公开(公告)号：US20180009009A1

公开(公告)日：2018-01-11

申请号：US15676786

申请日：2017-08-14

Applicant: Lockheed Martin Corporation

Inventor： William Schneider ,  Yvette Wood ,  Andrew Peduchi

IPC: B08B7/02 ,  F01D25/02 ,  B64D15/16 ,  F24F11/00 ,  F02C7/055 ,  F02C7/04 ,  B64D33/02

CPC classification number: B08B7/02 ,  B64D15/16 ,  B64D2033/0233 ,  F01D25/02 ,  F02C7/04 ,  F02C7/055 ,  F05D2260/96 ,  F05D2270/62 ,  F24F11/30 ,  F24F11/41 ,  Y02T50/672

Abstract: In one embodiment, a system includes an inlet grid configured to reduce distortion of an incoming airflow. The system may also include a vibration device coupled to the inlet grid and a controller communicatively coupled to the vibration device. The controller may transmit a vibration signal to the vibration device causing the vibration device to vibrate the inlet grid such that the inlet grid resonates at a natural frequency inducing a mode shape in the inlet grid. The mode shape may break up and prevent ice on the inlet grid.

公开(公告)号：US09816390B2

公开(公告)日：2017-11-14

申请号：US14789218

申请日：2015-07-01

Applicant: Hamilton Sundstrand Corporation

Inventor： Keith Bloxham ,  Derick S. Balsiger

IPC: F01D17/14 ,  F01D17/02 ,  F01D17/16 ,  F01D17/20 ,  F02C7/20 ,  F01D9/02 ,  F01D15/12

CPC classification number: F01D17/14 ,  F01D9/02 ,  F01D15/12 ,  F01D17/02 ,  F01D17/162 ,  F01D17/20 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/128 ,  F05D2240/60 ,  F05D2250/90 ,  F05D2260/40 ,  F05D2270/62

Abstract: An electric actuator for control of an engine includes an electric motor coupled to a drive shaft that extends to align a gear interface of the electric actuator with a variable geometry adjustment interface of the engine. A position feedback shaft extends coaxially with respect to the drive shaft. The position feedback shaft is coupled to an output shaft of the gear interface at a gear interface end of the position feedback shaft. A rotational position sensor is coupled to a motor end of the position feedback shaft proximate the electric motor. The drive shaft and the position feedback shaft are sized to position an output ring gear of the output shaft in contact with the variable geometry adjustment interface within a casing of the engine and to further position the electric motor and the rotational position sensor external to the casing of the engine.

公开(公告)号：US09803585B1

公开(公告)日：2017-10-31

申请号：US15387482

申请日：2016-12-21

Applicant: Geoffrey P. Pinto

Inventor： Geoffrey P. Pinto

IPC: F02K1/12 ,  F02K1/72 ,  F02K1/76 ,  F02K1/06 ,  F02K1/70 ,  F02K1/15 ,  F01D25/24 ,  F02K1/44 ,  F04D27/00 ,  F04D29/54

CPC classification number: F02K1/1261 ,  F01D25/24 ,  F02K1/06 ,  F02K1/12 ,  F02K1/15 ,  F02K1/44 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F04D27/009 ,  F04D29/545 ,  F05D2220/323 ,  F05D2260/4023 ,  F05D2260/4031 ,  F05D2260/57 ,  F05D2270/62 ,  Y02T50/671

Abstract: An aircraft engine variable area fan nozzle structure disposed abaft a thrust reverser, including a sleeve translatable over a cascade array, comprises two semi cylindrical segments that can be axially translated and radially tilted to enlarge the fan duct exhaust area in order to optimize exhaust pressure and associated noise in high thrust circumstances such as on take-off, and to constrict that area under lower thrust conditions such as cruise. The segments are moved by actuators anchored to the fixed engine framework and independently of the thrust reverser translating sleeve. Each actuator incorporates a linear variable differential transformer acting as a fan nozzle position sensor. The tilting movement is imposed by the pivoting links of each segment to carriages that ride in a non-linear trackway secured to a thrust reverser translating sleeve slider. In an alternate embodiment of the invention, the thrust reverser sleeve actuator and the variable area fan nozzle actuator are coaxially mounted in a compact assembly anchored to stationary components of the nacelle.

