公开(公告)号：US3508395A

公开(公告)日：1970-04-28

申请号：US3508395D

申请日：1968-04-01

申请人： FORD MOTOR CO

发明人： SEBESTYEN THOMAS M

IPC分类号： F02C9/54 ,  F02C3/10 ,  F02C9/08 ,  F02C9/10

CPC分类号： F02C9/54 ,  F05D2200/15

公开(公告)号：US3325994A

公开(公告)日：1967-06-20

申请号：US51270065

申请日：1965-12-09

申请人： BBC BROWN BOVERI & CIE

发明人： TADEUSZ ZABA ,  FRITS WEEHUIZEN

IPC分类号： F02C7/22 ,  F02C9/54

CPC分类号： F02C7/22 ,  F02C9/54

公开(公告)号：US3243596A

公开(公告)日：1966-03-29

申请号：US32541163

申请日：1963-11-21

申请人： GEN ELECTRIC

发明人： ARNE LOFT

IPC分类号： F02C9/54

CPC分类号： F02C9/54

公开(公告)号：US12012905B2

公开(公告)日：2024-06-18

申请号：US16766421

申请日：2018-11-30

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Keisuke Yamamoto ,  Kazushige Takaki ,  Makoto Kishi ,  Shinya Uchida ,  Hisashi Nakahara ,  Hikaru Katano ,  Yoshikazu Ui

IPC分类号： F02C9/54

CPC分类号： F02C9/54 ,  F05D2220/32 ,  F05D2270/05

摘要： A control device selects and executes any of normal control of outputting a fuel flow rate command value through feedback control based on a deviation between a target output and an actual output of a gas turbine and load decreasing control of outputting the fuel flow rate command value for reducing an output of the gas turbine to a predetermined target output during a predetermined first time without performing feedback control, and performs control of reducing a flow rate of air flowing into a compressor of the gas turbine such that an air-fuel ratio settles within a predetermined range, in parallel with execution of the load decreasing control when the load decreasing control is selected.

公开(公告)号：US20240102388A1

公开(公告)日：2024-03-28

申请号：US18494907

申请日：2023-10-26

申请人： ABB Schweiz AG

发明人： Camilo Lopez ,  Mark Foltz ,  Steve Miller ,  Kevin Dowdell ,  Mark Wieland ,  Alan Majors

IPC分类号： F01C20/28 ,  F01D17/06 ,  F01D17/14 ,  F01D17/26 ,  F01D21/02 ,  F01K13/00 ,  F01K13/02 ,  F02C7/232 ,  F02C9/26 ,  F02C9/28 ,  F02C9/52 ,  F02C9/54 ,  F16K37/00 ,  G01P21/02 ,  G01R31/28 ,  H02J3/38 ,  H02J3/40

CPC分类号： F01C20/28 ,  F01D17/06 ,  F01D17/145 ,  F01D17/26 ,  F01D21/02 ,  F01K13/003 ,  F01K13/02 ,  F02C7/232 ,  F02C9/263 ,  F02C9/28 ,  F02C9/52 ,  F02C9/54 ,  F16K37/0041 ,  F16K37/0083 ,  G01P21/02 ,  G01R31/2829 ,  H02J3/381 ,  H02J3/40 ,  F05D2220/31 ,  F05D2260/80 ,  F05D2270/02 ,  F05D2270/021 ,  F05D2270/80

摘要： A system for controlling a turbine valve is provided. The system includes a hydraulic pilot valve section being moveable in a first direction and a second direction; a main hydraulic valve section being moveable in a first direction to close the turbine valve and a second direction to open the turbine valve; a position demand indicating a desired position of the turbine valve; a first feedback indicating an actual position of the hydraulic pilot valve section; and aa second feedback indicating an actual position of the main hydraulic valve section. The system also includes a pilot valve error; a main valve error; a turbine valve error; and a pilot valve adjustment moving the hydraulic pilot valve section in response to the turbine valve error. The turbine valve error is repeatedly determined and the pilot valve adjustment repeatedly moves the hydraulic pilot valve section to minimize the turbine valve error.

公开(公告)号：US11920483B2

公开(公告)日：2024-03-05

申请号：US17425389

申请日：2020-01-23

申请人： SAFRAN HELICOPTER ENGINES

发明人： Matthieu Julien Gallot ,  Philippe Jean René Marie Benezech ,  Jean-Luc Charles Gilbert Frealle ,  Luc Jacques Pierre Reberga ,  Pascal Rizzo

IPC分类号： F01D17/26 ,  F01D17/16 ,  F01D21/00 ,  F02C7/22 ,  F02C9/20 ,  F02C9/54

CPC分类号： F01D17/26 ,  F01D17/16 ,  F01D21/003 ,  F02C7/22 ,  F02C9/20 ,  F02C9/54 ,  F05D2220/323 ,  F05D2220/329 ,  F05D2270/03 ,  F05D2270/44 ,  F05D2270/64

摘要： The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members (18) of a turbomachine (10), the members (18) being configured to travel over an operating area comprising a first position P1 and a second position P2, the method comprising the steps of: —(E23) determining a first pivoting speed V1 from the first position P1 to the second position P2; —(E25) determining a second pivoting speed from the second position P2 to the first position P1; and—(E26) determining an anomaly in the operation of the system for positioning the members (18) if the first speed V1 is lower than a first determined speed threshold and/or if the second speed V2 is lower than a second determined speed threshold.

