公开(公告)号：US20190382121A1

公开(公告)日：2019-12-19

申请号：US16012047

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  B64D31/14 ,  B64D33/04 ,  F02C6/20 ,  F02C6/14 ,  B64D31/02 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00

Abstract: A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least one auxiliary propulsion fan is configured to selectively receive a motive force from either or both of the at least two gas turbine engines through at least one shaft operatively coupled to the at least one auxiliary propulsion fan.

公开(公告)号：US10508601B2

公开(公告)日：2019-12-17

申请号：US15042794

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  David Allen Stachowiak

IPC: F02C7/26 ,  F02C7/32 ,  F01D25/36 ,  F02C7/268 ,  F01D21/00 ,  F02C7/275 ,  F02C9/00 ,  H02J7/00 ,  H02J7/34

Abstract: A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor operable to drive rotation of a starting spool of the gas turbine engine through the gear train at a substantially constant speed upon engine shutdown until an energy storage source is depleted.

公开(公告)号：US20190353105A1

公开(公告)日：2019-11-21

申请号：US15981559

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02K3/04 ,  F16H1/20 ,  F16D41/069

Abstract: A gas turbine engine includes a fan. Also included is an oil pump operatively connected to the fan by a main input drive gear, the drive gear rotating when the fan rotor rotates in either a first or second direction of the fan. Further included is a gear train intermediate the main input drive gear and the oil pump, the gear train including a first and second pinion gear, the first and second pinion gear each driven by the main input drive gear, the first pinion gear driving a first gear through a first clutch, the second pinion gear driving a second gear through a second clutch. Only one of the clutches transmits rotation from the respective pinion gear to the respective gear when the fan is rotating in the first direction, with the only the other clutch transmitting rotation when the fan is rotating in the second direction.

公开(公告)号：US20190323597A1

公开(公告)日：2019-10-24

申请号：US15958718

申请日：2018-04-20

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F02C7/06 ,  F01D25/20 ,  F02C7/36

Abstract: A gas turbine engine includes a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine and, in turn, to drive the fan rotor. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil supply system includes a rotation sensor for sensing rotation of a component that will rotate with the fan rotor, a control, an auxiliary oil pump, and a main supply sensor for sensing operation of the main oil supply system. The control is programmed to supply oil from the auxiliary oil pump to the gear reduction when the rotation sensor senses the component is rotating. A determination is made that inadequate oil is being supplied from the main oil supply system based upon information from the main supply sensor.

公开(公告)号：US10443708B2

公开(公告)日：2019-10-15

申请号：US15132620

申请日：2016-04-19

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F16H1/28 ,  F16H57/08 ,  F02C3/107 ,  F01D25/16 ,  F02C7/36

Abstract: A gear system for a geared turbofan engine includes a sun gear, a planet gear supported in a carrier and engaged to the sun gear, a forward journal bearing and an aft journal bearing both supporting the planet gear. The carrier includes a forward wall supporting the forward journal bearing and an aft wall supporting the aft journal bearing. A ring gear is engaged to the planet gear. A geared turbofan engine is also disclosed.

公开(公告)号：US20190292943A1

公开(公告)日：2019-09-26

申请号：US15934616

申请日：2018-03-23

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D25/20 ,  F16H57/04 ,  F02C7/36 ,  F01D15/12 ,  F02K3/06 ,  F02C7/06 ,  F02C7/32

Abstract: A gas turbine engine includes a fan driven by a fan drive turbine through a gear reduction. An oil pump is driven by a main input gear, and the main input drive gear rotates when the fan rotor rotates. A gear train is intermediate the main input gear and the oil pump. The gear train includes a forward input gear and a reverse input gear, each driven by the main input gear. The forward input gear drives a forward pinion gear through a first clutch and the reverse input gear drives a reverse pinion gear through a reverse clutch. The forward clutch transmits rotation from the forward input gear to the forward pinion gear when the fan is rotating in a first direction, and not transmitting rotation from the forward input gear to the forward pinion gear when the fan is rotating in a second opposed direction. The reverse clutch transmits rotation from the reverse input gear to the reverse pinion gear when the fan is rotating in the second opposed direction, and not transmitting rotation from the reverse input gear to the reverse pinion gear when the fan is rotating in the first direction. One of the forward and reverse pinion gears drive a pump drive gear, to, in turn, drive the pump.

公开(公告)号：US10422243B2

公开(公告)日：2019-09-24

申请号：US15410049

申请日：2017-01-19

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F01D15/12 ,  F02C7/268 ,  F01D5/06 ,  F01D15/10 ,  F01D25/20 ,  F16H3/30 ,  F02C7/277 ,  F02C7/32 ,  F02C7/36

Abstract: An exemplary gas turbine engine assembly includes a transmission coupling a starter generator assembly to a first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.

公开(公告)号：US10337401B2

公开(公告)日：2019-07-02

申请号：US14622523

申请日：2015-02-13

Applicant: United Technologies Corporation

Inventor： Daniel B. Kupratis ,  William G. Sheridan

IPC: F02C3/34 ,  F01D13/00 ,  F02C3/073 ,  F02C7/08 ,  F02C7/36 ,  F02C3/14 ,  F02K3/115

Abstract: A turbine engine is provided that includes a turbo-compressor, a combustor section, a flow path and a recuperator. The turbo-compressor includes a compressor section and a turbine section. The combustor section includes a combustor and a plenum adjacent the combustor. The flow path extends through the compressor section, the combustor section and the turbine section. The recuperator is configured with the flowpath between the combustor section and the turbine section. An inlet duct to the recuperator is fluidly coupled with the flow path upstream of the plenum. An outlet duct from the recuperator is fluidly coupled with the plenum.

公开(公告)号：US10316758B2

公开(公告)日：2019-06-11

申请号：US14888154

申请日：2014-05-02

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02K3/06

Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between about 219 and 328.

公开(公告)号：US10309307B2

公开(公告)日：2019-06-04

申请号：US15185377

申请日：2016-06-17

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Paul H. Dolman

IPC: F02C7/06 ,  F01D25/20 ,  F01M11/06 ,  F16K15/04

Abstract: A method of supplying a bearing compartment with fluid includes the steps of pumping a fluid from a main reservoir to a bearing compartment through a main supply passage which includes one or more passage segments. During a positive gravity condition, the pumping step is performed using a main pump arranged in the main supply passage. The main reservoir includes upper and lower portions. The main supply passage is in fluid communication with the lower portion. Fluid is provided from the main reservoir to the bearing compartment through a secondary supply passage that is fluidly connected to at least one segment of the main supply passage in response to a negative gravity condition. The secondary supply passage is in fluid communication with the upper portion.