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：US20180128186A1

公开(公告)日：2018-05-10

申请号：US15862777

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

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

Abstract: A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.

公开(公告)号：US20180128185A1

公开(公告)日：2018-05-10

申请号：US15862716

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

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

Abstract: A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.

公开(公告)号：US20180066590A1

公开(公告)日：2018-03-08

申请号：US15811251

申请日：2017-11-13

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36 ,  F02C7/00 ,  F02K3/06 ,  F01D1/04 ,  F02C3/04 ,  F01D25/16 ,  F01D9/04

CPC classification number: F02C7/36 ,  F01D1/04 ,  F01D9/041 ,  F01D25/162 ,  F02C3/04 ,  F02C7/00 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2260/40311

Abstract: In one exemplary embodiment, a gas turbine engine includes a fan section having a fan with a low corrected fan tip speed less than 1400 ft/sec. A bypass ratio is greater than 11.0 and less than 22.0. A fan pressure ratio is less than 1.48. A speed reduction device includes a gear system with a gear ratio of at least 2.6 and less than or equal to 4.1. A low pressure turbine including three stages and a high pressure turbine including two stages. The low pressure turbine includes at least one rotor constrained by a first stress level. At least one of a plurality of fan blades is constrained by a second stress level and has a fan tip speed boundary condition. The gear ratio is configured such that the at least one fan blade does not exceed the fan tip speed boundary condition or the second stress level.

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.

公开(公告)号：US20180010551A1

公开(公告)日：2018-01-11

申请号：US15206434

申请日：2016-07-11

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02K3/06

Abstract: A gas turbine engine includes a fan section that includes a fan rotatable about an engine axis. A compressor section includes a low pressure compressor rotatable about the engine axis. A turbine section includes a fan drive turbine for driving the fan and the low pressure compressor. A speed reduction device connects the fan drive turbine to the fan and the low pressure compressor. The speed reduction device includes a sun gear driven by an inner shaft. A plurality of intermediate gears surround the sun gear. A carrier supports the plurality of intermediate gears for driving the low pressure compressor. A ring gear is located radially outward from the intermediate gears and includes a forward portion for driving a fan drive shaft and an aft portion.

公开(公告)号：US09863326B2

公开(公告)日：2018-01-09

申请号：US14766766

申请日：2014-02-18

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

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

Abstract: A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.

公开(公告)号：US20170234232A1

公开(公告)日：2017-08-17

申请号：US15042794

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  David Allen Stachowiak

IPC: F02C7/268 ,  F02C9/00 ,  H02J7/00 ,  F02C7/275

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：US09732839B2

公开(公告)日：2017-08-15

申请号：US14484673

申请日：2014-09-12

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F16H1/28 ,  F02C7/36 ,  F02K3/06

CPC classification number: F16H57/0424 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  F16H1/28 ,  F16H1/2836 ,  F16H57/0427 ,  F16H57/046 ,  F16H57/0471 ,  F16H57/0479 ,  F16H57/08 ,  F16H2057/085 ,  Y02T50/672 ,  Y10T29/49465 ,  Y10T29/49682 ,  Y10T74/19642 ,  Y10T74/19991

Abstract: A method of assembling a fan drive gear system includes the steps of installing spherical bearings into respective races to provide a plurality of bearing assemblies, mounting at least one of the bearing assemblies onto a corresponding shaft of a torque frame, each of the shafts fixed relative to one another, installing at least one gear onto at least one of the bearing assemblies, the gears meshing with a ring gear and a centrally located sun gear and grounding the torque frame to a static structure to prevent rotation of the torque frame.