公开(公告)号：US12104501B2

公开(公告)日：2024-10-01

申请号：US17944790

申请日：2022-09-14

申请人： General Electric Company

发明人： Nicholas J. Kray ,  Vidyashankar Buravalla

IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D17/08 ,  F01D17/16 ,  F02C7/04 ,  F02C7/042 ,  F02C7/057 ,  F02K3/06 ,  F04D29/54 ,  F04D29/56 ,  B64D33/02

CPC分类号： F01D5/148 ,  F01D5/18 ,  F01D17/085 ,  F01D17/162 ,  F02C7/04 ,  F02C7/042 ,  F02C7/057 ,  F02K3/06 ,  F04D29/542 ,  F04D29/563 ,  B64D2033/0226 ,  F05D2220/323 ,  F05D2250/90 ,  F05D2260/20 ,  F05D2270/303 ,  F05D2270/3032 ,  F05D2300/505

摘要： Cantilevered airfoils and methods of forming the same are disclosed herein. An example airfoil disclosed herein includes an airfoil including an airfoil body including a first face and a second face, a first recessed portion formed in the first face and internal temperature-regulating features and a first insert disposed within the first recessed portion, the first insert causing the airfoil body to assume a first predefined curvature profile at a first temperature, the first insert causing the airfoil body to assume a second predefined curvature profile at a second temperature.

公开(公告)号：US12025055B1

公开(公告)日：2024-07-02

申请号：US18158690

申请日：2023-01-24

申请人： General Electric Company

发明人： Trevor H. Wood ,  Michael J. McMahon

IPC分类号： F02C7/042 ,  F02C7/057

CPC分类号： F02C7/042 ,  F02C7/057 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/60 ,  F05D2260/96

摘要： A turboprop engine includes a main nacelle body, a rotatable hub provided on the main nacelle body, a plurality of propellers connected to the rotatable hub, and a nacelle extension coupled to the main nacelle body, the nacelle extension including at least one wall defining an air intake inlet. The air intake inlet is movable in an airflow axis with respect to a trailing edge of a propeller in the plurality of propellers to vary a distance between the air intake inlet and the trailing edge of the propeller during various phases of operation of the turboprop engine.

公开(公告)号：US11965459B2

公开(公告)日：2024-04-23

申请号：US17723012

申请日：2022-04-18

申请人： Pratt & Whitney Canada Corp.

发明人： Hien Duong ,  Jason Nichols

IPC分类号： F02C7/042 ,  F02C7/052

CPC分类号： F02C7/042 ,  F02C7/052 ,  F05D2260/607

摘要： An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.

公开(公告)号：US11952943B2

公开(公告)日：2024-04-09

申请号：US18213823

申请日：2023-06-24

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Karan Anand ,  Hong Yu

IPC分类号： F02C9/20 ,  F01D17/14 ,  F02C3/04 ,  F02C7/042 ,  F02C9/54

CPC分类号： F02C7/042 ,  F01D17/141 ,  F02C3/04 ,  F02C9/20 ,  F02C9/54

摘要： Assemblies and methods for directing a flow of air through a compressor section of a gas turbine engine are disclosed. A method includes receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, and at least partially confining and modifying a strut wake generated in the flow of air by the strut using one or more variable orientation guide vanes.

公开(公告)号：US20230349323A1

公开(公告)日：2023-11-02

申请号：US17768933

申请日：2020-10-15

申请人： INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE ,  SAFRAN AIRCRAFT ENGINES

发明人： Nicolas Jérôme Jean TANTOT ,  Xavier CARBONNEAU ,  Philippe Gérard CHANEZ ,  Nicolas GARCIA ROSA ,  Alejandro MARTIN PLEGUEZUELO ,  Nicolas Joseph SIRVIN

IPC分类号： F02C7/042 ,  B64D29/00 ,  B64D33/02

CPC分类号： F02C7/042 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286

摘要： The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.

