公开(公告)号：US20080245050A1

公开(公告)日：2008-10-09

申请号：US11143246

申请日：2005-06-02

Applicant: Gary C. Wollenweber

Inventor： Gary C. Wollenweber

IPC: F02G3/00

CPC classification number: F02C6/08 ,  F02C6/02 ,  F02C6/06 ,  F02C7/277 ,  F02C7/32 ,  F02C9/18 ,  F02C9/28 ,  F02C9/42 ,  F02C9/50 ,  F02K3/06 ,  F02K3/12 ,  F05D2220/50 ,  F05D2270/13 ,  Y10T29/4932

Abstract: A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine, coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, such that at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas and channeled to the auxiliary engine for generating power, and coupling a modulating valve in flow communication to the propelling gas turbine engine to control the flow of airflow from the propelling gas turbine engine to the auxiliary engine, wherein the modulating valve is selectively operable to control an extraction point of airflow from the propelling gas turbine engine.

Abstract translation: 一种便于组装燃气涡轮发动机组件的方法。 该方法包括提供至少一个推进式燃气涡轮发动机，其包括包括至少一个涡轮机的核心发动机，将辅助发动机联接到推进燃气涡轮发动机，使得在推进燃气涡轮发动机的运行期间，使得至少一部分 进入推进式燃气涡轮发动机的气流从推进气体中抽出并被引导到辅助发动机以产生动力，并将与流动连通的调节阀联接到推进燃气涡轮发动机，以控制来自推进燃气涡轮发动机的气流 辅助发动机，其中调节阀可选择性地操作以控制来自推进燃气涡轮发动机的气流的提取点。

公开(公告)号：US06679046B2

公开(公告)日：2004-01-20

申请号：US10173857

申请日：2002-06-19

Applicant: Satoshi Tanaka ,  Miharu Matsuoka

Inventor： Satoshi Tanaka ,  Miharu Matsuoka

IPC: F02C618

CPC classification number: F02C9/42 ,  F01D21/06 ,  F01D21/14 ,  F01K23/101 ,  F02C9/26 ,  F02C9/46 ,  F05D2220/72 ,  F05D2220/74 ,  F05D2270/13 ,  Y02E20/16

Abstract: A single-shaft combined plant having an emergency shut-off oil system is provided. The emergency shut-off oil system is constituted such that when a steam governing valve tripping electromagnetic valve is opened, only a steam turbine is stopped; a master tripping electromagnetic valve is connected to a fuel gas control valve emergency shut-off oil line, a fuel oil control valve emergency shut-off oil line, and a steam governing valve emergency shut-off oil line via check valves; and when the master tripping electromagnetic valve is opened, both the steam turbine and a gas turbine are stopped. Thus, only the steam turbine can be stopped. Even if a tripping valve provided on the fuel gas control valve emergency shut-off oil line or the fuel oil control valve emergency shut-off oil line does not open because of a breakdown, the gas turbine can be stopped reliably.

Abstract translation: 提供具有紧急切断油系统的单轴联合设备。 紧急关闭油系统构成为：当蒸汽调节阀跳闸电磁阀打开时，仅停止蒸汽轮机; 主跳闸电磁阀通过止回阀连接到燃气控制阀紧急切断油路，燃油控制阀紧急关闭油管线和蒸汽调节阀紧急切断油路; 并且当主跳闸电磁阀打开时，蒸汽轮机和燃气轮机都停止。 因此，仅能够停止汽轮机。 即使在燃料气体控制阀紧急关闭油路或燃油控制阀紧急切断油路上设置的脱扣阀由于击穿而不能打开，也能够可靠地停止燃气轮机。

公开(公告)号：US5285638A

公开(公告)日：1994-02-15

申请号：US812415

申请日：1991-12-23

Applicant: Daniel G. Russ, deceased ,  George J. Bertsche

Inventor： Daniel G. Russ, deceased ,  George J. Bertsche

IPC: F02C9/28 ,  F02K3/00

CPC classification number: F02C9/28 ,  F05D2270/051 ,  F05D2270/07 ,  F05D2270/13

Abstract: A system and method to maximize fuel efficiency for a plurality of simultaneously operating engines is disclosed. The system includes means to determine the fuel consumption of the engine, measure the thrust of each engine and means to substantially equalize the ratio of the fuel consumption to the thrust between each of the engines. A pressure transducer is included to provide thrust data supply to each of the engines to a microprocessor, and a microprocessor is run to substantially equalize the ratio of the fuel consumption to the thrust to provide an increased fuel efficient system.

