Secondary systems and methods of control for variable area fan nozzles

A control system for a variable area fan nozzle (VAFN) is disclosed. The VAFN may have a plurality of petals and may be for use with a gas turbine engine. The control system may include a primary system configured to acquire primary data indicative of an operating condition of the VAFN, a secondary system configured to acquire secondary data indicative of a current operating condition of the gas turbine engine, and a control module in operative communication with the primary system and the secondary system. The control module may be configured to: determine a nozzle area of the VAFN based at least in part on the primary data, adjust the determined nozzle area based on the secondary data, and position the plurality of petals according to the adjusted nozzle area.

Thrust Reverser Apparatus and Method

A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream. 1. A thrust reverser configured to be positioned in a turbofan engine nacelle extending around an engine core cowl , the nacelle defining an axially extending bypass duct about the engine core cowl for receiving a fan bypass air stream , the thrust reverser comprising:a translating sleeve movably coupled to a fixed portion of the nacelle; anda blocker door pivotally coupled to the translating sleeve such that movement of the translating sleeve in an axially rearward direction causes the blocker door to move aft while remaining in an axial orientation, and wherein an outer wall of the bypass duct is radially interposed between the blocker door and a fan bypass air stream when the blocker door is in a stowed position.2. The thrust reverser of claim 1 , wherein a first end of the blocker door is coupled to the translating sleeve at a first pivot joint claim 1 , the blocker door configured to pivot about the first pivot joint radially inward to a deployed position in which the blocker door is disposed at least partially in the fan bypass ...

AIRCRAFT BLEED AIR AND ENGINE STARTER SYSTEMS AND RELATED METHODS

Example bleed air and engine starter systems are described herein that employ a shaft-driven compressor to start an aircraft engine and/or to supply pressurized air to one or more systems of an aircraft. An example compressor includes a housing and an impeller disposed within a cavity of the housing. The impeller is operatively coupled to a drive shaft. The compressor includes a first port in the housing to direct onto the impeller to rotate the impeller when the compressor is operating in a first mode. In the first mode, the impeller is to drive the drive shaft. The compressor also includes a second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode. In the second mode, the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air. 1. A compressor comprising:a housing;an impeller disposed within a cavity of the housing, the impeller operatively coupled to a drive shaft;a first port in the housing to direct air onto the impeller to rotate the impeller when the compressor is operating in a first mode, wherein in the first mode the impeller is to drive the drive shaft; anda second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode, wherein in the second mode the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air.2. The compressor of claim 1 , wherein the impeller has a first end and a second end opposite the first end claim 1 , the first port positioned to direct air onto the impeller in a location between the first end and the second end of the impeller.3. The compressor of claim 2 , wherein the second port is positioned adjacent the first end of the impeller.4. The compressor of claim 1 , wherein the first port includes a plurality of nozzles disposed around the cavity and oriented to direct air onto the impeller.5. The compressor of further ...

Bleed air systems for use with aircraft and related methods

Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.

COMPRESSION MOLDING ASSEMBLY AND METHODS FOR MOLDING A THERMOPLASTIC BLOCKER DOOR

A compression molding assembly for molding a honeycomb core, including a plurality of cells defined by a plurality of walls, of a blocker door is provided. The compression molding assembly includes a ram plate comprising a plurality of openings defined therethrough and a plurality of core inserts coupled to the ram plate such that the plurality of core inserts are configured to form the honeycomb core of the blocker door. Each core insert is removably coupled with a respective opening of the plurality of openings such that each core insert is configured to form a respective cell of the plurality of cells. 1. A compression molding assembly for molding a honeycomb core of a blocker door , wherein the honeycomb core comprises a plurality of cells defined by a plurality of walls , said compression molding assembly comprising:a ram plate comprising a plurality of openings defined therethrough; anda plurality of core inserts coupled to said ram plate and configured to form the honeycomb core of the blocker door, wherein each said core insert is removably coupled with a respective opening of said plurality of openings such that each core insert is configured to form a respective cell of the plurality of cells.2. The compression molding assembly according to claim 1 , wherein said plurality of core inserts comprises a plurality of sets of core inserts claim 1 , wherein each set of core inserts is a different size than every other set of core inserts.3. The compression molding assembly according to claim 1 , wherein said plurality of core inserts comprises a first set of core inserts and a second set of core inserts claim 1 , wherein said first set of core inserts comprises a first size and said second set of core inserts comprises a second size different than the first size.4. The compression molding assembly according to claim 1 , wherein a gap is defined between adjacent core inserts of said plurality of core inserts claim 1 , wherein the gap defines a thickness of a cell ...

