US 12,421,892 B2
Hybrid turbine engine with selective electrical module engagement
Richard Keller, Indianapolis, IN (US); and Dwayne Bevis, Bloomington, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed on Dec. 4, 2019, as Appl. No. 16/703,376.
Prior Publication US 2021/0171212 A1, Jun. 10, 2021
Int. Cl. F02C 3/10 (2006.01); B64D 27/10 (2006.01); B64D 27/33 (2024.01); B64D 31/06 (2006.01); B64D 31/18 (2024.01); B64D 27/02 (2006.01); F01D 15/10 (2006.01)
CPC F02C 3/10 (2013.01) [B64D 27/10 (2013.01); B64D 27/33 (2024.01); B64D 31/06 (2013.01); B64D 31/18 (2024.01); B64D 27/026 (2024.01); F01D 15/10 (2013.01); F05D 2220/323 (2013.01); F05D 2260/607 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A hybrid propulsion system for use with an aircraft, the hybrid propulsion system comprising:
a gas turbine engine core including a compressor, a combustor, and a turbine;
an electric power system that includes an energy storage device, a generator connected with the energy storage device, and a motor connected with the energy storage device, the motor configured to produce rotational energy in response to receiving electric energy from the energy storage device;
at least one propulsor configured to use energy received from at least one of the gas turbine engine core and the electric power system to generate thrust for propelling the aircraft; and
a controller configured to control provision of power from the gas turbine engine core and the electric power system to the at least one propulsor to cause the at least one propulsor to generate the thrust having a force magnitude value and to adjust the provision of power from the gas turbine engine core and the electric power system in response to the controller receiving a first signal so that the at least one propulsor continues to generate the thrust having the force magnitude value,
wherein the first signal is generated in response to the controller detecting a threat to the aircraft indicative of a missile targeting heat generated and exhausted by the gas turbine engine core and the controller is configured to control the provision of energy by reducing a fuel flow to the gas turbine engine core while simultaneously increasing the provision of power from the electric power system to the at least one propulsor so that the heat generated and exhausted by the gas turbine engine core is reduced and the threat to the aircraft is mitigated.
 
15. A method of operating a hybrid propulsion system, comprising:
providing a gas turbine engine core including a compressor, a combustor, and a turbine;
providing an energy storage device;
providing at least one propulsor configured to use energy received from at least one of the gas turbine engine core and the energy storage device to generate thrust for propelling an aircraft;
generating a signal in response to detection of a threat to the hybrid propulsion system indicative of a missile targeting heat generated and exhausted by the gas turbine engine core; and
varying a provision of power between the gas turbine engine core and the energy storage device to the hybrid propulsion system by reducing a fuel flow to the gas turbine engine core and increasing power from the energy storage device to the at least one propulsor in response to the signal being generated so that the at least one propulsor achieves a predetermined thrust level and the heat generated and exhausted by the gas turbine engine core is reduced and the threat of the missile to the hybrid propulsion system is mitigated.