A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.
A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.
F28D 1/03 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits
A method of operating a lubrication system for a turbine engine having a fan and one or more rotating components. The lubrication system includes a primary lubrication system and an auxiliary lubrication system. The method includes supplying lubricant to the one or more rotating components from the primary lubrication system during a normal operation of the turbine engine, determining whether at least one of a fuel pressure is less than a fuel pressure threshold or a hydraulic pressure is less than a hydraulic pressure threshold, and activating the auxiliary lubrication system to supply the lubricant to the one or more rotating components from the auxiliary lubrication system when the fuel pressure is less than the fuel pressure threshold or the hydraulic pressure is less than the hydraulic pressure threshold.
A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.
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 gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system is provided that adjusts parameters of the fuel based on data received from the sensors.
A system and method for using a fuel with an engine, an airframe having an aircraft heat load, a fuel tank, and a fuel oxygen reduction unit are provided. The method includes receiving an inlet fuel flow in the fuel oxygen reduction unit for reducing an amount of oxygen in the inlet fuel flow; separating a fuel/gas mixture within the fuel oxygen reduction unit into an outlet gas flow and an outlet fuel flow exiting the fuel oxygen reduction unit; controlling a first portion of the outlet fuel flow to the engine; and controlling a second portion of the outlet fuel flow to the airframe to transfer heat between the second portion of the outlet fuel flow and the aircraft heat load.
A method of forming an acoustic liner that includes bonding a first side of a facesheet to a first adhesive side of a first solid adhesive film. A second solid adhesive film is bonded to a second side of the facesheet at a first adhesive side of the second solid adhesive film. An acoustic screen is bonded to a second adhesive side of the first solid adhesive film and an acoustic core is bonded to a second adhesive side of the second solid adhesive film.
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.
General Electric Deutschland Holding GmbH (Germany)
Inventor
Osama, Mohamed
Yi, Xuan
Yagielski, John Russell
Huang, Shenyan
Abstract
A rotor of an electric machine is provided. The rotor includes a plurality of laminates arranged along an axial direction, the plurality of laminates including a first laminate having: a body formed of a first material, the first material being a ferromagnetic material; and a structural element formed integrally with the body of a second material, the second material being a non-ferromagnetic material.
H02K 1/276 - Magnets embedded in the magnetic core, e.g. interior permanent magnets [IPM]
H02K 1/02 - Details of the magnetic circuit characterised by the magnetic material
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
A seal assembly for a turbomachine includes a rotating component, a non-rotating component having a ring carrier, a face seal ring, and a joint disposed between the ring carrier and the non-rotating component. The non-rotating component is arranged with the rotating component at a sealing interface. The joint is capable of linear and tilt displacement to allow the non-rotating component to displace with respect to the rotating component. The sealing interface defines a gap between the face seal ring and the rotating component. The seal assembly also includes at least one damping element arranged with the ring carrier for maintaining the seal assembly centrally in a radial direction in the turbomachine. Further, the damping element(s) includes at least one mass element.
An electric machine having a stator circumscribed by a stator sleeve coupled to an interior surface of a housing. A thermal barrier is disposed between an outer surface at the axial center of the stator sleeve and the housing.
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 15/02 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
12.
AN ALTITUDE INSENSITIVE HIGH VOLTAGE INSULATION FOR POWER TRAIN IN AN ELECTRIFIED AIRCRAFT
An altitude insensitive composite coating includes a polymer resin and a plurality of ceramic particles in an electrophoretically formed layer. A fraction of the plurality of ceramic particles in the composite coating is at least 40% by volume. A dielectric strength of the composite coating is at least 30 kilovolts per millimeter (kV/mm) at an air pressure corresponding to high altitude.
A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.
A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.
Devices, systems, methods, and kits of parts for monitoring operation of an electron beam additive manufacturing systems are disclosed. A monitoring system includes one or more measuring devices positioned on the at least one wall in the interior of a build chamber of the additive manufacturing system. Each one of the one or more measuring devices includes a piezoelectric crystal. The monitoring system further includes an analysis component communicatively coupled to the one or more measuring devices. The analysis component is programmed to receive information pertaining to a frequency of oscillation of the piezoelectric crystal. A collection of material on the one or more measuring devices during formation of an article within the build chamber causes a change to the frequency of oscillation of the piezoelectric crystal that is detectable by the analysis component and usable to determine a potential build anomaly of the article.
A system for cooling oil in an aircraft turbine engine includes an intermediate support casing configured to be located between a low-pressure compressor and a high-pressure compressor of the aircraft turbine engine. The system further includes a heat exchanger for cooling the oil by heat exchange with air. The heat exchanger is at least partially integrated into the intermediate support casing.
