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.

IPC Classes  ?

• 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
• B64D 27/33 - Hybrid electric aircraft
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02P 6/182 - Circuit arrangements for detecting position without separate position detecting elements using back-emf in windings
• H02P 25/22 - Multiple windingsWindings for more than three phases
• H02P 29/024 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load

Abstract

A power source assembly is provided having a fuel cell module configured to provide a first direct current power output; a battery module configured to provide a second direct current power output; a direct current electric bus configured to provide a net direct current power output to a load; a DC/DC converter in electrical connection with the direct current electric bus, the DC/DC converter configured to receive the first direct current power output from the fuel cell module or the second direct current power output from the battery module; and a controller operably coupled to the DC/DC converter and configured to receive data indicative of the first direct current power output, the controller configured to control the DC/DC converter based on the data indicative of the first direct current power output to maintain a slew rate from the fuel cell module within a slew rate range.

IPC Classes  ?

• B60L 58/40 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for controlling a combination of batteries and fuel cells
• H01M 8/04537 - Electric variables
• H01M 8/04858 - Electric variables
• H01M 16/00 - Structural combinations of different types of electrochemical generators

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.

IPC Classes  ?

• 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

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.

IPC Classes  ?

• F02C 3/00 - Gas-turbine plants characterised by the use of combustion products as the working fluid
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another.

IPC Classes  ?

• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings

Abstract

Casing waste heat recirculation loops and related methods are disclosed. An example engine includes at least one of a compressor or a pump; a casing for at least one of the pump or the compressor, the casing including a conduit formed in a wall of the casing, the conduit to define a recirculation flow path for a fluid at least partially within the wall of the casing; a valve positioned at an inlet to the recirculation flow path; and an actuator operatively connected to the valve and configured to adjust a position of the valve among at least one of open, partially open, or closed, the valve to allow passage of at least a portion of the fluid when at least one of open or partially open.

IPC Classes  ?

• 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
• F02C 7/14 - Cooling of plants of fluids in the plant

Abstract

A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example airfoil includes an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall, and an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner and outer walls.

IPC Classes  ?

• F01D 25/26 - Double casingsMeasures against temperature strain in casings
• F01D 5/14 - Form or construction
• F01D 5/16 - Form or construction for counteracting blade vibration
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/26 - Antivibration means not restricted to blade form or construction or to blade-to-blade connections
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 25/04 - Antivibration arrangements
• F01D 25/12 - Cooling
• F01D 25/14 - Casings modified therefor
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• B33Y 80/00 - Products made by additive manufacturing

Abstract

An electric propulsor is provided. The electric propulsor includes a core cowl and an outer cowl. A first air flowpath is defined radially outward of the outer cowl and a second air flowpath is defined between the core cowl and the outer cowl. The electric propulsor also includes one or more electric machines, a fan rotatably drivable by at least one electric machine, and a booster having a plurality of airfoils disposed at least in part in the second air flowpath, the booster being rotatably drivable by at least one electric machine for compressing air flowing along the second air flowpath. The electric propulsor further includes a heat exchanger disposed within the second air flowpath downstream of the booster, the heat exchanger being in thermal communication with at least one of the one or more electric machines and/or a gearbox mechanically coupled with the fan.

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

f).

IPC Classes  ?

• H02M 1/32 - Means for protecting converters other than by automatic disconnection
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force

Abstract

A prefabricated fairing for a wind turbine blade, the fairing extending along a fairing profile terminating at fairing lips and comprising exterior and interior fairing surfaces and a plurality of layers including fibre-reinforced layers and an exterior erosion-resistant elastomer layer forming a portion of the exterior fairing surface and being configured for defining the leading edge of the wind turbine blade, the fairing further comprises a cured first resin binding the erosion-resistant elastomer layer and the one or more fibre-reinforced layers together.

IPC Classes  ?

• F03D 1/00 - Wind motors with rotation axis substantially parallel to the air flow entering the rotor
• F03D 1/06 - Rotors
• F03D 13/10 - Assembly of wind motorsArrangements for erecting wind motors

Abstract

A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.

IPC Classes  ?

• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F01D 25/12 - Cooling
• F02C 7/16 - Cooling of plants characterised by cooling medium

Abstract

An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.

IPC Classes  ?

