公开(公告)号：US12259036B2

公开(公告)日：2025-03-25

申请号：US15958718

申请日：2018-04-20

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F01D25/20 ,  F02C7/06 ,  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：US11415064B2

公开(公告)日：2022-08-16

申请号：US16689690

申请日：2019-11-20

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  William G. Sheridan

IPC: F02C7/36 ,  F16H57/00 ,  F16H57/08

Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a geared architecture. A flexible support supports the geared architecture relative to an engine static structure. A deflection limiter includes at least one of an axially extending branch or a radially extending branch. A flexible output shaft is in driving engagement with the fan section and driven by the geared architecture. A speed change mechanism for a gas turbine engine is also disclosed.

公开(公告)号：US11215122B2

公开(公告)日：2022-01-04

申请号：US16689656

申请日：2019-11-20

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Jason Husband

IPC: F02C7/36 ,  F02C7/06

Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a planetary gear system. The planetary gear system includes a plurality of planet gears surrounding a sun gear. A carrier supports the plurality of planet gears and includes a first carrier bearing flange. A ring gear surrounds the plurality of planet gears and includes a ring gear bearing flange. At least one ring gear carrier bearing engages the carrier bearing flange and the ring gear bearing flange. A speed change mechanism for a gas turbine is also disclosed.

公开(公告)号：US11053816B2

公开(公告)日：2021-07-06

申请号：US15007263

申请日：2016-01-27

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C3/06 ,  F01D25/24 ,  F02K3/06 ,  F16H1/28 ,  F02C3/107 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F04D29/32 ,  F02C7/36

Abstract: A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter. A transitional entrance passage is configured to communicate flow between the fan section and a compressor section. The transitional entrance passage includes an inlet disposed at an inlet diameter and an outlet to the compressor section disposed at an outlet diameter. A method of designing a gas turbine engine is also disclosed.

公开(公告)号：US11015533B2

公开(公告)日：2021-05-25

申请号：US16671432

申请日：2019-11-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02C7/36 ,  F16H1/28

Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.

公开(公告)号：US11008885B2

公开(公告)日：2021-05-18

申请号：US16208907

申请日：2018-12-04

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

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

Abstract: An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate by a connector. A first epicyclic gear set is supported adjacent the first plate and includes a first set of circumferentially offset intermediate gears meshing with a first sun gear and a first ring gear. A second epicyclic gear set is axially spaced from the first epicyclic gear set and supported adjacent the second plate and includes a second set of circumferentially offset intermediate gears meshing with a second sun gear and a second ring gear. The first epicyclic gear is set and the second epicyclic gear set maintain relative intermeshing alignment during flexure-induced deformation of the carrier. The first ring gear includes a first set of teeth that extends from a first flexible flange and the second ring gear includes a second set of teeth that extends from a second flexible flange.

公开(公告)号：US10801355B2

公开(公告)日：2020-10-13

申请号：US16173051

申请日：2018-10-29

Applicant: United Technologies Corporation

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

IPC: F01D15/12 ,  F02C7/36 ,  F01D25/18 ,  F02K3/06 ,  F16H1/28 ,  F16H57/04

Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.

公开(公告)号：US10794216B2

公开(公告)日：2020-10-06

申请号：US16012059

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D15/10 ,  F02C7/36 ,  F02K3/06 ,  H02K11/00 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other things, a fan driven by a fan shaft rotatable about an engine axis; a fan drive electric motor providing a supplemental drive input to the fan; a turbine section driving an input shaft; a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and a generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor, wherein the generator communicates electric power to power the fan drive electric motor.

公开(公告)号：US10787971B2

公开(公告)日：2020-09-29

申请号：US16148239

申请日：2018-10-01

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

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：US10753285B2

公开(公告)日：2020-08-25

申请号：US15869276

申请日：2018-01-12

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  William G. Sheridan

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

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.