An apparatus and method to detect and locate electrical faults in an insulated supply conductor sheathed in a conductive screen is disclosed. The apparatus is positioned along the supply conductor between a power supply and an electrical load. The conductive screen is coupled to an electrical ground via a first resistive element. A voltage on the conductive screen is sensed and compared to a threshold to determine whether a fault condition exists. The apparatus is configured to inject a voltage pulse to the conductive screen and detect a reflected pulse therefrom. The location of the fault condition is determined based on an elapsed time between the injection of the voltage pulse and the detection of the reflected pulse.
A rotor assembly includes a rotor core having a rotatable shaft and defining at least one rotor post, a winding wound around the post that defines an end turn, and a winding support assembly including a winding support assembly coupled to the rotatable shaft. The end turn defines a set of channels therethrough and is disposed in a first chamber defined by the winding support assembly.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan; a turbomachine drivingly coupled to the fan, the turbomachine comprising an outer casing; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip; and an accessory gearbox positioned at least partially inward of the outer casing of the turbomachine.
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
F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
F02K 3/075 - 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 controlling flow ratio between flows
Composite components and methods for adding a composite material to a composite component are provided. For example, a method comprises positioning a composite material segment against the composite component to form a component layup; applying an insulating material around at least a portion of the component layup to form an insulated layup; and densifying the insulated layup, where the composite component was previously densified before positioning the composite material segment against the composite component. In some embodiments, the composite material is ceramic matrix composite (CMC) and the composite material segment is a plurality of CMC plies. The composite component may be a CMC gas turbine engine component that comprises an original CMC component and a new CMC material segment joined to the original CMC component through the transfer of silicon between the original CMC component and the new CMC material segment during melt infiltration.
Methods are provided for forming a coating on a surface of a substrate. The method may include: applying a negative charge to the surface of the substrate; electrophoretically depositing a slurry layer onto the surface of the substrate; and densifying the slurry layer on the surface of the substrate at a sintering temperature to form a sintered layer of the coating. The slurry layer may include a plurality of EBC material particles, a cationic polyelectrolyte, a plurality of polymeric binder particles, and a solvent. The plurality of EBC material particles may comprise barium strontium aluminosilicate (BSAS), mullite, silicon, rare earth compounds, or combinations thereof.
C09D 5/44 - Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects producedFilling pastes for electrophoretic applications
C25D 15/00 - Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires
A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.
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
A CVFDR system of an aircraft includes a cockpit voice and flight data recorder (CVFDR) communicatively coupled, via a data communication network, to a set of flight recorder modules. The CVFDR receives a first voltage from a remote first power source. In the event of an interruption of the first voltage, the CVFDR receives a second voltage from a local second power source for a predetermined period.
A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.
A fuel cell assembly is provided, including a fuel cell stack having a fuel cell, the fuel cell having a cathode and an anode; and a multi-gas sensor configured to sense gas composition data of a flow of output products from the cathode, gas composition data of a flow of output products from the anode, gas composition data of a fluid surrounding the fuel cell, or a combination thereof to determine fuel cell leakage diagnostic information.
G01M 3/26 - Investigating fluid tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
A computer implemented method for servicing an engine including receiving information including an initial condition profile, CP1, of the engine; forming a workscope associated with a servicing operation of the engine in view of the initial condition profile, CP1; servicing the engine in view of the workscope; determining at least in part an updated condition profile, CP2, of the engine in view of information acquired during the service; and storing the updated condition profile, CP2, for use in a subsequent service operation.
B60S 5/00 - Servicing, maintaining, repairing, or refitting of vehicles
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
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. 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 training data store may contain training data associated with monitoring node values during normal operation of an industrial asset and simulated abnormal data. An offline model tuning platform accesses the training data from normal operation of the industrial asset and the simulated abnormal data in the training data store. Based on the training data from normal operation of the industrial asset, the simulated abnormal data, an abnormal operating condition, and a constrained optimization solution, controller tuning parameters are created for at least one tuned data-driven adaptive controller such that an operating condition of the industrial asset will move from the abnormal operating condition to a normal operation condition through a stable trajectory. An online monitoring platform receives a stream of current monitoring node values and, when the abnormal operating condition is detected, utilizes the controller tuning parameters to implement the at least one tuned data-driven adaptive controller.
G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.
F04C 2/08 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
31.
GAS TURBINE ENGINE HAVING A HEAT EXCHANGER LOCATED IN AN ANNULAR DUCT
A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.
A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.
Bearings with grooves and methods of producing the same are disclosed. Examples disclosed herein include a bearing having a bearing surface with a groove, the bearing positioned adjacent to a shaft, the groove facing the shaft, and a negative thermal expansion (NTE) material positioned in the groove, the NTE material at least partially filling the groove.
