公开(公告)号：US20220010736A1

公开(公告)日：2022-01-13

申请号：US17484331

申请日：2021-09-24

Applicant: Raytheon 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. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

公开(公告)号：US11156166B2

公开(公告)日：2021-10-26

申请号：US16180548

申请日：2018-11-05

Applicant: Raytheon 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：US11091272B2

公开(公告)日：2021-08-17

申请号：US16039849

申请日：2018-07-19

Applicant: Raytheon Technologies Corporation

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

IPC: F02C6/14 ,  B64D27/24 ,  B64D27/10 ,  F01D15/10 ,  F02C7/36 ,  H02K7/18 ,  B64D27/02 ,  F02C6/02 ,  F02C3/107

Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.

公开(公告)号：US20210010426A1

公开(公告)日：2021-01-14

申请号：US16919620

申请日：2020-07-02

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F02C3/04

Abstract: A gas turbine engine comprises a fan rotor having a hub and a plurality of fan blades extending radially outwardly of the hub. A compressor is positioned downstream of the fan rotor, and has a first compressor blade row defined along a rotational axis of the fan rotor and the compressor rotor. A gear reduction is positioned axially between the first compressor blade row and the fan rotor, and includes a ring gear and a carrier. The carrier has an axial length and the ring gear has an outer diameter. A ratio of the axial length to the outer diameter may be greater than or equal to about 0.20 and less than or equal to about 0.40. The gear reduction is connected to drive the hub to rotate. A method of designing a gas turbine engine is also disclosed.