• B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
• B60L 50/13 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines using AC generators and AC motors
• B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/275 - Mechanical drives
• H02J 1/10 - Parallel operation of dc sources
• H02K 11/042 - Rectifiers associated with rotating parts, e.g. rotor cores or rotary shafts
• H02P 101/30 - Special adaptation of control arrangements for generators for aircraft

Abstract

A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includes one or more engine loads and an external electrical connection for communicating electrical power between the turbine engine and an electrical system of an aircraft. The turbine engine includes a power management system including a high voltage DC busbar configured to communicate electrical power between the first and second electric machines and the engine loads and the external electrical connection. The power management system includes a control system configured to control power offtake from and injection to the first and second electric machines, and controls power delivered to the one or more engine loads and the external electrical connection.

IPC Classes  ?

• F02C 3/107 - 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
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/275 - Mechanical drives

Abstract

A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.

IPC Classes  ?

• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components

Abstract

A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction

IPC Classes  ?

• F02C 3/067 - 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 having counter-rotating rotors
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

An airgap cooling system (140) for an electric machine (100), the electric machine (100) including a rotor assembly (102) rotatably mounted within a stator assembly (120) and defining an airgap (130) therebetween, wherein the stator assembly (120) comprises a lamination stack (124). The airgap cooling system (140) includes a plurality of distribution passages (142) that extend through the lamination stack (124); a plurality of discharge passages (150) that extend between the plurality of distribution passages (142) and the airgap (130); a cooling manifold (160) defining an annular distribution plenum (164) in fluid communication with the plurality of distribution passages (142), wherein the cooling manifold (160) is configured for receiving a cooling fluid (144) and directing the cooling fluid (144) into the distribution plenum (164), through the distribution passage (142) and the discharge passage (150), and into the airgap (130).

IPC Classes  ?

• H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
• H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use

Abstract

A generator assembly includes a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly including: a stator support structure fixedly attached to the engine stator component; a stator disposed on a supporting surface of the stator support; a manifold coupled to the stator support, the manifold defining a connection volume and including at least one coolant opening at a connection end of the manifold; and an electrical connector extending between the stator and a connection device disposed on the connection end. The generator assembly also includes a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another.

IPC Classes  ?

• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings
• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft

Abstract

A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another.

IPC Classes  ?

• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings
• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft

Abstract

A turbofan engine is provided. The turbofan engine includes a fan; a turbomachine operably coupled to the fan for driving the fan, wherein the turbomachine, the fan, or both include an engine component; a heat source; and a heat transfer system configured to reduce ice buildup or ice formation in the engine component, the heat transfer system in communication with the heat source, the heat transfer system comprising: a first heat transfer component in communication with the heat source; and a second heat transfer component that extends from the first heat transfer component to or through the engine component, wherein the first heat transfer component comprises one of a heat pipe or a graphene rod, and wherein the second heat transfer component comprises the other of the heat pipe or the graphene rod.

IPC Classes  ?

• F02C 7/047 - Heating to prevent icing
• F01D 25/08 - CoolingHeatingHeat insulation

Abstract

A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.

IPC Classes  ?

• 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 3/067 - 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 having counter-rotating rotors
• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

A propulsor is provided including a gas turbine engine having a shaft and one or more bearings supporting the shaft, a rotor hub operatively coupled to the shaft and comprising a hub flange, an electric machine comprising a stator assembly and a rotor assembly, a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange, and an insulated joint for operatively coupling the rotor assembly with the shaft. The insulated joint includes a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft.

IPC Classes  ?

• H02K 11/40 - Structural association with grounding devices
• H02K 11/21 - Devices for sensing speed or position, or actuated thereby
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 11/02 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for suppression of electromagnetic interference
• H02K 24/00 - Machines adapted for the instantaneous transmission or reception of the angular displacement of rotating parts, e.g. synchro, selsyn
• H03H 1/00 - Constructional details of impedance networks whose electrical mode of operation is not specified or applicable to more than one type of network

Abstract

A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine that includes a stator assembly and a rotor assembly rotatable with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both relative to one another. In addition, the turbomachine includes a controller configured to receive data indicating an operating state of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component.

IPC Classes  ?

• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02P 9/00 - Arrangements for controlling electric generators for the purpose of obtaining a desired output

Abstract

A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.

IPC Classes  ?