The present disclosure is directed to an additive manufacturing system configured to generate an electron beam directed toward a target to generate x-ray flux. The x-ray flux is directed toward the component through at least one plate with a pinhole. Interactions between the component and the x-ray flux generate x-ray radiation. The at least one detector is configured to detect the x-ray radiation through a pinhole. An analysis component is configured to generate an image comprising a three-dimensional component based on the x-ray radiation detected by the at least detector.
G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
35.
VIBRATION SENSOR AND METHODS FOR DEPOSITION MONITORING
Apparatuses and methods are provided herein that are useful to monitoring a coating deposition process. In some embodiments, a method of monitoring a coating process for a target object involves applying a coating to at least a portion of a beam during at least part of a coating deposition process to obtain a coated beam. The method also includes exciting the coated beam such that the coated beam vibrates. The method also includes monitoring the vibration response of the coated beam and determining at least one of a deposition rate or a drying rate for the target object based on the change in the frequency response of the coated beam.
A system comprises an energy source and detector. The energy source is configured to emit energy from a focal spot. The detector comprises an array of pixels. Each of the pixels of the array of pixels has a centerline extending longitudinally through the pixel. The centerline of each pixel is focally aligned with the focal spot of the energy source. Each of the pixels receives selected amounts of the energy from the energy source that have passed through an object.
G01N 23/04 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material
The present disclosure is generally related to a fault isolation sensor system for use with determining whether a potential fault is more likely to be on a rotor side or a stator side. The measurement signals are transmitted from the rotor antenna to the stator antenna, and then from the stator antenna to a controller. The controller is configured to monitor the measurement signals. If the measurement signal is outside of a predetermined range or past a predetermined threshold, then the stator antenna can be interrogated with an interrogation signal with a reflected signal being compared with the interrogation signal and a ratio thereof being used to identify the potential side of the fault.
G01R 31/11 - Locating faults in cables, transmission lines, or networks using pulse-reflection methods
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
H02K 11/20 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for measuring, monitoring, testing, protecting or switching
38.
METHODS AND APPARATUS TO IMPROVE FAN OPERABILITY CONTROL USING SMART MATERIALS
Systems, apparatus, articles of manufacture, and methods are disclosed to improve fan operability control using smart materials. An engine comprising an engine surface in an airflow path, a sensor positioned on the engine surface, and a smart-material-based feature positioned on the engine surface, the smart-material-based feature triggered to modify the airflow path when the sensor outputs an indication of a detected deviation from a reference value of an operating parameter of the engine.
A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.
A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.
An aircraft defining a vertical direction, a longitudinal direction, and a transverse direction is provided. The aircraft includes: a fuselage; a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage in the transverse direction. The wing includes a support structure that comprises a plurality of first support members and a plurality of second support members. The plurality of first support members extending at least partially between the plurality of second support members. The plurality of vertical thrust electric fans arranged between the plurality of first support members and the plurality of second support members.
A fuel nozzle valve includes a fuel nozzle valve liner having a channel with an opening for allowing fuel to flow therethrough and a seat. A plunger has a stud and a base substantially perpendicular to the stud, the plunger being configured to move relative to the fuel nozzle valve liner to seal or to open the opening of the fuel nozzle valve. The fuel nozzle valve further includes a metal resilient member configured to contact the base of the plunger and the seat of the fuel nozzle valve liner to seal the opening of the fuel nozzle valve when the plunger is moved to seal the fuel nozzle valve.
A fuel oxygen reduction unit is provided for reducing an oxygen content of a flow of liquid fuel to an engine. The fuel oxygen reduction unit includes: a stripping gas supply line for providing a flow of stripping gas; a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet, the stripping gas supply line in airflow communication with the stripping gas inlet; a means for modulating the flow of stripping gas through the stripping gas supply line; and a controller operable with the means for modulating the flow of stripping gas through the stripping gas supply line to modulate the flow of stripping gas through the stripping gas supply line in response to an engine operability parameter.
A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.
General Electric Company Polska sp. z o.o. (Poland)
Inventor
Jasiczek, Michal
Sinha, Shatil
Keshavan, Hrishikesh
Gemeinhardt, Gregory Carl
Graves, John Harvey
Lin, Wendy Wenling
Abstract
A geopolymer composite material includes a geopolymer resin, a fibrous reinforcement material embedded in the geopolymer resin for reinforcing the geopolymer resin, and a protective coating material covering the fibrous reinforcement material embedded in the geopolymer resin to provide a coated fibrous reinforcement material. Further, the geopolymer resin and the coated fibrous reinforcement material are combined together to form a prepreg containing the geopolymer resin being pre-impregnated into the coated fibrous reinforcement material and being curable into a solid matrix.
