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.

公开(公告)号：US09976437B2

公开(公告)日：2018-05-22

申请号：US14824351

申请日：2015-08-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F16H57/08 ,  F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F02C7/32 ,  F16H57/04

CPC classification number: F01D15/12 ,  F01D1/02 ,  F01D5/02 ,  F01D5/027 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F16H2057/085

Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).

公开(公告)号：US20180135523A1

公开(公告)日：2018-05-17

申请号：US15869276

申请日：2018-01-12

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F16H57/023 ,  F02C3/107 ,  F02C7/32 ,  F02K3/06 ,  F16H1/28 ,  F16H57/08 ,  F16H57/04

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02C7/32 ,  F02K3/06 ,  F05D2230/60 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/023 ,  F16H57/0423 ,  F16H57/0456 ,  F16H57/0479 ,  F16H57/0486 ,  F16H57/082 ,  Y02T50/671 ,  Y10T29/49464

Abstract: A method of assembling an epicyclic gear train according to an example of the present disclosure includes, among other things, the steps of providing a carrier having a central axis that includes spaced apart side walls and circumferentially spaced connecting structure defining mounts that interconnect the side walls, spaced apart apertures provided at an outer circumference of the carrier, gear pockets provided between the side walls and extending to the apertures, and a central opening in at least one of the walls, providing oil baffles between the side walls, the oil baffles including ends that abut the mounts, inserting a plurality of intermediate gears through the central opening, and then moving the intermediate gears radially outwardly into the gear pockets to extend into the apertures, inserting a sun gear through the central opening, and moving the plurality of intermediate gears radially inwardly to engage the sun gear.

公开(公告)号：US20180135454A1

公开(公告)日：2018-05-17

申请号：US15856396

申请日：2017-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F04D25/04 ,  F02K3/06 ,  F04D29/053 ,  F01D5/06 ,  F04D19/00

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness the ring gear transverse stiffness.

公开(公告)号：US20180119564A1

公开(公告)日：2018-05-03

申请号：US15856441

申请日：2017-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/053 ,  F04D25/04 ,  F04D19/00 ,  F01D5/06

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A gear system input connected to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness At least one of the gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.

公开(公告)号：US20180073393A1

公开(公告)日：2018-03-15

申请号：US15816487

申请日：2017-11-17

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/32 ,  F02C7/36 ,  F04D29/056 ,  F04D19/02 ,  F02K3/06 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D5/06 ,  F01D9/02 ,  F01D25/28 ,  F01D15/12

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/16 ,  F01D25/28 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/045 ,  F04D29/053 ,  F04D29/056 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671 ,  Y10T29/49321

Abstract: A gas turbine engine includes a fan that has fan blades. A fan shaft is drivingly connected to the fan. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation. The gear system flex mount arrangement includes a gear mesh that defines a gear mesh lateral stiffness and a flexible support that defines a flexible support lateral stiffness that is less than 8% of the gear mesh lateral stiffness.

公开(公告)号：US20180073392A1

公开(公告)日：2018-03-15

申请号：US15801611

申请日：2017-11-02

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F02C3/107 ,  F04D29/056 ,  F02C7/06 ,  F02C7/20 ,  F04D29/66 ,  F01D5/06 ,  F01D9/04

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/041 ,  F01D15/12 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/028 ,  F04D25/045 ,  F04D29/056 ,  F04D29/325 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20180045119A1

公开(公告)日：2018-02-15

申请号：US15232101

申请日：2016-08-09

Applicant: United Technologies Corporation

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

IPC: F02C7/32 ,  F02C7/275 ,  F02N11/00 ,  F02K3/06

CPC classification number: F02C7/32 ,  F02C3/107 ,  F02C7/275 ,  F02K3/06 ,  F02N11/00 ,  F05D2220/327 ,  F05D2220/76 ,  F05D2260/532 ,  F05D2260/85 ,  F05D2260/98

Abstract: A geared turbofan engine includes a first spool including a first compressor and a first turbine. The first compressor is immediately before a combustor and the first turbine is immediately after the combustor. A second spool includes at least a second turbine disposed axially aft of the first turbine. A first tower shaft is engaged to drive the high speed spool. A second tower shaft engaged to be driven by the second spool. A starter is engaged to drive the first tower shaft. An accessory gear box is driven by the second tower shaft. A first clutch is disposed between the first tower shaft and the starter. The first clutch is configured to enable the starter to drive the high speed spool. A second clutch is disposed between the second tower shaft and the accessory gear box, the second clutch configured to enable the second spool to drive the accessory gear box. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

公开(公告)号：US09885282B2

公开(公告)日：2018-02-06

申请号：US14207718

申请日：2014-03-13

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 (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.