公开(公告)号：US20210222623A1

公开(公告)日：2021-07-22

申请号：US17060560

申请日：2020-10-01

Applicant: Raytheon Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/18 ,  F01D15/10 ,  F01D25/12 ,  F02C7/32 ,  H02K9/16 ,  H02K7/18 ,  H02K9/06

Abstract: A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.

公开(公告)号：US11040780B2

公开(公告)日：2021-06-22

申请号：US16057362

申请日：2018-08-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: H02K7/02 ,  B64D27/02 ,  B64D27/24 ,  B64D35/04 ,  B64D35/08 ,  H02J15/00

Abstract: An aircraft power system according to an exemplary embodiment of this disclosure includes, among other possible things, a battery, a motor/generator coupled to the battery, an inertial drum rotatable about an axis of rotation and coupled to the motor/generator, wherein the motor/generator drives rotation of the inertial drum in a first operating mode and is driven by the inertial drum in a second operating mode; and a housing defining a chamber for the inertial drum, the chamber filled with low-viscosity medium to reduce friction on the inertial drum.

公开(公告)号：US10815823B2

公开(公告)日：2020-10-27

申请号：US16424641

申请日：2019-05-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F01D15/12 ,  F01D21/00 ,  F04D29/053 ,  F04D29/32 ,  F02K3/06 ,  F02C7/32 ,  F02C7/36 ,  F16D63/00 ,  F01D21/04 ,  F16D11/16 ,  F16D11/00

Abstract: A gas turbine engine has an engine static structure and at least one component rotatable relative to the engine static structure about an engine axis of rotation. A fan is coupled to at least one component for rotation about the engine axis of rotation. An actuator is mounted to the engine static structure, wherein the actuator is activated to prevent the fan from rotation and is inactivated to allow the fan to rotate. A method for preventing rotation of a fan in a gas turbine engine is also disclosed.