BLEED AIR SYSTEMS FOR USE WITH AIRCRAFT AND RELATED METHODS

Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox. 1. A bleed air system for an aircraft , the bleed air system comprising:a turbo-compressor including a compressor, a turbine, and a first drive shaft coupled between the compressor and the turbine, the compressor having a compressor inlet to receive bleed air from an engine of the aircraft and a compressor outlet to be fluidly coupled to a system of the aircraft that receives pressurized air;a gearbox operatively coupled to and powered by a second drive shaft extending from the engine; anda freewheel disposed between the first drive shaft and the gearbox to operatively couple the first drive shaft and the gearbox.2. The bleed air system of claim 1 , wherein claim 1 , during a first operating condition of the aircraft claim 1 , the freewheel is to operatively couple the first drive shaft to the gearbox such that the gearbox drives the first drive shaft to drive the compressor and claim 1 , during a second operating condition of the aircraft claim 1 , the freewheel is to enable the first drive shaft to rotate faster than an output of the gearbox.3. The bleed air system of claim 2 , wherein claim 2 , during the second operating condition of the aircraft claim 2 , the turbine is to drive the ...

BLOCKER DOOR ASSEMBLY HAVING A THERMOPLASTIC BLOCKER DOOR FOR USE IN A TURBINE ENGINE

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material. 1. A blocker door assembly for use in a gas turbine engine , said blocker door assembly comprising:a facesheet, wherein said facesheet comprises a plurality of openings to facilitate noise attenuation; anda body portion coupled to said facesheet, wherein said body portion comprises a backsheet integrally formed with a honeycomb core, wherein said body portion is molded from a thermoplastic material.2. The blocker door assembly according to claim 1 , wherein said body portion comprises a plurality of mounting structures integrally formed with said backsheet and said honeycomb core.3. The blocker door assembly according to claim 1 , wherein said facesheet is formed from the thermoplastic material.4. The blocker door assembly according to claim 1 ,wherein said honeycomb core comprises a plurality of cells comprising a plurality of walls claim 1 , and wherein said plurality of cells comprises a plurality of sets of cells claim 1 , wherein each set of cells comprises a wall thickness that is different than a wall thickness of every other set of cells.5. The blocker door assembly according to claim 1 , wherein said facesheet is coupled to said body portion by at least one of thermal bonding claim 1 , adhesive bonding claim 1 , and a plurality of mechanical fasteners.6. The blocker door assembly according to claim 1 , wherein said body portion comprises a first portion and a second portion claim 1 , wherein said blocker door assembly further comprises an intermediate sheet coupled between said first and said second portions.7. The blocker door assembly according to claim 6 , wherein said intermediate sheet is formed from the thermoplastic ...

Advanced inlet design

A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.