• F01D 11/16 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means

Abstract

A trailing edge panel is configured to be attached to a trailing edge of a wind turbine blade and includes a base element and a number of protruding aerodynamic elements. The base element has an attachment part configured to be attached to and extend from the trailing edge of the wind turbine blade and to an upstream position on a first blade side of the wind turbine blade. The base element further has a serrated part extending from the second side of the attachment part and configured to project out from the trailing edge of the wind turbine blade, wherein the serrated part comprises a number of serrations, including a first serration and a second serration. The number of protruding aerodynamic elements, including a first protruding aerodynamic element, includes a first protruding part attached to the serrated part of the base element.

IPC Classes  ?

• F03D 1/06 - Rotors

Abstract

A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Abstract

A combustor includes an annular dome and a plurality of dampers integral with the annular dome. Each of the plurality of dampers includes an adjustable damper cover and a damper portion defining a cavity having a volume. The damper cover is mounted to the damper portion integrated with the annular dome and is movable to adjust the volume of the cavity to adjust a frequency of each of the plurality of dampers to reduce an acoustic amplitude of the combustor.

IPC Classes  ?

• F23M 20/00 - Details of combustion chambers, not otherwise provided for

Abstract

A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.

IPC Classes  ?

• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components
• F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.

IPC Classes  ?

• F01D 25/26 - Double casingsMeasures against temperature strain in casings
• F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Abstract

A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.

IPC Classes  ?

• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components

Abstract

An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 25/12 - Cooling
• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements

Abstract

A power system including a power converter system and an electric machine is provided. In one aspect, the power converter system has first and second switching elements. The electric machine includes a first multiphase winding electrically coupled with the first switching elements and a second multiphase winding electrically coupled with the second switching elements. The first and second multiphase windings are arranged and configured to operate electrically opposite in phase with respect to one another. One or more processors control the first switching elements to generate first pulse width modulated (PWM) signals based on received voltage commands to render a first common mode signal and also control the second switching elements to generate second PWM signals based on received voltage commands to render a second common mode signal. The rendered first and second common mode signals have the same or similar waveform with opposite polarity with respect to one another.

IPC Classes  ?

• H02M 7/5395 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency by pulse-width modulation
• H02P 27/08 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters with pulse width modulation
• H02P 25/22 - Multiple windingsWindings for more than three phases
• B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
• H02M 1/44 - Circuits or arrangements for compensating for electromagnetic interference in converters or inverters
• B64D 27/02 - Aircraft characterised by the type or position of power plants

Abstract

A compressor section of a gas turbine engine includes an upstream portion and a downstream portion. The upstream portion includes at least one stage of stator vanes and at least one stage of blades configured to rotate about an axial centerline of the compressor section. The at least one stage of stator vanes and the at least one stage of blades are in an alternating arrangement along an axial direction of the gas turbine engine. The downstream portion is disposed immediately adjacent to and downstream along the axial direction from the upstream portion. The downstream portion includes a first set of rotating blade rows and a second set of rotating blade rows. The first and second sets of rotating blade rows are in an alternating arrangement along the axial direction of the gas turbine engine. The first and second sets of rotating blade rows are in a counter-rotating arrangement.

IPC Classes  ?

• F02C 3/067 - 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 having counter-rotating rotors
• F04D 19/02 - Multi-stage pumps

Abstract

An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.

IPC Classes  ?

• B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
• B60L 50/13 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines using AC generators and AC motors
• B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/275 - Mechanical drives
• H02J 1/10 - Parallel operation of dc sources
• H02K 11/042 - Rectifiers associated with rotating parts, e.g. rotor cores or rotary shafts
• H02P 101/30 - Special adaptation of control arrangements for generators for aircraft

Abstract

A gas turbine engine is provided having a static structure including a flowpath wall. A fluid circuit is extended through the flowpath wall and includes a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit, in which the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/26 - Double casingsMeasures against temperature strain in casings
• F01D 9/06 - Fluid supply conduits to nozzles or the like

Abstract

A three-stream gas turbine engine with an embedded electric machine and methods of operating the same are disclosed. In one aspect, a three-stream engine includes an electric machine operatively coupled with a shaft of the engine. The three-stream engine also includes a core engine and a primary fan and a mid-fan positioned upstream of the core engine. The primary fan and the mid-fan are operatively coupled with the shaft. During operation, the three-stream engine defines a tip speed ratio being defined by a tip speed of a rotor of the electric machine to a tip speed of a mid-fan blade of the mid-fan. The tip speed ratio is defined as being equal to or greater than 0.2 and less than or equal to 1.0.

IPC Classes  ?