C04B 20/00 - Use of materials as fillers for mortars, concrete or artificial stone according to more than one of groups and characterised by shape or grain distributionTreatment of materials according to more than one of the groups specially adapted to enhance their filling properties in mortars, concrete or artificial stoneExpanding or defibrillating materials
C04B 28/00 - Compositions of mortars, concrete or artificial stone, containing inorganic binders or the reaction product of an inorganic and an organic binder, e.g. polycarboxylate cements
C04B 40/00 - Processes, in general, for influencing or modifying the properties of mortars, concrete or artificial stone compositions, e.g. their setting or hardening ability
A lubrication system for a turbine engine. The turbine engine includes a fan having a fan shaft and one or more rotating components. The lubrication system includes one or more tanks that stores lubricant therein, a primary lubrication system, and an auxiliary lubrication system. The primary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump that is coupled to the fan shaft. The auxiliary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components based on a pressure of the lubricant in the primary lubrication system. Rotation of the fan shaft causes the auxiliary pump to pump the lubricant to the one or more rotating components.
An apparatus for servicing internal components of an aircraft engine includes a flexible hollow tube; a latching mechanism connected to or incorporated with the flexible hollow tube; and a servicing device to be inserted through the flexible hollow tube. The servicing device is freely moveable through the flexible hollow tube and decoupled from the latching mechanism. The flexible hollow tube is shaped and configured so as to enable proximate positioning of the flexible hollow tube with respect to a rotatable component of an aircraft engine allowing attachment of the flexible hollow tube to the rotatable component via the latching mechanism after the flexible hollow tube is inserted through an entry port of the aircraft engine.
A turbine engine component assembly includes a first part comprising a ceramic matrix composite material and having a first flange defining a first borehole, a second part defining a second borehole, and a pin inserted, in an axial direction, through the first borehole and the second borehole to connect the first part to the second part. The pin includes a first contact portion positioned at a first axial location of the pin corresponding to the first borehole and an elongated portion extending axially from the first contact portion. The first contact portion includes a first chamfered section, a second chamfered section, and a first contact surface between the first chamfered section and the second chamfered section. The first chamfered section and the second chamfered section slope away from the first contact surface with decreasing diameters.
An inlet duct for a nacelle of a ducted fan engine includes an inlet portion having an inlet lip and a hardwall portion, a highlight plane defined at an upstream end of the inlet portion, and an acoustic liner downstream of the inlet portion, a hardwall-acoustic liner interface defined at an interface of the hardwall portion and the acoustic liner. The inlet portion and the acoustic liner are coupled at an inlet-acoustic liner interface extending circumferentially about an inner circumferential surface of the inlet duct. The inlet lip varies circumferentially and axially with respect to the highlight plane and the inlet centerline axis, and includes a plurality of inlet lip crests arranged along the highlight plane, and a plurality of inlet lip troughs arranged downstream of the highlight plane. The hardwall-acoustic liner interface extends circumferentially about the inner circumferential surface and is arranged axially parallel to the highlight plane.
Hybrid electric propulsion systems includes a combustion engine and an electric motor. The hybrid electric propulsion systems may include or utilize a non-transitory computer-readable medium comprising computer-executable instructions, which when executed by a processor associated with the hybrid electric propulsion system, cause the processor to perform a method that includes determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system, and controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.
B64D 31/06 - Initiating means actuated automatically
B60W 10/06 - Conjoint control of vehicle sub-units of different type or different function including control of propulsion units including control of combustion engines
B60W 10/08 - Conjoint control of vehicle sub-units of different type or different function including control of propulsion units including control of electric propulsion units, e.g. motors or generators
B60W 20/10 - Controlling the power contribution of each of the prime movers to meet required power demand
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 37/00 - Arrangements in connection with fuel supply for power plant
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.
B01D 45/16 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by the winding course of the gas stream
B04C 3/00 - Apparatus in which the axial direction of the vortex remains unchanged
B04C 3/06 - Construction of inlets or outlets to the vortex chamber
F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
F01D 9/06 - Fluid supply conduits to nozzles or the like
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 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02K 3/04 - 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
A gas turbine engine is provided. The 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, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core 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
A system (e.g., an ultrasound imaging system) is provided. The system includes an ultrasound probe having a cable, and an ultrasound probe holder configured to receive the ultrasound probe. The system further includes a housing supported by a base. The housing includes a connector port and a cable manage passage. The cable manage passage positioned at an upper end of the housing distal to the base. The cable extending through the cable manage passage, and is attached to the connector port. The ultrasound probe holder is coupled to a front side of the housing.