DUAL DOOR FAN AIR MODULATING VALVE

A fan air modulating valve (FAMV) employs a pair of doors rotatably attached at the fan bypass air exit of a precooler. An actuator engages the doors for simultaneous rotation through a range of motion from a first closed position to a second open position, wherein trailing edges of said doors sealingly engage an exit plenum extending from the precooler in the first closed position and fan bypass air flow is modulated by positioning the doors within the range of motion between the first and second positions. 1. A fan air modulating valve (FAMV) comprising:at least one pair of doors rotatably attached at an air exit of a fan bypass air cooled device; and,an actuator engaging the doors for simultaneous rotation from a closed position to an open position, wherein said doors sealingly engage an exit plenum extending from the precooler.2. The FAMV as defined in further comprising a hinge rod received within a leading edge of each of the doors to support rotation of the door.3. The FAMV as defined in wherein rotation of the doors from the closed position to the open position is controllable through a range of motion by the actuator for modulation of fan bypass air.4. The FAMV as defined in wherein the actuator incorporates a push rod extendible from a first position corresponding to the closed position to a second position corresponding to the open position and the FAMV further comprises tie rods connected at a single hinge point on the push rod and extending to a hinge joint on the doors.5. The FAMV as defined in wherein the doors have an airfoil shape and the hinge joint on each door is located at about mid chord.6. The FAMV as defined in wherein the doors have an airfoil shape.7. The FAMV as defined in wherein the doors incorporate an airfoil shape and further comprising:an aerodynamic centerbody located between leading edges of the doors;a hinge rod received within each of the doors for rotation of the doors, a first inboard flow path between the first one of the ...

Bleed air systems for use with aircrafts and related methods

Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor of the aircraft engine. The compressor inlet to receive fluid from either the low-pressure compressor or the high-pressure compressor based on a first system parameter of the aircraft. A turbine has a turbine inlet fluidly coupled to the intermediate port of the high pressure compressor and a high-pressure port of the high pressure compressor of the aircraft engine. The turbine inlet to receive fluid from either the intermediate port of the high-pressure compressor or the high-pressure port of the high-pressure compressor based on a second system parameter of the aircraft.

Bleed air systems for use with aircraft and related methods

Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet and a compressor outlet. The compressor is to be driven by a drive shaft extending from an engine of an aircraft. The example apparatus also includes a first passageway to fluidly couple a first low-pressure bleed air port from the engine to the compressor inlet and a second passageway to fluidly couple the compressor outlet to a system of the aircraft.

Bleed air systems for use with aircraft and related methods

Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.

Thermal management systems incorporating shape memory alloy actuators and related methods

Thermal management systems incorporating shape memory alloy (SMA) actuators and related methods. A thermal management system includes a heat transfer region, a process fluid conduit, a thermal management fluid conduit, and an SMA actuator assembly. The SMA actuator assembly includes an SMA element coupled to an actuation element, which is configured to assume a position among a plurality of positions defined between a restrictive position and an open position. The position of the actuation element is based, at least in part, on a conformation of the SMA element. A method of passively regulating a temperature of a process fluid includes conveying a process fluid stream in heat exchange relation with an SMA element, transitioning the SMA element to assume a conformation, flowing each of the process fluid stream and a thermal management fluid stream through a heat transfer region, and modulating a flow rate of the thermal management fluid stream.

BLOCKER DOOR ASSEMBLY HAVING A THERMOPLASTIC BLOCKER DOOR FOR USE IN A TURBINE ENGINE

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

Systems and Methods for Transferring Mechanical Power in a Turbine Engine

A system (166) for transferring mechanical power in a turbine engine (150/151) including a low pressure spool (162) and a high pressure spool (156) includes a power transfer unit (168) coupled between an output shaft (172) of the low pressure spool (162) and a drive shaft (174) of the high pressure spool (156) to mechanically link the low pressure spool (162) to the high pressure spool (156), and a clutch (170) coupled to the power transfer unit (168), wherein the clutch (170) is configured to transfer power produced from the low pressure spool (162) to the high pressure spool (156).

Thermal management systems

A thermal management system includes a heat exchanger and a housing that receives the heat exchanger. The heat exchanger defines a heat transfer region within which thermal exchange occurs between a process fluid and a thermal management fluid. The thermal management system further includes a process fluid conduit to convey the process fluid through the heat transfer region and an actuator assembly configured to position the heat exchanger relative to the housing. The actuator assembly is configured to selectively assume a position between a stowed position and a deployed position. When the actuator assembly is in the deployed position, the heat transfer region extends within a flow of the thermal management fluid such that the process fluid flow flows in heat exchange relation with the thermal management fluid flow. In some such embodiments, the actuator assembly automatically transitions between the stowed position and the deployed position.

