公开(公告)号：US20190085771A1

公开(公告)日：2019-03-21

申请号：US16186795

申请日：2018-11-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02C3/107 ,  F02K3/06

Abstract: A method is provided that includes providing a first turbine engine and providing a second turbine engine. The first turbine engine is configured with a first thrust rating. The first turbine engine includes a first engine rotating assembly and a first engine case structure housing at least the first engine rotating assembly. The second turbine engine is configured with a second thrust rating that is different than the first thrust rating. The second turbine engine includes a second engine rotating assembly and a second engine case structure housing at least the second engine rotating assembly. The first engine case structure and the second engine case structure have at least substantially common configurations. The first turbine engine and the second turbine engine are provided by a common entity.

公开(公告)号：US10167873B2

公开(公告)日：2019-01-01

申请号：US15021293

申请日：2014-07-23

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Reade W. James ,  Jacob Peter Mastro

IPC: F01D25/20 ,  F04D29/063 ,  F02C7/32 ,  F01D21/00 ,  F04D19/00 ,  F04D25/02 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D15/12 ,  F16H3/00 ,  F16H57/04

Abstract: A lubrication system includes a shaft rotatable about an axis, a lubrication pump configured to supply a lubricant flow to a gear system, and a gear train coupled to the shaft and configured to drive the lubrication pump in a first direction responsive to rotation of the shaft in both the first direction and a second direction. A gas turbine engine and method are also disclosed.

公开(公告)号：US20180363665A1

公开(公告)日：2018-12-20

申请号：US15625144

申请日：2017-06-16

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F04D25/16 ,  F04D25/04 ,  F04D29/046 ,  F04D29/041 ,  F01D5/02 ,  F01D15/12 ,  F16H1/28 ,  F16H57/10

Abstract: A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

公开(公告)号：US10066506B2

公开(公告)日：2018-09-04

申请号：US15685491

申请日：2017-08-24

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D25/18 ,  F16H1/28 ,  F01D25/16 ,  F02C7/36 ,  F02C7/06 ,  F16H57/04

Abstract: A lubrication system for a fan drive planetary gear system according to an exemplary aspect of the present disclosure includes, among other things, a stationary first bearing configured to receive a lubricant from a lubricant input, the stationary first bearing is axially aligned with a fan drive shaft. A second bearing is configured to rotate with the fan drive shaft, the first bearing engages the second bearing and is configured to transfer the lubricant from the first bearing to the second bearing and into at least one fluid passage in the fan drive shaft. A conduit fluidly connects the at least one passage in the fan drive shaft with at least one component on the fan drive gear system.

公开(公告)号：US10060289B2

公开(公告)日：2018-08-28

申请号：US14794866

申请日：2015-07-09

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D25/18 ,  F01D25/20 ,  F02C7/06 ,  B01D19/00

CPC classification number: F01D25/18 ,  B01D19/0068 ,  B01D19/0073 ,  F01D25/20 ,  F02C7/06 ,  F05D2260/609 ,  Y02T50/671

Abstract: A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed.

公开(公告)号：US20180171815A1

公开(公告)日：2018-06-21

申请号：US15827132

申请日：2017-11-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  William G. Sheridan ,  Michael E. McCune

IPC: F01D15/12 ,  F01D15/08 ,  F01D15/10 ,  F16H1/22 ,  F16H15/04 ,  F16H37/02

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D15/08 ,  F01D15/10 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/402 ,  F05D2260/4031 ,  F05D2270/024 ,  F16H1/222 ,  F16H15/04 ,  F16H37/021

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.

公开(公告)号：US09995177B2

公开(公告)日：2018-06-12

申请号：US14761428

申请日：2014-02-19

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Alan J. Goetschius

IPC: F01D15/12 ,  F01D25/16 ,  F03B11/08 ,  F04D29/70 ,  B01D27/06 ,  F01M11/03 ,  F01D25/20 ,  F02C7/06 ,  F01D5/02 ,  F01M1/10

CPC classification number: F01D25/20 ,  F01D5/02 ,  F01D15/12 ,  F01D25/16 ,  F01M2001/1021 ,  F02C7/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/54 ,  F05D2240/60 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A pump system for a gas turbine engine has at least one pump. At least one valve has an outlet and at least one inlet is fluidly connected to the at least one pump. A geared architecture is positioned within a bearing compartment. The geared architecture is configured to receive lubricating fluid from the outlet of the at least one valve, a self-cleaning filter is positioned downstream of the at least one valve and upstream of the geared architecture. A gas turbine engine and a method are also disclosed.

公开(公告)号：US20180135524A1

公开(公告)日：2018-05-17

申请号：US15872158

申请日：2018-01-16

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F16H57/04 ,  F02C7/06 ,  F01D25/20 ,  F02C3/06 ,  F01D25/16 ,  F04D29/32 ,  F16H1/48

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D9/041 ,  F01D25/162 ,  F01D25/18 ,  F01D25/20 ,  F02C3/04 ,  F02C3/06 ,  F02C3/062 ,  F02C3/107 ,  F02C7/06 ,  F02C7/16 ,  F02C7/32 ,  F02K3/06 ,  F04D19/02 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H1/48 ,  F16H57/0412 ,  F16H57/0486 ,  Y02T50/671

Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an axis, a bypass duct, a compressor section and a bypass ratio greater than 10. A combustor in fluid communication with the compressor section and a fan drive turbine in communication with the combustor. A gear system provides a speed reduction between the fan drive turbine and the fan and transfer power input from the fan drive turbine to the fan at an efficiency greater than 98%.

公开(公告)号：US20180094579A1

公开(公告)日：2018-04-05

申请号：US15828510

申请日：2017-12-01

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F02C7/06

CPC classification number: F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/403 ,  F05D2260/4031

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan delivering air into a bypass duct and into a core engine, a fan drive gear system having a gear carrier, and a fan shaft coupling the fan drive gear system to the fan. The core engine includes a low spool including a low pressure turbine and a low pressure shaft, and a high spool including a high pressure turbine, a compressor, and a high pressure shaft coupling the high pressure turbine to the compressor. A first bearing is forward of the fan drive gear system, and supporting said fan shaft and said fan drive gear system, and a second bearing is aft of the fan drive gear system, and supporting the fan drive gear system.

公开(公告)号：US09926850B2

公开(公告)日：2018-03-27

申请号：US14170687

申请日：2014-02-03

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F16H1/46 ,  F16H1/22

CPC classification number: F02C7/36 ,  F05D2220/327 ,  F05D2260/40311 ,  F16H1/227 ,  F16H1/46

Abstract: A compound star gear system includes a sun gear rotatable about a first axis that drives a first plurality of star gears rotatable about a plurality of fixed axes. The first plurality of star gears drives a second plurality of star gears spaced axially apart from the first plurality of star gears. The second plurality of star gears drive the ring gear that in turn drives a fan drive shaft.