A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include intertwined fibers defining a three-dimensional structure. A laminate overlay surrounds at least a portion of the inner support structure.
A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include a first core, a second core, and at least one pin. A laminate overlay surrounds at least a portion of the inner support structure.
A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
F02K 3/04 - 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
57.
METHOD AND SYSTEM FOR A BATTERY MONITORING CIRCUIT
A method and system for determining the health of a set of batteries through the use of a battery monitoring circuit. The battery monitoring circuit including a first current loop and a second current loop. The first current loop being enabled by a first switch, a first resistor and a second switch. The second current loop being enabled by the first switch, a third switch, a voltage sensor, and the second switch.
A snake-arm robot and a servicing device are mechanically coupled. The mechanical coupling is accomplished by a longitudinal insertion of the snake-arm robot into the servicing device or the servicing device into the snake-arm robot. An actuator moves the snake-arm robot through a passage within an engine until the snake-arm robot reaches a desired location. The movement of the snake-arm robot concurrently moves the servicing device through the passage. Subsequently, the snake-arm robot is de-coupled from the servicing device and the snake-arm robot is removed from the engine while leaving the servicing device in place within the engine.
A turbine engine includes a rotor, a stator having an aft wall, and a seal assembly having a plurality of seal segments disposed between the rotor and the stator. The rotor, the stator, and the seal assembly are arranged together to define a high pressure region and a low pressure region. The turbine engine also includes at least one biasing member engaged with one or more of the plurality of seal segments. The plurality of seal segments include a primary seal segment and a secondary seal segment connected together via a flexible joint. As such, the flexible joint allows for angular misalignment between the primary seal segment and the secondary seal segment, thereby allowing the primary seal segment to move with the rotor while the secondary seal segment maintains contact with the aft wall of the stator.
This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include one or more paired rotors and stators and at least one interface between the rotors and the stators. The components of the stator may be axially and radially movable by vibrations and other mechanical interference. The stators comprise a sealing element, a seal housing, and a stator interface connected to the engine housing. In some examples, seal assembly includes a damping element to isolate one or more of the rotating components from vibrations mechanical interference that might misalign the rotating components from the stationary components while the turbomachine is operational. In some examples, the damping element is positioned between the seal housing and the stator interface. In other examples, the damping element is positioned between the stator interface and the engine housing.
A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
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 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
A composition of matter is generally provided, in one embodiment, a titanium alloy comprising 5 wt % to 8 wt % aluminum; 2.5 wt % to 5.5 wt % vanadium; 0.1 wt % to 2 wt % of one or more elements selected from the group consisting of iron and molybdenum; 0.01 wt % to 0.2 wt % carbon; up to 0.3 wt % oxygen; silicon and copper; and titanium. A turbine component is also generally provided, in one embodiment, that comprises an article made from a titanium alloy. Additionally, methods are also generally provided for making an alloy component having a beta transus temperature and a titanium silicide solvus temperature.
Example variable bleed valve assemblies for a gas turbine engine are disclosed herein, including a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, and an acoustic suppressor positioned on a wall of the port, the acoustic suppressor extending circumferentially along the wall by a length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion.
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
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
65.
GEARBOX ASSEMBLY LUBRICATION SYSTEM FOR A TURBINE ENGINE
A lubrication system for a gearbox assembly for a turbine engine. The gearbox assembly includes a gear assembly including one or more gears and one or more bearings. The lubrication system includes a sump. The sump is a primary reservoir that has a first lubricant level. The lubrication system also includes a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level that is greater than the first lubricant level. A plurality of drain ports includes a first drain port and a second drain port. The lubrication system fills the secondary reservoir with lubricant between the first lubricant level and the second lubricant level and a portion of the lubricant drains though the second drain port. The one or more gears collects the lubricant to supply the lubricant from the secondary reservoir to the one or more gears or to the one or more bearings.
A turbine engine has a longitudinal centerline axis. The turbine engine includes a fan, a turbo-engine, and a unidirectional brake. The fan includes a plurality of fan blades that rotate in a first direction about the longitudinal centerline axis. The turbo-engine includes a combustor that combusts compressed air and fuel to generate combustion gases and a low-pressure turbine including a low-pressure shaft. The low-pressure turbine receives the combustion gases to rotate the low-pressure turbine. The fan is coupled to the low-pressure shaft such that rotation of the low-pressure shaft causes the fan to rotate in the first direction. A unidirectional brake is coupled to the low-pressure shaft to prevent rotation of the low-pressure shaft and, thus, the fan in a second direction opposite the first direction.
A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.
