公开(公告)号：US11840968B2

公开(公告)日：2023-12-12

申请号：US17485982

申请日：2021-09-27

Applicant: RTX Corporation

Inventor： Matthew D. Teicholz ,  James W. Dunn ,  Christopher P. Kmetz ,  Louis A. Celiberti

IPC: F02C9/42 ,  F01D25/34 ,  F02C7/275 ,  F02C7/26 ,  F01D13/00 ,  B64D27/02 ,  B64D31/02 ,  F01D19/00 ,  F01D21/00 ,  F02C7/268

CPC classification number: F02C9/42 ,  B64D27/02 ,  B64D31/02 ,  F01D13/003 ,  F01D19/00 ,  F01D21/003 ,  F01D25/34 ,  F02C7/26 ,  F02C7/268 ,  F02C7/275 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/13 ,  F05D2270/14

Abstract: An aspect includes a method for motoring control for multiple engines of an aircraft is provided. A controller can determine a motoring time of a first engine starting system to cool a first engine. The controller can compare the motoring time of the first engine starting system with a motoring time of one or more other engine starting systems of one or more other engines of the aircraft. The motoring time of the first engine starting system can be controlled relative to a tolerance of the motoring time of the one or more other engine starting systems by adjusting the motoring time of the first engine starting system relative to the one or more other engine starting systems in a motoring sequence based on comparing the motoring time of the first engine starting system with the motoring time of the one or more other engine starting systems.

公开(公告)号：US11668248B2

公开(公告)日：2023-06-06

申请号：US16895223

申请日：2020-06-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Dana Tomescu

IPC: F02C9/00 ,  F01D19/02 ,  F02C7/268 ,  F01D21/00 ,  F01D25/34

CPC classification number: F02C9/00 ,  F01D19/02 ,  F01D21/00 ,  F01D25/34 ,  F02C7/268 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/303 ,  F05D2270/313 ,  F05D2270/44 ,  F05D2270/708

Abstract: There is provided a rotor bow mitigation system and method for an aircraft engine. At least one value of at least one engine parameter prior to a shutdown of the engine is obtained, the at least one engine parameter comprising a first temperature internal to the engine. A second temperature external to the engine is measured and a motoring duration and a motoring interval for the engine are determined based on at least the first temperature and on the second temperature. Upon detecting a start indication for the engine, the engine is motored for the motoring duration and at the motoring interval.

公开(公告)号：US11274604B2

公开(公告)日：2022-03-15

申请号：US16745921

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Amy R. Grace

IPC: F01D19/02 ,  F01D25/34 ,  F02C7/27 ,  F02C7/268 ,  F01D25/24 ,  F02C3/107 ,  F02C7/06 ,  F02K3/04 ,  G05B15/02

Abstract: A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter based on at least one aircraft-based parameter received on the aircraft communication bus, where the at least one inferred engine operating thermal parameter is based on data describing a history of the aircraft before an engine shutdown. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected range.

公开(公告)号：US11187102B2

公开(公告)日：2021-11-30

申请号：US16931857

申请日：2020-07-17

Applicant: General Electric Company

Inventor： Charles Stanley Orkiszewski

IPC: F01D19/02 ,  F04D29/66 ,  F01D25/34 ,  F01D5/02 ,  F04D29/52 ,  F16D43/30 ,  F16D43/04 ,  F01D19/00 ,  F02C7/268 ,  F02C7/26 ,  F02C7/277

Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.

公开(公告)号：US11131323B2

公开(公告)日：2021-09-28

申请号：US16507553

申请日：2019-07-10

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F04D29/56 ,  F04D27/00 ,  F01D9/04 ,  F01D17/12 ,  F01D17/14 ,  F01D17/16 ,  F01D25/34

Abstract: A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.