公开(公告)号：US11814964B2

公开(公告)日：2023-11-14

申请号：US17092477

申请日：2020-11-09

申请人： ABB Schweiz AG

发明人： Camilo Lopez ,  Mark Foltz ,  Steve Miller ,  Kevin Dowdell ,  Mark Wieland ,  Alan Majors

IPC分类号： F01C20/28 ,  G01P21/02 ,  G01R31/28 ,  F01D17/06 ,  F02C9/28 ,  F01D21/02 ,  H02J3/38 ,  H02J3/40 ,  F01K13/00 ,  F01K13/02 ,  F16K37/00 ,  F02C7/232 ,  F02C9/26 ,  F02C9/52 ,  F02C9/54 ,  F01D17/14 ,  F01D17/26

CPC分类号： F01C20/28 ,  F01D17/06 ,  F01D17/145 ,  F01D17/26 ,  F01D21/02 ,  F01K13/003 ,  F01K13/02 ,  F02C7/232 ,  F02C9/263 ,  F02C9/28 ,  F02C9/52 ,  F02C9/54 ,  F16K37/0041 ,  F16K37/0083 ,  G01P21/02 ,  G01R31/2829 ,  H02J3/381 ,  H02J3/40 ,  F05D2220/31 ,  F05D2260/80 ,  F05D2270/02 ,  F05D2270/021 ,  F05D2270/80

摘要： A control system is provided for a turbine valve. The turbine valve has a first coil and a second coil to control or sense movement of a mechanical valve positioner. Two valve positioners are provided with each valve positioner having two drive circuits to drive the first and second coils. Switches are provided such that only one drive circuit is connected to each coil at a time. The control system may also include a hydraulic pilot valve section and a main hydraulic valve section. Feedbacks are used to determine a pilot valve error and a main valve error which are combined to determine a turbine valve error. The turbine valve error is repeatedly determined to minimize the error.

公开(公告)号：US11746713B2

公开(公告)日：2023-09-05

申请号：US16794620

申请日：2020-02-19

申请人： ROLLS-ROYCE plc

发明人： Ibrahim Sanusi ,  Andrew R Mills ,  Derek S Wall

IPC分类号： F02C9/52 ,  F02C9/54

CPC分类号： F02C9/52 ,  F02C9/54 ,  F05D2270/30 ,  F05D2270/303 ,  F05D2270/44

摘要： A control system of a gas turbine engine is provided. The engine has a fuel flow metering valve which regulates a fuel flow to the engine, and one or more variable geometry components which are movable between different set points to vary an operating configuration of the engine. The control system has an engine fuel control sub-system which provides a fuel flow demand signal for controlling the fuel flow metering valve. The control system further has a variable geometry control sub-system which determines current set points to be adopted by the variable geometry components given the current engine operating condition in order to comply with one or more engine constraints. The control system further has an optimiser that receives the current set points and determines adjusted values of the set points which optimise, while complying with the engine constraints, an objective function modelling a performance characteristic of the engine, the objective function adapting to change in engine performance with time. The control system further has a feedback loop in which the adjusted values of the set points thus-determined are sent to the variable geometry control sub-system to vary the current set points.

公开(公告)号：US11655778B2

公开(公告)日：2023-05-23

申请号：US17396050

申请日：2021-08-06

申请人： Raytheon Technologies Corporation

发明人： Michael M. Joly ,  Zaffir A. Chaudhry ,  Andrzej Ernest Kuczek ,  Om P. Sharma ,  Georgi Kalitzin ,  Simon W. Evans

IPC分类号： F02C9/20 ,  F02K3/06 ,  F02C9/22 ,  F01D5/28 ,  F02C9/58 ,  F02C9/54

CPC分类号： F02K3/06 ,  F01D5/28 ,  F02C9/20 ,  F02C9/22 ,  F02C9/54 ,  F02C9/58 ,  F05D2220/36 ,  F05D2240/128

摘要： A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

公开(公告)号：US11542872B2

公开(公告)日：2023-01-03

申请号：US17501051

申请日：2021-10-14

申请人： Raytheon Technologies Corporation

发明人： Neil Terwilliger ,  John P. Virtue

IPC分类号： F02C7/268 ,  B64D27/10 ,  B64D27/24 ,  F02C9/54 ,  F02K5/00 ,  F02C6/14 ,  B64D27/02 ,  B64D31/06 ,  B64D33/00 ,  F02C9/26

摘要： An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state.