Abstract translation: 公开了一种用于使多个同时操作的发动机的燃料效率最大化的系统和方法。 该系统包括用于确定发动机的燃料消耗的装置，测量每个发动机的推力和基本上均衡燃料消耗与每个发动机之间的推力的比率的装置。 包括压力传感器以向每个发动机向微处理器提供推力数据，并且运行微处理器以基本上均衡燃料消耗与推力的比率，以提供增加的燃料效率系统。

公开(公告)号：US11952138B2

公开(公告)日：2024-04-09

申请号：US18082008

申请日：2022-12-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin Drolet ,  Frederic Fortin

IPC: B64D31/00 ,  B64D27/10 ,  B64D35/08 ,  F02C6/02 ,  F02C6/18 ,  F02C9/16 ,  F02C9/20

CPC classification number: B64D31/00 ,  B64D27/10 ,  B64D35/08 ,  F02C6/02 ,  F02C6/18 ,  F02C9/16 ,  F02C9/20 ,  F05D2220/323 ,  F05D2220/329 ,  F05D2270/13 ,  F05D2270/304

Abstract: There are described methods and systems for operating an aircraft having two or more engines. One method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft; governing the first engine in the active mode using a first governing logic; and governing the second engine in the standby mode using a second governing logic, the second governing logic based on a target compressor speed and variable geometry mechanism (VGM) settings that are adjusted using trim values dependent on at least one parameter of the second engine in the standby mode.

公开(公告)号：US11732643B2

公开(公告)日：2023-08-22

申请号：US17649866

申请日：2022-02-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Kevin Ng ,  Johnny Vinski ,  Adam Logan

IPC: F02C9/18 ,  F02C9/42 ,  B64D13/06 ,  F02C6/02 ,  B64D35/08 ,  F02C6/04 ,  F02C9/52

CPC classification number: F02C6/02 ,  B64D35/08 ,  F02C6/04 ,  F02C9/18 ,  F02C9/42 ,  F02C9/52 ,  F05D2220/329 ,  F05D2270/093 ,  F05D2270/13

Abstract: A multi-engine aircraft includes a first engine drivingly engaged to a common rotatable load and a second engine drivingly engaged to the common rotatable load, the second engine having a bleed air system and a control system in communication with a compressed air switching system. The control system controls operation of the second engine and/or the compressed air switching system. The compressed air switching system includes a switching valve that is displaceable between at least a first position and a second position, the first position interconnecting a lower pressure inlet and a switch outlet, and the second position interconnecting a high pressure inlet and the switch outlet. The switch outlet is in communication with the bleed air system of the second engine. The control system actuates the switching valve to switch between the first and second positions.

公开(公告)号：US11649045B2

公开(公告)日：2023-05-16

申请号：US17949511

申请日：2022-09-21

Applicant: Textron Innovations Inc.

Inventor： William Mathisen Gons

IPC: B64C27/12 ,  B64D31/00 ,  F02C6/20 ,  F02C9/56 ,  F02C9/44 ,  F02C9/48 ,  F02C9/42 ,  B64D27/14 ,  B64D31/06 ,  F02C9/28 ,  B64C27/06 ,  B64D27/24 ,  B64D27/02 ,  B64D35/08

CPC classification number: B64C27/12 ,  B64D27/14 ,  B64D31/00 ,  B64D31/06 ,  F02C6/206 ,  F02C9/28 ,  F02C9/42 ,  F02C9/44 ,  F02C9/48 ,  F02C9/56 ,  B64C27/06 ,  B64D27/24 ,  B64D35/08 ,  B64D2027/026 ,  F05D2220/329 ,  F05D2270/13 ,  F05D2270/44

Abstract: A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.