SHAPE MEMORY ALLOY LIFTING TUBES AND SHAPE MEMORY ALLOY ACTUATORS INCLUDING THE SAME

A shape memory alloy (SMA) actuator includes an SMA lifting tube that extends between a first end and a second end and that is configured to be in thermal communication with a process fluid during operative use of the SMA actuator. The SMA actuator is configured to assume a conformation among a plurality of conformations defined between and including a first conformation and a second conformation based, at least in part, on the temperature of the process fluid that is in thermal communication with the SMA lifting tube. The SMA lifting tube is configured such that the second end translates relative to the first end at least partially along a lateral direction that is at least substantially perpendicular to at least a portion of the SMA lifting tube between the first end and the second end as the SMA actuator transitions between the first conformation and the second conformation. 1. A shape memory alloy (SMA) actuator , comprising:an SMA lifting tube that includes and extends between a first end and a second end and that is configured to be in thermal communication with a process fluid during operative use of the SMA actuator;wherein the SMA actuator is configured to assume a conformation among a plurality of conformations defined between and including a first conformation and a second conformation; wherein the conformation of the SMA actuator is based, at least in part, on the temperature of the process fluid that is in thermal communication with the SMA lifting tube during operative use of the SMA actuator; and wherein the SMA lifting tube is configured such that the second end translates relative to the first end at least partially along a lateral direction that is at least substantially perpendicular to at least a portion of the SMA lifting tube between the first end and the second end as the SMA actuator transitions between the first conformation and the second conformation.2. The SMA actuator of claim 1 , wherein the first end and the second end are at least ...

SECONDARY SYSTEMS AND CONTROL METHODS FOR VARIABLE AREA FAN JUMPS

a presente invenção refere-se a um sistema de controle para um bocal de ventoinha de área variável (vafn). o vafn tem uma pluralidade de pétalas e pode ser para utilização com um motor de turbina a gás. o sistema de controle pode incluir um sistema primário configurado para adquirir dados primários indicativos de uma condição de funcionamento do vafn, um sistema secundário configurado para adquirir dados secundários indicativos de uma condição de funcionamento atual do motor de turbina a gás, e um módulo de controle em comunicação operativa com o sistema primário e o sistema secundário. o módulo de controle pode ser configurado para: determinar uma área de bocal do vafn com base, pelo menos em parte, nos dados primários, ajustar a área de bocal determinada com base nos dados secundários, e posicionar a pluralidade de pétalas de acordo com a área de bocal ajustada. The present invention relates to a control system for a variable area fan (vafn) nozzle. The vafn has a plurality of petals and may be for use with a gas turbine engine. the control system may include a primary system configured to acquire primary data indicative of a vafn operating condition, a secondary system configured to acquire secondary data indicative of a current gas turbine engine operating condition, and a control module. in operative communication with the primary system and the secondary system. the control module can be configured to: determine a vafn nozzle area based at least in part on the primary data, adjust the determined nozzle area based on secondary data, and position the plurality of petals according to adjusted nozzle area.

Shape memory alloy lifting tubes and shape memory alloy actuators including the same

A shape memory alloy (SMA) actuator includes an SMA lifting tube that extends between a first end and a second end and that is configured to be in thermal communication with a process fluid during operative use of the SMA actuator. The SMA actuator is configured to assume a conformation among a plurality of conformations defined between and including a first conformation and a second conformation based, at least in part, on the temperature of the process fluid that is in thermal communication with the SMA lifting tube. The SMA lifting tube is configured such that the second end translates relative to the first end at least partially along a lateral direction that is at least substantially perpendicular to at least a portion of the SMA lifting tube between the first end and the second end as the SMA actuator transitions between the first conformation and the second conformation.

Dual door fan air modulating valve

A fan air modulating valve (FAMV) employs a pair of doors rotatably attached at the fan bypass air exit of a precooler. An actuator engages the doors for simultaneous rotation through a range of motion from a first closed position to a second open position, wherein trailing edges of said doors sealingly engage an exit plenum extending from the precooler in the first closed position and fan bypass air flow is modulated by positioning the doors within the range of motion between the first and second positions.

