公开(公告)号：US20220396363A1

公开(公告)日：2022-12-15

申请号：US17345619

申请日：2021-06-11

Applicant: Raytheon Technologies Corporation

Inventor： Arnab Roy ,  Marc J. Muldoon ,  Neil Terwilliger ,  Nancy Poisson

IPC: B64D27/24 ,  B64D27/10 ,  G08G5/00 ,  B64D31/06

Abstract: Examples described herein provide a computer-implemented method for managing battery usage for a hybrid electric engine of an aircraft. The method includes receiving a flight plan comprising flight plan data for a flight of an aircraft. The method further includes receiving battery data about a battery system of the aircraft. The method further includes determining waypoints for when to apply electric power from the battery system based at least in part on the flight plan data and the battery data. The method further includes controlling, based at least in part on the waypoints, an electric motor while the flight plan is executed. The method further includes updating, while the flight plan is executed, the waypoints based at least in part on data received during the flight.

公开(公告)号：US20220397064A1

公开(公告)日：2022-12-15

申请号：US17837829

申请日：2022-06-10

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Arnab Roy ,  John R. Farris

IPC: F02C7/32 ,  B64D27/24 ,  B64D27/16 ,  F02C6/14

Abstract: A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; at least one blade outer air seal positioned between an outer case of the high pressure turbine and a plurality of blades of the high pressure turbine; a clearance control system operably coupled to the at least one blade outer air seal, the clearance control system configured to vary a position of the at least one blade outer air seal with respect to the plurality of blades of the high pressure turbine; and a controller operably coupled to the electric motor and the clearance control system, wherein the controller is configured to operate the clearance control system based upon an operational state of the electric motor.