Methods and systems for calibrating a model are provided herein. In some embodiments, the methods include receiving, via a control circuit, test data for an operational parameter of a real-world system, such as an engine, from operational tests. The control circuit also receives model data for the operational parameter from simulations performed via a model of the engine. The control circuit then compresses the test data and the model data to generate compressed test data and compressed model data and fusing the compressed test data with the compressed model data to generate fused data. The control circuit performs parallel Bayesian inference simulations using the fused data to identify at least one value for a tuning parameter of the model. The control circuit may identify and select tuning parameters to match the model data with test data, the model data may be one or more model outputs (i.e., output parameters).
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
69.
METHOD OF GENERATING POWER WITH AN ELECTRIC MACHINE
General Electric Deutschland Holding GmbH (Germany)
Inventor
Zatorski, Darek Tomasz
Ostdiek, David Marion
Osama, Mohamed
Solomon, William Joseph
Abstract
A method is provided of generating electric power with an electric machine. The method includes rotating a rotor of the electric machine relative to a stator of the electric machine with a shaft of a gas turbine engine during an operating condition of the gas turbine engine, the gas turbine engine being a three-stream gas turbine engine defining an axial direction, the three-stream gas turbine engine comprising: the shaft, a primary fan operatively coupled with the shaft, a mid-fan positioned downstream of the primary fan and operatively coupled with the shaft, a low pressure turbine operatively coupled with the shaft, wherein rotating the rotor of the electric machine relative to the stator of the electric machine comprises generating an electric machine power during the operating condition and generating a low pressure turbine power during the operating condition.
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
71.
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. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
72.
Turbine engine with fan bypass water injection to augment thrust
A gas turbine has a core turbine engine, and a fan having a plurality of fan blades. A nacelle surrounds the fan and at least a portion of the core turbine engine. The nacelle defines an inlet arranged upstream of the fan, and a bypass flow passage downstream of the fan defined between the nacelle and the core turbine engine. The gas turbine also includes a bypass flow passage water injection system that includes (a) at least one water injection nozzle assembly arranged to inject water into at least one of the inlet of the nacelle, or into the bypass flow passage, and (b) a water injection supply system arranged to supply water from a storage tank to the at least one water injection nozzle assembly. Water is provided by the bypass flow passage water injection system during a high power operating states of the gas turbine to augment thrust.
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 3/06 - 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
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
Goods & Services
Insulating and switching gas for high voltage electrical transmission equipment; Electrical power instrument transformers; Fiber optic cables; Gas insulated electrical substations; Gas insulated electrical switchgear panels and switchgear controls; Electrical voltage and electrical current measurement devices; Gas monitoring devices, including multiple gas transformer dissolved gas analysis (DGA) devices; Low power instrument transformers; Circuit breakers, fuses and switches, namely, circuit protection devices, to protect, control and isolate electrical equipment Lifecycle assessment services for electrical grid equipment and services; Power transformer oil recycling services; Electrical grid repair and retrofitting services
A lock lug for inhibiting movement of a plurality of rotor blades includes a body and an engagement mechanism. The body is sized and configured to be received within the rim slot of the rotor disk and defines a dovetail receiving aperture. The engagement mechanism extends from the body and has a retracted configuration configured to allow entry and exit of a dovetail of at least one or more of the plurality of rotor blades into and out of the dovetail receiving aperture and an extended configuration configured to block the dovetail from entering the dovetail receiving aperture.
A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
A gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a low speed spool; a rotor assembly coupled to the low speed spool; an electric machine mechanically coupled to the low speed spool at a connection point of the low speed spool; and a clutch positioned in the torque path of the low speed spool between the connection point and the rotor assembly
F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
A powder reclamation system is provided. The powder reclamation system includes a support structure; a filter housing movable relative to the support structure, the filter housing defining an inlet and an outlet; a raw reclaimed powder hopper in communication with the inlet of the filter housing; a first reclamation passageway in communication with the raw reclaimed powder hopper and configured to be in communication with a first metal powder processing device to recover a first unused portion of a first powder from the first metal powder processing device to the raw reclaimed powder hopper; and a second reclamation passageway in communication with the raw reclaimed powder hopper and configured to be in communication with a second metal powder processing device to recover a second unused portion of a second powder from the second metal powder processing device to the raw reclaimed powder hopper.
B07B 9/00 - Combinations of apparatus for screening or sifting or for separating solids from solids using gas currentsGeneral arrangement of plant, e.g. flow sheets
B22F 10/00 - Additive manufacturing of workpieces or articles from metallic powder
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
General Electric Company Polska sp. z o.o. (Poland)
Inventor
Owoeye, Eyitayo James
Ganiger, Ravindra Shankar
Pazinski, Adam Tomasz
Abstract
A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals:
A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals:
[
HTSA
OGV
×
BPR
(
BPR
+
1
)
×
C
air
×
(
T
inlet
-
T
air
)
×
v
flight
×
D
fan
Fn
Total
×
v
tip
speed
×
Δ
H
]
1
/
3
,
and
wherein
HTSA
OGV
=
N
vane
×
D
fan
2
×
(
1
-
R
OGV
_
ratio
2
)
2
×
sin
(
180
/
N
vane
)
×
sin
θ
OGV
×
f
OGV
.
