公开(公告)号：US20230160358A1

公开(公告)日：2023-05-25

申请号：US18151652

申请日：2023-01-09

Applicant: Raytheon Technologies Corporation

Inventor： Neil Terwilliger ,  Gary Collopy

IPC: F02K5/00 ,  F01D19/00 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/28

CPC classification number: F02K5/00 ,  F01D19/00 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/28 ,  B64D2027/026

Abstract: A system includes a gas turbine engine of an aircraft, the gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool and a high spool motor configured to augment rotational power of the high speed spool. The system further includes a controller configured to cause fuel flow. The controller is configured to control a thrust response of the gas turbine engine to a thrust target between zero and a thrust level to move the aircraft during engine start and during engine idle. The controller is also configured to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.

公开(公告)号：US11608797B2

公开(公告)日：2023-03-21

申请号：US17355327

申请日：2021-06-23

Applicant: Raytheon Technologies Corporation

Inventor： Lance L. Smith ,  Neil Terwilliger

IPC: B64D27/00 ,  F02K5/00 ,  B64D27/16 ,  B64D27/24 ,  F01D15/10 ,  F02C7/36 ,  F02C7/32 ,  B64D27/02

Abstract: A hybrid electric gas turbine engine system includes a first compressor and an auxiliary compressor. The first compressor is configured to output first compressed air. The auxiliary compressor is configured to operate in parallel with the first compressor to output second compressed air. A controller is configured to selectively activate the first compressor or the auxiliary compressor based on an operating condition of the hybrid electric gas turbine engine system.

公开(公告)号：US20220412268A1

公开(公告)日：2022-12-29

申请号：US17359891

申请日：2021-06-28

Applicant: Raytheon Technologies Corporation

Inventor： Michael D. Greenberg ,  Lance L. Smith ,  Dennis P. Cronin ,  Nancy Poisson ,  Christopher D. Ramsey ,  Neil Terwilliger

IPC: F02C7/36 ,  F02C6/00

Abstract: A hybrid electric engine of an aircraft includes a compressor, a turbine operably connected to the compressor via a variable gear ratio gearbox and a combustor configured to drive the turbine via a flow of combustion products. An electric motor is operably connected to the variable gear ratio rear box and configured to input rotational energy into the gearbox. The input of rotational energy into the gearbox from the electric motor changes a rotational speed of one of the compressor or the turbine relative to the other of the compressor or the turbine.

公开(公告)号：US20220128003A1

公开(公告)日：2022-04-28

申请号：US17571720

申请日：2022-01-10

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

IPC: F02C6/20 ,  F02C7/36

Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

公开(公告)号：US20210047969A1

公开(公告)日：2021-02-18

申请号：US16912110

申请日：2020-06-25

Applicant: Raytheon Technologies Corporation

Inventor： Neil Terwilliger ,  Marc J. Muldoon

IPC: F02C7/36 ,  F02C6/00 ,  F02C7/20 ,  F02C7/32 ,  F02C3/04 ,  F02K5/00

Abstract: Hybrid electric propulsion systems are described. The hybrid electric propulsion systems include a gas turbine engine including a low speed spool and a high speed spool, the low speed spool including a low pressure compressor and a low pressure turbine, and the high speed spool including a high pressure compressor and a high pressure turbine, a mechanical power transmission configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric motor configured to augment rotational power of at least one of the low speed spool and the high speed spool, and a controller operable to control a power augmentation of at least one of the low speed spool and the high speed spool during an operational stress state of operation of the gas turbine engine.