公开(公告)号：US20180112599A1

公开(公告)日：2018-04-26

申请号：US15331111

申请日：2016-10-21

Applicant: GE AVIATION SYSTEMS, LLC

Inventor： Manish Ashvinkumar Dalal

IPC: F02C7/262 ,  B64D31/06 ,  F02N11/04 ,  F02C7/268

CPC classification number: F02C7/262 ,  B64D33/00 ,  B64D2221/00 ,  F02C7/268 ,  F02N11/04 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2270/13 ,  H02J1/102 ,  H02J3/38 ,  H02J4/00

Abstract: An electrical power system architecture and method for allocating power includes a power distribution bus configured to receive power generated by a first engine having a first generator and a second generator, a first set of electrical buses connected with the power distribution bus and associated with the first engine, and a second set of electrical buses configured to selectively connect with the power distribution bus.

公开(公告)号：US09915201B2

公开(公告)日：2018-03-13

申请号：US14140959

申请日：2013-12-26

Applicant: Rolls-Royce Corporation

Inventor： Michael Abraham Karam ,  Craig Heathco ,  Andrew Eifert

IPC: F02C6/16 ,  F02C7/045 ,  F02C3/13 ,  F02C6/14 ,  F02C7/27 ,  F02K3/12 ,  F02C3/30 ,  F02C6/08 ,  F02C6/04 ,  F02C9/18 ,  F02C7/262 ,  F02C9/52 ,  F02C1/02 ,  F02C6/06 ,  F02C7/26 ,  F02C9/50

CPC classification number: F02C7/045 ,  F02C1/02 ,  F02C3/13 ,  F02C3/305 ,  F02C6/04 ,  F02C6/06 ,  F02C6/08 ,  F02C6/14 ,  F02C6/16 ,  F02C7/26 ,  F02C7/262 ,  F02C7/27 ,  F02C9/18 ,  F02C9/50 ,  F02C9/52 ,  F02K3/12 ,  F05B2260/42 ,  F05B2270/103 ,  F05B2270/1031 ,  F05B2270/1033 ,  F05B2270/1073 ,  F05B2270/111 ,  F05D2260/42 ,  F05D2260/963 ,  F05D2270/05 ,  F05D2270/051 ,  F05D2270/093 ,  F05D2270/13 ,  F05D2270/3061

Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

公开(公告)号：US09845145B2

公开(公告)日：2017-12-19

申请号：US14830914

申请日：2015-08-20

Applicant: General Electric Company

Inventor： Manxue Lu ,  R. Sheldon Carpenter

IPC: B64C11/30 ,  F02C9/58 ,  B64D27/10 ,  B64D27/00

CPC classification number: B64C11/305 ,  B64D27/10 ,  B64D2027/005 ,  F02C9/58 ,  F05D2270/02 ,  F05D2270/052 ,  F05D2270/13 ,  Y02T50/66

Abstract: A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.

公开(公告)号：US20170211468A1

公开(公告)日：2017-07-27

申请号：US15006519

申请日：2016-01-26

Applicant: General Electric Company

Inventor： Maruthi Narasinga Rao Devarakonda ,  Rachel Tarvin Farr

IPC: F02B73/00 ,  F02D41/14 ,  F01N9/00 ,  F02D41/02 ,  F02C9/00 ,  F01N3/20 ,  B01D53/94

CPC classification number: F02B73/00 ,  B01D53/94 ,  B01D53/9431 ,  B01D53/9495 ,  F01K13/02 ,  F01K23/00 ,  F01N3/20 ,  F01N3/208 ,  F01N9/00 ,  F01N2610/02 ,  F02C9/00 ,  F02D41/0235 ,  F02D41/14 ,  F05D2220/32 ,  F05D2270/05 ,  F05D2270/07 ,  F05D2270/08 ,  F05D2270/13

Abstract: A system includes a hybrid power plant controller programmed to receive a plurality of signals representative of one or more operating parameters of a hybrid power plant. The hybrid power plant includes at least one gas turbine engine, at least one gas engine, and at least one catalyst system. The hybrid power plant controller is programmed to utilize closed-loop optimal control to generate one or more operational setpoints based on the one or more operating parameters for the hybrid power plant to optimize performance of the hybrid power plant. The hybrid power plant controller uses closed-loop optimal control to provide the one or more operational setpoints to respective controllers of the at least one gas turbine engine, the at least one gas engine, and the at least one catalyst system to control operation of the gas turbine engine, the gas engine, and the catalyst system.