• 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
• 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

Abstract

A prefabricated fairing for a wind turbine blade, the fairing extending along a fairing profile terminating at fairing lips and comprising exterior and interior fairing surfaces and a plurality of layers including fibre-reinforced layers and an exterior erosion-resistant elastomer layer forming a portion of the exterior fairing surface and being configured for defining the leading edge of the wind turbine blade, the fairing further comprises a cured first resin binding the erosion-resistant elastomer layer and the one or more fibre-reinforced layers together.

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B64C 27/473 - Constructional features
• F03D 1/06 - Rotors

Abstract

A prefabricated fairing for a wind turbine blade, the fairing extending along a fairing profile terminating at fairing lips and comprising exterior and interior fairing surfaces and a plurality of layers including fibre-reinforced layers and an exterior erosion-resistant elastomer layer forming a portion of the exterior fairing surface and being configured for defining the leading edge of the wind turbine blade, the fairing further comprises a cured first resin binding the erosion-resistant elastomer layer and the one or more fibre-reinforced layers together.

IPC Classes  ?

• F03D 1/06 - Rotors
• B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
• B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• B64C 27/473 - Constructional features

Abstract

A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway extending at least partially radially therethrough through which a fluid coolant flows and another of the multiple guide vanes includes a heated fluid passageway extending at least partially radially therethrough through which the fluid coolant flows and receives heat from exhaust airflow from the core airflow path.

IPC Classes  ?

• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02C 7/16 - Cooling of plants characterised by cooling medium
• F01D 25/12 - Cooling

Abstract

A hybrid-electric propulsion system is provided. In one example aspect, the hybrid-electric propulsion system includes a power converter and a propulsor. The propulsor includes a gas turbine engine having a shaft and one or more bearings supporting the shaft. The propulsor also includes an electric machine electrically coupled with the power converter. The electric machine includes a stator assembly and a rotor assembly. The rotor assembly has a rotor and a rotor connection assembly. The rotor connection assembly operatively couples the rotor with the shaft. The rotor connection assembly has an insulated joint for interrupting common mode electric current from flowing from the rotor of the electric machine to the shaft. A grounding device is included to electrically ground the shaft. The power converter includes an electromagnetic interference filter to reduce common mode voltage reaching the electric machine.

IPC Classes  ?

• H02K 11/40 - Structural association with grounding devices
• H02K 11/21 - Devices for sensing speed or position, or actuated thereby
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 11/02 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for suppression of electromagnetic interference
• H02K 24/00 - Machines adapted for the instantaneous transmission or reception of the angular displacement of rotating parts, e.g. synchro, selsyn
• H03H 1/00 - Constructional details of impedance networks whose electrical mode of operation is not specified or applicable to more than one type of network

Abstract

A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 21/14 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• F02C 7/275 - Mechanical drives

Abstract

A method of removing heat from an electrical machine located in a gas turbine engine at least partially inward of a core airflow path in a radial direction, the electrical machine comprising an outer electrical machine stator and an inner electrical machine rotor is provided. The method includes directing a liquid coolant radially inward past the outer electrical machine stator and toward an inner electrical machine rotor using a coolant passageway. The liquid coolant is directed onto and/or through one or both of the inner electrical machine rotor and a rotor support thereby removing heat from the inner electrical machine rotor.

IPC Classes  ?

• F01D 25/12 - Cooling
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/24 - Heat or noise insulation
• H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil

Abstract

An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F01D 25/12 - Cooling
• F01D 25/18 - Lubricating arrangements

Abstract

A method of removing heat from an electrical machine located in a gas turbine engine at least partially inward of a core airflow path in a radial direction, the electrical machine including an outer generator stator and an inner generator rotor is provided. The method includes directing cooling airflow radially through an airflow passageway to an enclosure at least partially defined by a thermal shield at least partially around the electrical machine. The cooling airflow is directed radially inward past the outer generator stator and toward the inner generator rotor using a cooling manifold thereby removing heat from the generator rotor.

IPC Classes  ?

• H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
• H02K 1/278 - Surface mounted magnetsInset magnets
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
• H02K 1/32 - Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use

Abstract

An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.

IPC Classes  ?

• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 1/12 - Stationary parts of the magnetic circuit
• H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
• H02K 7/08 - Structural association with bearings
• H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans

Abstract

The present invention relates to a trailing edge panel configured to be attached to a trailing edge of a wind turbine blade. The trailing edge panel comprises a a base element and a number of protruding aerodynamic elements. The base element having an attachment part configured to be attached to and extend from the trailing edge of the wind turbine blade and to an upstream position on a first blade side of the wind turbine blade. The base element further having a serrated part extending from the second side of the attachment part and configured to project out from the trailing edge of the wind turbine blade, wherein the serrated part comprises a number of serrations, including a first serration and a second serration. The number of protruding aerodynamic elements, including a first protruding aerodynamic element, comprising a first protruding part attached to the serrated part of the base element; and a second protruding part extending from the first protruding part towards the attachment part at an inclined angle relative to the base element and being configured to be attached to and extend along a second blade side of the wind turbine blade.

IPC Classes  ?

• F03D 1/06 - Rotors

Abstract

A generator assembly includes a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly including: a stator support structure fixedly attached to the engine stator component; a stator disposed on a supporting surface of the stator support; a manifold coupled to the stator support, the manifold defining a connection volume and including at least one coolant opening at a connection end of the manifold; and an electrical connector extending between the stator and a connection device disposed on the connection end. The generator assembly also includes a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• F01D 25/12 - Cooling
• F02C 7/12 - Cooling of plants
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

In a method for handling tower sections for a tower, in particular a wind power plant, wherein the finished tower sections are at least stored, transported and sequentially set up at least partially one on top of another, the tower sections are each already equipped on their ends with a handling device during or after their completion. Then the finished tower sections are coupled to the load-bearing equipment of transport means using the handling devices with unchanged linkage thereof on the tower section and then the tower sections are brought in the horizontal position to the location of their erection; the tower sections transported to the erection location are then brought to a vertical position by means of the handling devices with unchanged linkage thereof on the tower section by means of at least one lifting device.

IPC Classes  ?

• F03D 1/00 - Wind motors with rotation axis substantially parallel to the air flow entering the rotor

Abstract

A device (186) includes a first thyristor element (188) configured to be coupled to a first voltage line (114) and a second voltage line (116), wherein the first voltage line is configured to transmit power in a first phase and the second voltage line is configured to transmit power in a second phase. The device includes a second thyristor element (190) configured to be coupled to the second voltage line and a third voltage line (118), wherein the third voltage line is configured to transmit power in a third phase. The device includes a third thyristor element (192) configured to be coupled to the first voltage line and the third voltage line.

IPC Classes  ?

• H02H 3/00 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection
• H02H 7/10 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for convertersEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for rectifiers
• H02H 9/04 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess voltage
• H02M 7/42 - Conversion of DC power input into AC power output without possibility of reversal

Goods & Services

(1) Computed radiography phosphor scanners not for medical use; industrial x-ray testing equipment for determining industrial flaws.

Goods & Services

Computed radiography phosphor scanners not for medical use; industrial X-ray apparatus in the nature of testing equipment for determining industrial flaws.

Goods & Services

Computed radiography phosphor scanners not for medical use; industrial X-ray apparatus in the nature of testing equipment for determining industrial flaws

Goods & Services

Appareils et instruments électriques et électroniques non compris dans d'autres classes; appareils et instruments pour mesurer, signaler, indiquer, contrôler, étalonner, réguler, simuler, convertir des signaux et stimuler la pression, la température, l'accélération, le courant, le niveau, la charge et/ou la force; appareils pour la mesure électronique de la pression d'un fluide, ainsi que pour la conversion de la pression mesurée en un signal électrique et pour la transmission de ce signal; appareils d'étalonnage, de contrôle et d'indication; appareils pour l'analyse des données d'air; logiciels pour créer, maintenir et/ou contrôler des bases de données en rapport avec les produits précités; programmes d'ordinateur enregistrés pour la création, l'entretien et/ou le contrôle d'instruments. Installation, réparation et entretien d'appareils et d'instruments électriques et électroniques; installation, réparation, réglage et entretien d'appareils et instruments pour mesurer, signaler, indiquer, contrôler, étalonner, réguler, simuler, convertir des signaux et stimuler la pression, la température, l'accélération, le courant, le niveau, la charge et/ou la force; installation, réparation, réglage et entretien d'appareils et d'instruments pour la transduction, la transmission, l'étalonnage, le contrôle, l'indication et/ou pour l'analyse des données d'air; installation, réparation et entretien d'ordinateurs.

Goods & Services

Amplificateurs de détection comme instruments de mesure de précision pour mesurer électroniquement des distances et vibrations, applicables en matière de mesurage de la torsion, de l'expansion, du diamètre, de la pression et du déplacement.