公开(公告)号：US20170306853A1

公开(公告)日：2017-10-26

申请号：US15137640

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Kurt J. Sobanski

IPC: F02C7/32 ,  F02K3/06 ,  F02C3/04 ,  F02C9/00

CPC classification number: F02C7/32 ,  F02C3/04 ,  F02C7/25 ,  F02C9/00 ,  F02K3/06 ,  F05D2260/57 ,  F05D2260/96 ,  F05D2270/62

Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component in communication with the mechanical component separated from the mechanical component by a firewall, the firewall comprising a first side and a second side, the second side having a lower operating temperature than the first side. A vibration isolation structure is located at the second side. The electronic module is connected thereto and includes at least one vibration isolator secured to the firewall to vibrationally isolate the electronic module from gas turbine engine vibrations.

公开(公告)号：US20170218791A1

公开(公告)日：2017-08-03

申请号：US15326999

申请日：2015-07-16

Applicant: Safran Aircraft Engines

Inventor： Irène BUJON

IPC: F01D21/14 ,  F01D21/20

CPC classification number: F01D21/14 ,  F01D21/20 ,  F02C7/232 ,  F02C9/26 ,  F02C9/46 ,  F05D2270/62

Abstract: There is proposed a method for controlling a bistable shutoff vale for an aircraft engine, involving the steps of: emitting a closure signal on one of the control channels—emitting an open signal on the other control channel, the method being characterized in that—the amplitude of the close signal is designed to cause the vane to move into a first position constantly in a given period of time,—in the same period, the amplitude of the open signal fluctuates between a value designed to urge the valve toward a second position and a rest value, the actuating values of the two signals being adapted to one another in order to keep the vane immobile when the two signals received by the valve simultaneously adopt said actuation values.

公开(公告)号：US09719365B2

公开(公告)日：2017-08-01

申请号：US14031695

申请日：2013-09-19

Applicant: ROLLS-ROYCE PLC

Inventor： Marko Bacic ,  Timothy John Scanlon ,  Ronald William Daniel

IPC: F01D11/10 ,  F01D11/24 ,  F01D11/06 ,  F01D11/20

CPC classification number: F01D11/10 ,  F01D11/06 ,  F01D11/20 ,  F01D11/24 ,  F05D2260/16 ,  F05D2270/172 ,  F05D2270/62

Abstract: A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

公开(公告)号：US09601970B2

公开(公告)日：2017-03-21

申请号：US14135567

申请日：2013-12-19

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Mat French ,  John T. Alt ,  Mark J. Blackwelder

IPC: H02K7/18 ,  F02C7/32 ,  F01D15/10 ,  F02C7/36 ,  F02C9/00 ,  H02J9/06 ,  F02C7/268 ,  B81B7/02 ,  B81C1/00 ,  H02P101/30 ,  H02P101/25

CPC classification number: H02P9/48 ,  B81B7/02 ,  B81B2201/0257 ,  B81B2201/0264 ,  B81C1/00158 ,  B81C1/00301 ,  F01D15/10 ,  F02C7/268 ,  F02C7/32 ,  F02C7/36 ,  F02C9/00 ,  F02K3/06 ,  F02N11/0862 ,  F05B2220/706 ,  F05D2220/76 ,  F05D2270/62 ,  H02J1/102 ,  H02J1/16 ,  H02J3/30 ,  H02J3/32 ,  H02J3/38 ,  H02J9/061 ,  H02K7/1823 ,  H02P2101/25 ,  H02P2101/30

Abstract: A gas turbine engine includes an electrical system that includes a controller coupled to a first inverter/converter controller, a second inverter/converter controller, and a converter/controller that is coupled to an energy storage device. The system is configured to provide electrical power to a first electrical bus and a second electrical bus, from first and second electrical machines, under the direction of the controller. The converter controller is configured to control the amount of electrical power supplied to the first electrical bus and the second electrical bus from the energy storage system. The amount of electrical power received from the first electrical bus and the second electrical bus, and energy supplied to the energy storage system are under the direction of the controller.

