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：US20220396365A1

公开(公告)日：2022-12-15

申请号：US17345626

申请日：2021-06-11

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Christopher D. Ramsey ,  Coy Bruce Wood ,  Lance L. Smith

IPC: B64D31/10 ,  B64D27/24 ,  B64D27/10 ,  H02P9/00

Abstract: Examples described herein provide a computer-implemented method that includes monitoring a hybrid electric turbine engine of an aircraft, the hybrid electric turbine engine including a first electric machine associated with a high speed spool and a second electric machine associated with a low speed spool. The method further includes receiving an indication of a failed electric machine, the failed electric machine being an electric machine on another hybrid electric turbine engine of the aircraft. The method further includes, responsive to detecting the failed electric machine, distributing power from one or more of the first electric machine or the second electric machine to a spool associated with the failed electric machine.