US 12,385,439 B2
Aircraft with thermal energy storage system
Douglas J. Snyder, Carmel, 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. 21, 2023, as Appl. No. 18/393,008.
Application 18/393,008 is a continuation of application No. 17/491,470, filed on Sep. 30, 2021, abandoned.
Claims priority of provisional application 63/086,804, filed on Oct. 2, 2020.
Prior Publication US 2024/0124150 A1, Apr. 18, 2024
Int. Cl. F02K 3/115 (2006.01); F02C 7/12 (2006.01); F02C 7/224 (2006.01); F02K 7/10 (2006.01)
CPC F02K 3/115 (2013.01) [F02C 7/12 (2013.01); F02C 7/224 (2013.01); F02K 7/10 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01); F05D 2270/303 (2013.01); F05D 2270/3062 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A thermal energy system for use with an aircraft, the thermal energy system comprising:
a heat source,
a cooling loop having a fluid conduit and a pump configured to move a fluid through the fluid conduit to transfer heat from the heat source to the fluid to cool the heat source,
a cooler that includes a duct configured to conduct a flow of air through the duct and an air-stream heat exchanger located in the duct and in thermal communication with the fluid in the cooling loop to transfer heat between the cooling loop and the flow of air conducted through the duct,
a thermal-storage fuel system that includes a TMS fuel tank configured to store a first fuel therein at a first temperature, an aircraft fuel tank independent of the TMS fuel tank configured to store a second fuel at a second temperature that is different from the first temperature of the first fuel in the TMS fuel tank, and a fuel-tank heat exchanger in thermal communication with the fluid in the cooling loop and configured to transfer heat between the fluid in the cooling loop and the first fuel from the TMS fuel tank,
an engine-fuel unit configured to receive the second fuel from the aircraft fuel tank and deliver the second fuel from the aircraft fuel tank to an engine, and
a controller connected with one or more valves, a valve system, and one or more sensors;
wherein the engine-fuel unit includes the valve system and an engine-fuel heat exchanger, the valve system is in fluid communication with the aircraft fuel tank, the engine-fuel heat exchanger is in thermal communication with the valve system and the cooling loop and is configured to transfer heat between the fluid in the cooling loop and the second fuel in the engine-fuel unit delivered from the aircraft fuel tank,
wherein the controller is configured to vary a flow of the second fuel from the aircraft fuel tank through the engine-fuel heat exchanger via the valve system to deliver the second fuel from the aircraft fuel tank to the engine at a third temperature that is less than or equal to an engine-fuel unit predetermined threshold temperature,
wherein the controller is configured to vary a flow of the fluid in the cooling loop through the fuel-tank heat exchanger via the one or more valves to heat the first temperature of the first fuel in the TMS fuel tank to a first fuel tank predetermined threshold temperature which is greater than the engine-fuel unit predetermined threshold temperature.