公开(公告)号：US11060419B2

公开(公告)日：2021-07-13

申请号：US16425246

申请日：2019-05-29

Applicant: Rolls-Royce Deutschland Ltd & Co KG

Inventor： Hannes Wuestenberg

IPC: F01D25/28 ,  F01D25/34 ,  F02C7/36 ,  F16H57/025 ,  F16H57/08 ,  F16H57/02

Abstract: The invention relates to a planetary gearbox having a ring gear support, in particular in a geared fan engine, characterized by a bolt connection for connecting the ring gear support to a static component, wherein the bolt connections are arranged on the circumference of the ring gear support in the axial direction of the planetary gearbox, and the bolt connections are designed and arranged in such a way that there is a frictional joint with a defined frictional force between the ring gear support and the static component and that a material separation, in particular a gap, is arranged between the ring gear support and the static component.

公开(公告)号：US20200003127A1

公开(公告)日：2020-01-02

申请号：US16451606

申请日：2019-06-25

Applicant: ROLLS-ROYCE plc

Inventor： Mark N. BINNINGTON

IPC: F02C7/36 ,  F01D25/16 ,  F01D25/34 ,  F02K3/06 ,  F16H1/28 ,  F16H57/08

Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a part on the input shaft on the input side of the gearbox device.

公开(公告)号：US10301962B2

公开(公告)日：2019-05-28

申请号：US15079400

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jesse M Chandler ,  Gabriel L Suciu ,  Joseph Stack

IPC: F01D9/04 ,  F01D17/12 ,  F01D17/14 ,  F01D17/16 ,  F01D25/34 ,  F02K3/02

Abstract: A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.

公开(公告)号：US20180283274A1

公开(公告)日：2018-10-04

申请号：US15475791

申请日：2017-03-31

Applicant: The Boeing Company

Inventor： Jason J. Jackowski ,  Kent E. Karnofski

IPC: F02C6/14 ,  F01D15/10 ,  F02C7/20 ,  F02C9/26 ,  F01D15/12 ,  B64D27/18 ,  F01D25/34

CPC classification number: F02C6/14 ,  B64D27/16 ,  B64D41/00 ,  B64D2221/00 ,  F01D25/34 ,  F02C3/107 ,  F02C7/20 ,  F02C7/32 ,  F02C7/36 ,  F02C9/26 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/43 ,  F05D2260/941 ,  Y02T50/672

Abstract: A mechanical flywheel used to power an aircraft system. In one example, the flywheel is used to rotate a rotor shaft in the aircraft's engine and prevent bowing of the rotor shaft caused by a thermal gradient. In another example, the mechanical flywheel provides electrical power at peak demand times. In yet another example, the flywheel is used as a load source or sink by the engine's control system so as to aid engine operability and engine acceleration rates during abnormal flight conditions.

公开(公告)号：US09970328B2

公开(公告)日：2018-05-15

申请号：US14156028

申请日：2014-01-15

Applicant: ANSALDO ENERGIA IP UK LIMITED

Inventor： Axel Haerms ,  Felix Staehli ,  Marc Rauch ,  Eric Knopf

IPC: F01D21/12 ,  F01D25/34 ,  F01D25/36 ,  F01D21/06

CPC classification number: F01D25/36 ,  F01D21/06 ,  F01D25/34 ,  F05D2260/4031 ,  F05D2270/304

Abstract: A method for barring a rotor of a thermally loaded turbomachine includes stopping normal operation of the turbomachine; providing a barring device for rotating the rotor about a machine axis; coupling the barring device to the rotor; letting the rotor cool down during cool down of the rotor rotating the rotor by means of the barring device. A damage of the machine due to thermally induced buckling during the barring process is avoided by consecutively determining the force or torque applied to the rotor by the barring device for rotating the rotor and/or the circumferential speed of the rotor during barring. The rotation of the rotor is controlled by means of the barring device in dependence of the determined force or torque and/or circumferential speed in order to reduce a bending or imbalance of the rotor, which is due to a nonuniform temperature distribution on the rotor during cool down.