Patent ID: 11867131
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A system comprising:
a first gas turbine engine of an aircraft, the first gas turbine engine comprising a first low speed spool, a first high speed spool, and a first combustor;
a first high spool motor configured to augment rotational power of the first high speed spool;
a second gas turbine engine of the aircraft, the second gas turbine engine comprising a second low speed spool, a second high speed spool, and a second combustor;
a second high spool motor configured to augment rotational power of the second high speed spool; and
a controller to:
determine a thrust requirement to satisfy a desired glide slope;
determine whether thrust matching between the first gas turbine engine and the second gas turbine engine can be maintained while operating the first gas turbine engine in a fuel-burning mode and operating the second gas turbine engine in an electrically powered mode; and
responsive to determining that thrust matching cannot be maintained, command fuel flow to the second combustor of the second gas turbine engine to cause the second gas turbine engine to operate in the fuel-burning mode.