公开(公告)号：US11702218B2

公开(公告)日：2023-07-18

申请号：US16951716

申请日：2020-11-18

申请人： Textron Innovations Inc.

发明人： Thomas Dewey Parsons

IPC分类号： B64D33/02 ,  B64C33/02 ,  F02C7/057 ,  F02C7/04 ,  F02C7/042 ,  B64C27/04

CPC分类号： B64D33/02 ,  B64C33/02 ,  F02C7/04 ,  F02C7/042 ,  F02C7/057 ,  B64C27/04 ,  B64D2033/0253 ,  F05D2220/329

摘要： The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.

公开(公告)号：US11661887B2

公开(公告)日：2023-05-30

申请号：US17319439

申请日：2021-05-13

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Michel Labrecque ,  Vincent Couture-Gagnon ,  Richard Ullyott

IPC分类号： F02C7/045 ,  F02C7/042 ,  F02K3/04 ,  F02K3/06 ,  F02K3/02 ,  F01D17/14 ,  B64D33/02 ,  F02K3/068

CPC分类号： F02C7/045 ,  F02C7/042 ,  B64D2033/0206 ,  B64D2033/0286 ,  F01D17/143 ,  F02K3/025 ,  F02K3/04 ,  F02K3/06 ,  F02K3/068 ,  F05D2250/311 ,  F05D2250/712 ,  F05D2250/90 ,  F05D2260/96

摘要： A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.

公开(公告)号：US20230147099A1

公开(公告)日：2023-05-11

申请号：US17916287

申请日：2021-03-10

申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA

发明人： Takahiro ANDO ,  Hirokazu SASAKI ,  Hidetoshi TAKEMURA ,  Nobuhiro TATEMATSU ,  Mitsuhiro KAWAKATSU ,  Ryosuke URAGUCHI ,  Kohei YUKI

IPC分类号： F02C7/042

CPC分类号： F02C7/042 ,  F05D2250/90 ,  F05D2300/6034 ,  F05D2300/44

摘要： A unison ring of a gas turbine engine includes: an annular body including fiber-reinforced resin or circular-arc bodies including the fiber-reinforced resin, the fiber-reinforced resin including resin and reinforced fibers; and pin holes in which a pin is in a radial direction orthogonal to an axial direction of the unison ring. A main orientation of the reinforced fibers of the fiber-reinforced resin is directed in a circumferential direction of the unison ring.

公开(公告)号：US20180354639A1

公开(公告)日：2018-12-13

申请号：US15992861

申请日：2018-05-30

申请人： Airbus Defence and Space GmbH

发明人： Thomas BERENS

IPC分类号： B64D33/02 ,  F02C7/042 ,  F02C7/057

CPC分类号： B64D33/02 ,  B64C23/005 ,  B64C2230/06 ,  B64D2033/0226 ,  B64D2033/026 ,  F02C7/04 ,  F02C7/042 ,  F02C7/057

摘要： A device for a variable and adaptable diverterless bump engine inlet of an aircraft comprises a flexible inlet, a mechanism to change the shape of the flexible inlet, and a processing unit to control the mechanism. The flexible inlet of the device includes a plurality of edges attached partly to a fuselage skin and partly to an engine inlet duct. With this device, the shape of the flexible inlet can be controlled according to the flight conditions, and hence the engine air intake will perform more efficient at all speeds while fulfilling requirements for less radar visibility.

公开(公告)号：US20180328284A1

公开(公告)日：2018-11-15

申请号：US16043629

申请日：2018-07-24

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Michel LABRECQUE ,  Vincent COUTURE-GAGNON ,  Richard ULLYOTT

IPC分类号： F02C7/045 ,  F02C7/052 ,  F02C7/042 ,  F01D17/08 ,  F02C7/05 ,  F01D17/10 ,  F02K3/02

CPC分类号： F02C7/045 ,  F01D17/08 ,  F01D17/105 ,  F02C7/042 ,  F02C7/05 ,  F02C7/052 ,  F02K3/025

摘要： An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor.