公开(公告)号：US20200284336A1

公开(公告)日：2020-09-10

申请号：US16833754

申请日：2020-03-30

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F16H57/04 ,  F01D25/18 ,  F02C7/36 ,  F02C3/04

Abstract: A method of assembling an epicyclic gear train includes providing a unitary carrier that includes spaced apart walls and circumferentially spaced mounts interconnecting the walls, spaced apart apertures provided between the mounts at an outer circumference of the carrier, gear pockets provided between the walls and mounts extending to the apertures, and a central opening in at least one of the walls, inserting an intermediate gear through the central opening and moving the intermediate gear radially into the gear pocket to extend through the aperture, inserting a baffle into the carrier, and inserting a sun gear through the central opening to intermesh with the intermediate gear.

公开(公告)号：US10590854B2

公开(公告)日：2020-03-17

申请号：US15006474

申请日：2016-01-26

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C3/10 ,  F02C7/36 ,  F02C3/04 ,  F02C3/00

Abstract: A turboshaft engine includes a high speed spool that connects a high pressure compressor with a high pressure turbine. A low speed spool connects a low pressure compressor with a low pressure turbine. A speed change mechanism includes an input that is in communication with the low spool and a fixed gear ratio. An output turboshaft is in communication with an output of the speed change mechanism.

公开(公告)号：US20200025101A1

公开(公告)日：2020-01-23

申请号：US16203088

申请日：2018-11-28

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F01D25/16 ,  F02C3/107 ,  F02C7/06 ,  F01D5/02 ,  F01D15/12 ,  F02C3/04

Abstract: A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub.

公开(公告)号：US10533522B2

公开(公告)日：2020-01-14

申请号：US15659992

申请日：2017-07-26

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02K3/068 ,  F02C3/073 ,  F02C7/36 ,  F16H1/28 ,  F16H1/48 ,  F16H57/04

Abstract: A disclosed fan drive gear system includes a sun gear rotatable about an axis of rotation, a plurality of intermediate gears rotatable about an intermediate gear rotation axis in meshing engagement with the sun gear and a ring gear circumscribing the intermediate gears. A bearing assembly supports at least one of the plurality of intermediate gears and includes a first beam extending in a first direction and a second beam extending from an end of the first beam in a second direction. The bearing surface supported on the second beam such that first and second beams are configured to maintain the bearing surface substantially parallel to the intermediate gear rotation axis during operation.

公开(公告)号：US20190368424A1

公开(公告)日：2019-12-05

申请号：US15992051

申请日：2018-05-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  William G. Sheridan

IPC: F02C7/36 ,  F01D15/10

Abstract: A power extraction and amplification system for a gas turbine engine is disclosed. In various embodiments, the power extraction and amplification system includes a low spool tower shaft configured for engagement with a low speed spool, a high spool tower shaft configured for engagement with a high speed spool, a first motor, a generator, a differential gear box operably coupled to the low spool tower shaft, to the first motor and to the generator, and a second motor operably coupled to the generator and the high spool tower shaft.

公开(公告)号：US20190353104A1

公开(公告)日：2019-11-21

申请号：US15980870

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Christopher J. Hanlon ,  William G. Sheridan

IPC: F02C7/36 ,  F02C6/00 ,  F02C9/00 ,  F16H1/28 ,  F02K3/06 ,  H02K7/14 ,  H02K7/116 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.

公开(公告)号：US10458330B2

公开(公告)日：2019-10-29

申请号：US15112869

申请日：2015-01-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan

IPC: F02C7/06 ,  F02K3/06 ,  F01D25/20

Abstract: A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.

公开(公告)号：US10358981B2

公开(公告)日：2019-07-23

申请号：US15484376

申请日：2017-04-11

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C7/18 ,  F02C7/36

Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.

公开(公告)号：US20190153887A1

公开(公告)日：2019-05-23

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 ,  F16H57/04 ,  F01D25/18 ,  F16H1/28 ,  F02K3/06

CPC classification number: F01D15/12 ,  F01D25/18 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/50 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/0479 ,  F16H57/0486

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：US20190107004A1

公开(公告)日：2019-04-11

申请号：US16208907

申请日：2018-12-04

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

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

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.