a service SaaS services featuring software for use in asset optimization, machine diagnostics, and optimization of healthcare processes; technical support services, namely, troubleshooting of computer software problems; remote diagnosis of medical and clinical equipment for determining the need for repair; providing technical consulting services to start-ups in the field of Healthcare IT and development of software applications for use in the medical field; providing real time monitoring of networked medical and Internet of Things (IOT) devices installed in a hospital or other healthcare facilities for detecting unauthorized access or data breach.