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
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
80.
SYSTEM AND METHOD FOR EFFICIENTLY DETERMINING A PHASE SHIFT IN A PROPULSION SYSTEM
A propulsion system includes at least two propulsors. The at least two propulsors each comprising a fan having a plurality of fan blades. A controller includes memory and one or more processors. The memory stores instructions that when executed by the one or more processors cause the system to perform the following: determine a pairwise phase difference between one propulsor of the at least two propulsors and another propulsor of the at least two propulsors; generate a reference phase angle; determine a target phase shift for each propulsor of the at least two propulsors; and adjust a speed of each propulsor of the at least two propulsors based on the target phase shift until the pairwise phase difference is equal to the reference phase angle.
A circumferential row of vanes for a gas turbine engine, the circumferential row of vanes has non-uniform spacing. The circumferential row of vanes includes a plurality of stator vanes arranged circumferentially about an inner ring. The plurality of stator vanes include a first group of stator vanes having a first spacing between adjacent stator vanes of the first group of stator vanes and a second group of stator vanes having a second spacing between adjacent stator vanes of the second group of stator vanes. The second spacing is from two percent to eleven percent greater than a nominal uniform vane spacing or from two percent to eleven percent lesser than the nominal uniform vane spacing, the nominal uniform vane spacing being defined by a total number of the plurality of stator vanes. An engine includes the circumferential row of vanes.
Example apparatus, systems, and methods for rapid active clearance control of inter-stage and mid-stage seals are disclosed. An example apparatus to control clearance for a turbine engine comprises a case surrounding at least part of the turbine engine and defining an opening therethrough; a nozzle, the nozzle including a reference pressure sensor and a static pressure sensor on a tip of the nozzle; an actuator including a multilayer stack of material, a rod coupled to the first actuator and coupled to the nozzle through the opening in the case, the rod to move the nozzle based on contraction or expansion of the multilayer stack of material; and a controller to calculate and set the clearance between the rotor and the nozzle by supplying an electrical current to the multilayer stack to cause the multilayer stack to at least one of expand or contract.
A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, a compressor of the compressor section comprising an aft-most compressor stage; a stage of stator vanes located downstream of the aft-most compressor stage; a stator case including a seal pad; and a spool drivingly coupled to the compressor, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the spool comprising a seal tooth assembly, the seal tooth assembly including a seal support extension, a seal tooth extending from the seal support extension toward the seal pad, and a dampener operable with the seal support extension.
A contactor apparatus and method for operating the contactor apparatus can include a contactor assembly with a contactor coil operably coupled to a contactor switch. One or more sensors can be provided in the contactor assembly adapted to measure one or more aspects of the contactor assembly. Based upon the measured aspects, a controller can initiate operation of the contactor switch to effectively toggle the contactor switch at a zero-crossing point along an alternating current waveform.
H01H 47/18 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for modifying the operation of the relay for introducing delay in the operation of the relay
B64D 41/00 - Power installations for auxiliary purposes
H01H 9/56 - Circuit arrangements not adapted to a particular application of the switching device and for which no provision exists elsewhere for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 33/59 - Circuit arrangements not adapted to a particular application of the switch and not otherwise provided for, e.g. for ensuring operation of the switch at a predetermined point in the AC cycle
H01H 47/00 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current
H01H 47/26 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for supplying energising current for relay coil having thermo-sensitive input
H02H 3/02 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details
A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.
A propulsion system includes at least two propulsors. The at least two propulsors each include a fan and a controller having one or more processors configured to implement controller logic. The controller logic includes a phase angle control scheme and a speed control scheme. In implementing the controller logic, the one or more processors are configured to: determine an actual pairwise phase difference between a pair of propulsors of the at least two propulsors; generate a reference phase angle for the pair of propulsors; compare the actual pairwise phase difference to the reference phase angle to generate a phase error; provide the phase error to a phase controller module to generate an output based on the phase error; and adjust a speed of at least one propulsor of the at least two propulsors based on the output to drive the phase error towards zero.
