公开(公告)号：US11480112B2

公开(公告)日：2022-10-25

申请号：US16892690

申请日：2020-06-04

Applicant: ROLLS-ROYCE plc

Inventor： Paul D Whatley

IPC: F02C9/48

Abstract: A gas turbine engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; a combustion system comprising a fuel metering unit; and an engine controller configured to, in response to a change of a throttle lever angle setting indicative of an acceleration event, increase fuel flow to the combustion system by the fuel metering unit, and to operate the first electric machine in a motor mode to increase the HP spool rotational speed and engine core mass flow.