公开(公告)号：US09587584B2

公开(公告)日：2017-03-07

申请号：US14578110

申请日：2014-12-19

Applicant: AIRCELLE

Inventor： Hakim Maalioune ,  Alain Nourrisson

IPC: H02P7/06 ,  F02K1/76 ,  B64D41/00 ,  B64D33/04

CPC classification number: F02K1/763 ,  B64D33/04 ,  B64D41/00 ,  B64D2221/00 ,  F02K1/76 ,  F05D2260/901 ,  F05D2270/62 ,  H02P7/06 ,  Y02T50/44 ,  Y02T50/671

Abstract: A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

Abstract translation: 用于飞行器的推力反向装置包括至少两个推力反向器，并且它们中的每一个包括由由电动机驱动的致动器可移动地致动的可动外罩。 电动机由单个功率转换模块供电，所述单个功率转换模块包括至少一个自耦变压器，该自耦变压器被提供有交流电压并且连接到将交流电压转换为直流电压的至少一个整流器级。 整流器级连接到电流平衡级和电流平滑级，向可动罩的电致动器的电动机提供直流电压。

公开(公告)号：US20160347440A1

公开(公告)日：2016-12-01

申请号：US15114628

申请日：2015-01-22

Applicant: SNECMA

Inventor： Laurence Francine Vion ,  Rasika Fernando ,  Norman Bruno André Jodet

IPC: B64C11/18 ,  B64C11/48 ,  B64D27/10

CPC classification number: B64C11/18 ,  B64C11/48 ,  B64D27/10 ,  B64D2027/005 ,  F01D5/145 ,  F01D5/148 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/96 ,  F05D2260/961 ,  F05D2270/62 ,  F05D2270/64 ,  F05D2270/65 ,  Y02T50/66 ,  Y02T50/673

Abstract: A blade for a turbine engine propeller, in particular a propfan engine, comprising a protruding part on the leading edge thereof, wherein said blade comprises means for controlling the position of the protruding part along the leading edge thereof.

Abstract translation: 一种用于涡轮发动机螺旋桨，特别是普罗芬发动机的叶片，其包括在其前缘上的突出部分，其中所述叶片包括用于控制突出部分沿其前缘的位置的装置。

公开(公告)号：US20160265445A1

公开(公告)日：2016-09-15

申请号：US14644796

申请日：2015-03-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Janusz FIEDLER ,  Tatjana PEKOVIC ,  Dave SELLORS ,  Amandeep Singh CHAHAL

IPC: F02C9/44

CPC classification number: F02C9/44 ,  B64D31/10 ,  F01D21/00 ,  F01D21/02 ,  F02C9/263 ,  F02C9/28 ,  F02C9/46 ,  F05D2270/021 ,  F05D2270/051 ,  F05D2270/62 ,  G05B9/03

Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.

Abstract translation: 一种飞机发动机的推力保护系统。 该系统包括发动机超速保护单元，其包括超速逻辑和由超速逻辑控制的超速电磁阀，所述超速逻辑被配置为对超速电磁阀通电，以在检测到飞机发动机的超速状况时去除发动机的燃料流; 以及超控制器控制器，其耦合到所述超速保护单元并且被配置成测量发动机推力并且当已经超过发动机推力阈值时检测到推力状态，并且被配置为在检测到所述推力状态时触发所述超速电磁阀的通电， - 地面条件。