Compression molding assembly and methods for molding a thermoplastic blocker door

Thrust reverser apparatus and method

A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.

Compression molding assembly and methods for molding a thermoplastic blocker door

A compression molding assembly for molding a honeycomb core, including a plurality of cells defined by a plurality of walls, of a blocker door is provided. The compression molding assembly includes a ram plate comprising a plurality of openings defined therethrough and a plurality of core inserts coupled to the ram plate such that the plurality of core inserts are configured to form the honeycomb core of the blocker door. Each core insert is removably coupled with a respective opening of the plurality of openings such that each core insert is configured to form a respective cell of the plurality of cells.

Bleed air systems for use with aircrafts and related methods

Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor of the aircraft engine. The compressor inlet to receive fluid from either the low-pressure compressor or the high- pressure compressor based on a first system parameter of the aircraft. A turbine has a turbine inlet fluidly coupled to the intermediate port of the high pressure compressor and a high-pressure port of the high pressure compressor of the aircraft engine. The turbine inlet to receive fluid from either the intermediate port of the high-pressure compressor or the high-pressure port of the high-pressure compressor based on a second system parameter of the aircraft.

Bleed air systems for use with aircrafts and related methods

Bleed air systems for use with aircrafts and related methods are disclosed. An apparatus comprising: a turbo-compressor including: a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft; and a turbine having a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft, wherein the turbo- compressor is to increase a pressure of bleed air received from the low-pressure compressor, and wherein the high-pressure compressor has a higher pressure than the low-pressure compressor.

Advanced inlet design

A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.

Dual door fan air modulating valve

A fan air modulating valve (FAMV) employs a pair of doors rotatably attached at the fan bypass air exit of a precooler. An actuator engages the doors for simultaneous rotation through a range of motion from a first closed position to a second open position, wherein trailing edges of said doors sealingly engage an exit plenum extending from the precooler in the first closed position and fan bypass air flow is modulated by positioning the doors within the range of motion between the first and second positions.

Formed structural assembly and associated preform

A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.

Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers

Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers. The sound-attenuating heat exchangers include a base region, which defines a first base side and a second base side, and a plurality of elongate fluid conduits, which are at least partially defined by the base region and configured to contain a cooled fluid stream. The sound-attenuating heat exchangers also include a plurality of heat transfer-enhancing structures, which extend from the first base side and are configured to exchange thermal energy with a cooling fluid stream, and a sound-attenuating region, which extends from the second base side. The sound-attenuating region includes a plurality of resonator cells configured to attenuate sound and a plurality of resonator cell openings. Each resonator cell opening opens from a corresponding resonator cell toward the plurality of heat transfer-enhancing structures. The methods include methods of operating the sound-attenuating heat exchanger.

Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers

Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers. The sound-attenuating heat exchangers include a base region, which defines a first base side and a second base side, and a plurality of elongate fluid conduits, which are at least partially defined by the base region and configured to contain a cooled fluid stream. The sound-attenuating heat exchangers also include a plurality of heat transfer-enhancing structures, which extend from the first base side and are configured to exchange thermal energy with a cooling fluid stream, and a sound-attenuating region, which extends from the second base side. The sound-attenuating region includes a plurality of resonator cells configured to attenuate sound and a plurality of resonator cell openings. Each resonator cell opening opens from a corresponding resonator cell toward the plurality of heat transfer-enhancing structures. The methods include methods of operating the sound-attenuating heat exchanger.

Entrada para um motor turbofan, conjunto, e, método para operar um motor turbofan

entrada para um motor turbofan, conjunto, e, método para operar um motor turbofan. um desenho de entrada compacto incluindo um único anteparo e/ou um painel acústico que se estende ao interior da região do lábio da entrada de ar da nacele para redução de ruído. a entrada compacta é usada com um sistema de proteção contra gelo com fluido de baixa potência capaz de impedir a formação de gelo no painel acústico na região do lábio da entrada de ar da nacele.

Advanced inlet design

A cornpact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection systern capable of preventing ice build-up on the acoustic panel in the nacelle lip region.

Advanced inlet design

A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.

Blocker door assembly having a thermoplastic blocker door for use in a turbine engine

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

Advanced inlet design

Advanced inlet design

A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction.

Formed structural assembly and associated preform and method

A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.

Formed structural assembly and associated preform

A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.

Thermal management systems incorporating shape memory alloy actuators and related methods

Thermal management systems incorporating shape memory alloy (SMA) actuators and related methods. A thermal management system includes a heat transfer region, a process fluid conduit, a thermal management fluid conduit, and an SMA actuator assembly. The SMA actuator assembly includes an SMA element coupled to an actuation element, which is configured to assume a position among a plurality of positions defined between a restrictive position and an open position. The position of the actuation element is based, at least in part, on a conformation of the SMA element. A method of passively regulating a temperature of a process fluid includes conveying a process fluid stream in heat exchange relation with an SMA element, transitioning the SMA element to assume a conformation, flowing each of the process fluid stream and a thermal management fluid stream through a heat transfer region, and modulating a flow rate of the thermal management fluid stream.

Sistemas de gerenciamento térmico

Sistemas de gerenciamento térmico que incorporam atuadores de liga com memória de forma (SMA) e métodos relacionados. Um sistema de gerenciamento térmico inclui uma região de transferência de calor, um conduto de fluido de processo, um conduto de fluido de gerenciamento térmico e um conjunto de atuador SMA. O conjunto de atuador SMA inclui um elemento SMA acoplado a um elemento de atuação, que é configurado para assumir uma posição entre uma pluralidade de posições definidas entre uma posição restritiva e uma posição aberta. A posição do elemento de atuação é baseada, pelo menos em parte, em uma conformação do elemento SMA. Um método de regular passivamente a temperatura de um fluido de processo inclui transferir uma corrente de fluido de processo em relação de troca de calor com um elemento SMA, transicionar o elemento SMA para assumir uma conformação, escoar cada da corrente de fluido de processo e de uma corrente de fluido de gerenciamento térmico através de uma região de transferência de calor e modular uma vazão da corrente de fluido de gerenciamento térmico.

Sistemas de gestión térmica que incorporan accionadores de aleación con memoria de forma y métodos relacionados

Un sistema de gestión térmica (100) configurado para regular la temperatura de un fluido de proceso a través del intercambio térmico entre el fluido de proceso y un fluido de gestión térmica, comprendiendo el sistema de gestión térmica: una región de transferencia de calor (182) dentro de la que se produce el intercambio térmico entre el fluido de proceso y el fluido de gestión térmica; un conducto de fluido de proceso (141) configurado para transportar un flujo de fluido de proceso (112) del fluido de proceso en relación de intercambio de calor con la región de transferencia de calor (182); un conducto de fluido de gestión térmica (184) configurado para transportar un flujo de fluido de gestión térmica (114) del fluido de gestión térmica en relación de intercambio de calor con la región de transferencia de calor (182); y un conjunto de accionador de aleación con memoria de forma (SMA) (110) configurado para regular selectivamente un caudal del flujo de fluido de gestión térmica (114), incluyendo el conjunto de accionador de SMA: (i) un tubo de torsión de SMA (120) en contacto térmico con el flujo de fluido de proceso (112) y configurado para adoptar una conformación entre una pluralidad de conformaciones, en el que se basa la conformación del elemento de SMA, al menos en parte, a una temperatura del flujo de fluido de proceso; (ii) un elemento de accionamiento (160) acoplado al tubo de torsión de SMA (120), en el que el elemento de accionamiento está configurado para adoptar una posición entre una pluralidad de posiciones definidas entre una posición restrictiva, en la que el elemento de accionamiento restringe el flujo del flujo de fluido de gestión térmica (114) dentro del conducto de fluido de gestión térmica (184), y una posición abierta, en la que el elemento de accionamiento (160) permite el flujo del flujo de fluido de gestión térmica (114) dentro del conducto de fluido de gestión térmica (184), y en la que además se basa la posición del elemento de ...