公开(公告)号：US20190128182A1

公开(公告)日：2019-05-02

申请号：US16225623

申请日：2018-12-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C3/107 ,  F02C7/06 ,  F04D29/32 ,  F02C7/36 ,  F01D25/16 ,  F04D29/059 ,  F04D25/02 ,  F02K3/06

CPC classification number: F02C3/107 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F04D25/028 ,  F04D29/059 ,  F04D29/321 ,  F05D2260/40311

Abstract: A turbofan engine comprising a fan shaft configured to rotate about an axis of the engine. A fan drive gear system is configured to drive the fan shaft. A first spool comprises a high pressure turbine and a high pressure compressor. A second spool comprises a lower pressure turbine, a lower pressure compressor, and a shaft coupling the lower pressure turbine to the intermediate pressure compressor. The engine has a plurality of main bearings. The lower pressure compressor has a plurality of disks and a forward hub mounted to a forwardmost disk.

公开(公告)号：US20190072040A1

公开(公告)日：2019-03-07

申请号：US16180548

申请日：2018-11-05

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F01D25/16

Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

公开(公告)号：US20190032572A1

公开(公告)日：2019-01-31

申请号：US16148239

申请日：2018-10-01

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/20 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F02C7/20 ,  F05D2260/403 ,  F05D2260/40311 ,  F05D2260/96

Abstract: A gas turbine engine includes a non-rotatable flexible coupling having Stiffnesses A, B, C, D and E, which are defined herein, and at least ratio of a frame lateral stiffness FLS as follows: FLS/Stiffness A in a range of about 6.0 to about 25.0, FLS/Stiffness B in a range of about 10.0 to about 40.0, FLS/Stiffness C in a range of about 1.5 to about 7.0, FLS/Stiffness D in a range of about 0.25 to about 0.50, or FLS/Stiffness E in a range of about 6.0 to about 40.0.

公开(公告)号：US20180371929A1

公开(公告)日：2018-12-27

申请号：US15632628

申请日：2017-06-26

Applicant: United Technologies Corporation

Inventor： Armando Amador ,  Nasr A. Shuaib ,  Martin J. Walsh ,  William G. Sheridan ,  Eric A. Grover

IPC: F01D11/04 ,  F01D25/16 ,  F16C33/76

Abstract: A bearing assembly according to an example of the present disclosure includes, among other things, a bearing situated in a bearing compartment, a seal assembly that defines the bearing compartment, at least one deflector between the bearing and the seal assembly that is rotatable about an axis, and a coalescer at least partially extending about the at least one deflector to define a fluid passage. A method of sealing is also disclosed.

公开(公告)号：US10161409B2

公开(公告)日：2018-12-25

申请号：US15105118

申请日：2014-11-25

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl D. Blume

IPC: F01D25/18 ,  F16H57/04 ,  F04D29/063 ,  F01M11/02 ,  F04D25/02 ,  F04D29/054 ,  F04D29/056 ,  F04D29/64 ,  F02C7/36

Abstract: A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.

公开(公告)号：US20180355802A1

公开(公告)日：2018-12-13

申请号：US15619799

申请日：2017-06-12

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02C3/04 ,  F02C7/06

Abstract: A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.

公开(公告)号：US10145259B2

公开(公告)日：2018-12-04

申请号：US14785768

申请日：2014-04-25

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F01D15/12 ,  F16H1/28 ,  F01D21/04 ,  F16H1/48

Abstract: An epicyclic gear assembly according to an exemplary embodiment includes, among other things, a carrier including a first plate axially spaced from a second plate by a radially outer connector. A first set of epicyclic gears supported adjacent the first plate include a first set of circumferentially offset intermediate gears meshing with a first sun gear and a first ring gear. A second set of epicyclic gears are axially spaced from the first set of epicyclic gears and supported adjacent the second plate, and include a second set of circumferentially offset intermediate gears meshing with a second sun gear and a second ring gear. The first epicyclic gear set and the second epicyclic gear set maintain relative intermeshing alignment during flexure induced deformation of the carrier.

公开(公告)号：US10119465B2

公开(公告)日：2018-11-06

申请号：US15182909

申请日：2016-06-15

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C3/107 ,  F01D25/18 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F16H1/28 ,  F16H1/48 ,  F02K3/06

Abstract: A geared turbofan engine includes a fan rotatable about an engine axis. A compressor section compresses air and delivers the compressed air to a combustor where the compressed air is mixed with fuel and ignited to drive a turbine section that in turn drives the fan and the compressor section. A gear system is driven by the turbine section for driving the fan at a speed different than the turbine section. The gear system includes a carrier attached to a fan shaft. A plurality of planet gears are supported within the carrier. Each of the plurality of planet gears includes a first row of gear teeth and a second row of gear teeth supported within the carrier. A sun gear is driven by a turbine section. The sun gear is in driving engagement with the plurality of planet gears. At least two separate ring gears circumscribe the plurality of planet gears. Each of the at least two ring gears are supported by a respective flexible ring gear mount that enables movement relative to an engine static structure. A fan drive gear system for a gas turbine engine is also disclosed.

公开(公告)号：US20180202368A1

公开(公告)日：2018-07-19

申请号：US15410113

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: F02C7/32 ,  F02C3/06 ,  F02C7/18 ,  F02C7/36 ,  F02C7/268 ,  F01D15/10 ,  F01D15/12 ,  F01D25/12 ,  F16H1/22 ,  H02K7/116 ,  H02K7/18

CPC classification number: F02C7/32 ,  F01D15/10 ,  F01D15/12 ,  F01D25/12 ,  F02C3/06 ,  F02C7/185 ,  F02C7/268 ,  F02C7/275 ,  F02C7/36 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2260/85 ,  F16H1/222 ,  H02K7/116 ,  H02K7/1823

Abstract: An exemplary gas turbine engine assembly includes a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second turbines are mounted for rotation about a common rotational axis within an engine static structure. The first and second turbine shafts are coaxial with one another. First and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox has a set of gears. A compressor is driven by the first towershaft. The engine assembly further includes a starter generator assembly, and a transmission coupling the starter generator assembly to the 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：US20180202367A1

公开(公告)日：2018-07-19

申请号：US15409974

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: F02C7/32 ,  F02C7/277 ,  F02C7/22 ,  F01D15/10 ,  F01D15/08 ,  F01D15/12 ,  F01D5/06 ,  F01D25/20 ,  F01D25/16

CPC classification number: F02C7/32 ,  F01D5/06 ,  F01D15/08 ,  F01D15/10 ,  F01D15/12 ,  F01D25/16 ,  F01D25/20 ,  F02C7/22 ,  F02C7/277 ,  F02C7/36 ,  F05D2220/32 ,  F05D2220/50 ,  F05D2240/60 ,  F05D2260/4031

Abstract: A gas turbine engine assembly includes 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, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first gear train and a second gear train, the first towershaft extending into a housing and coupled to the first gear train, the second towershaft extending into the housing and coupled to the second gear train, a hydraulic pump, a transmission coupling the hydraulic pump to the first gear train, the transmission transitionable between a first mode where the hydraulic pump is driven at a first speed relative to the first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.