General Electric Company Polska sp. z o.o. (Poland)
Inventor
Kumar, Rajesh
Subramanian, Sesha
Raghuvaran, Vaishnav
Ganiger, Ravindra Shankar
Pazinski, Adam Tomasz
Abstract
A gas turbine engine includes a compressor section comprising a compressor, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, the compressor comprising an aft-most compressor stage; a spool drivingly coupled to the compressor; a stage of stator vanes located downstream of the aft-most compressor stage; and a stator case, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the stage of stator vanes including a first stator vane defining a fluid passage, and the stator case defining a plenum and a supplemental airflow passage, the plenum in fluid communication with the fluid passage in the first stator vane, the supplemental airflow passage in fluid communication with the plenum and the rotor cavity for proving an airflow to the rotor cavity
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 including a primary combustor liner having an inner liner and an outer liner. A dome wall and a dome inlet are located in the dome wall. At least one opening is located in the outer liner downstream from the 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.
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
F23R 3/34 - Feeding into different combustion zones
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
An aircraft component inspection system is provided. The system includes an image capture system including: an image sensor system, a positioning system, and a processor configured to determine an inspection recipe based at least on an identifier associated with a component of an aircraft being inspected, identify a plurality of locations for performing image capture during an inspection workflow based on the inspection recipe, provide machine instruction to the positioning system to position the image sensor system relative to the component based on the plurality of locations, cause the image sensor system to capture images at the plurality of locations, and store the images with capture location data in an inspection data database.
A printing assembly for an additive manufacturing apparatus includes an energy emitter configured to steer one or more emissions across a build platform to raise a temperature of a build material on the build platform from an initial temperature to a first temperature, the first temperature being less than a threshold temperature set by material dependent metallurgical properties, and a fusing beam emitter configured to generate one or more laser beams to raise the temperature of the build material on the build platform from the first temperature to a second temperature, the second temperature being greater than the threshold temperature.
A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
F02C 3/02 - Gas-turbine plants characterised by the use of combustion products as the working fluid using exhaust-gas pressure in a pressure exchanger to compress combustion-air
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
93.
SYSTEMS AND METHODS FOR ADDITIVELY MANUFACTURING THREE-DIMENSIONAL OBJECTS WITH ARRAY OF LASER DIODES
A system for additively manufacturing a three-dimensional object is provided. The system includes a build platform, an array of laser diodes, each laser diode of the array of laser diodes configured to direct a laser beam toward the build platform, and a controller communicatively coupled to each laser diode of the array of laser diodes such that control signals are communicated from the controller to each laser diode individually.
A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
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 gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
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
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.
F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02K 3/00 - Plants including a gas turbine driving a compressor or a ducted fan
97.
CLEANING FLUIDS FOR USE IN ADDITIVE MANUFACTURING APPARATUSES AND METHODS FOR MONITORING STATUS AND PERFORMANCE OF THE SAME
Embodiments of the present disclosure are directed to additive manufacturing apparatuses, cleaning stations incorporated therein, and methods of cleaning using the cleaning stations.
C09D 11/107 - Printing inks based on artificial resins containing macromolecular compounds obtained by reactions only involving carbon-to-carbon unsaturated bonds from unsaturated acids or derivatives thereof
A decision tool models emissions for a sustainable aircraft fuel (SAF) for the lifecycle of the fuel. The decision tool includes a controller module configured to receive data related to at least one fuel pathway for the fuel wherein the fuel pathway considers emissions from initial feedstock production to fuel burn during flight and arrival. The decision tool determines at least one fuel pathway for the fuel used to fuel the aircraft during a flight, models an emission score for the at least one fuel pathway, and then outputs the emission score where a user can purchase the fuel or make other decisions based upon the fuel pathway provided by the decision tool.
Methods and apparatus to remove liquid from a housing are disclosed. An example system includes a pump including a chamber, a shaft positioned at least partially in the chamber, and a bearing to support the shaft, the chamber including a chamber inlet and a chamber outlet, the chamber to hold a fluid in a first state, a first conduit to carry the fluid in a second state of the fluid, the first conduit fluidly coupled to the chamber inlet, a second conduit to carry the fluid in the first state of the fluid, the second conduit fluidly coupled to the chamber outlet, at least one jet pump to deliver a mixture of the fluid in the first state of the fluid and the second state of the fluid to a third conduit, and a heat exchanger coupled to the first conduit upstream of the first inlet.
A composite airfoil assembly for a turbine engine. The composite airfoil assembly has an airfoil outer surface defining opposing pressure and suction sides, which extend between a leading edge and a trailing edge. The composite airfoil assembly includes a woven core, a skin applied to at least a portion of a core exterior, and a cladding located adjacent the trailing edge, the leading edge, a root, or a tip, where a portion of a skin outer surface defines a first portion of the airfoil outer surface and a cladding outer surface defines a second portion of the airfoil outer surface.
