Thermal management system for an aircraft
AssigneeUnited Technologies Corporation
InventorsDaniel Sabatino, Louis J. Spadaccini, Scott Kaslusky
Life of this patent
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Abstract
A fuel based thermal management system includes a fuel stabilization system which permits the fuel to exceed the traditional coking temperatures. High temperature components are arranged along the fuel flow path such that even at the higher operating temperatures the fuel operates as a heat sink to transfer heat from high temperature components to the fuel. An optimal high temperature ester-based oil permits an oil-loop to exceed current oil temperature limits and achieve a high temperature to permit efficient rejection of heat to the fuel late in the fuel flow path.
Claims22
A method of thermal management within a vehicle having a gas turbine engine comprising the steps of:
- (1) deoxygenating a fuel onboard the vehicle to provide a deoxygenated fuel;
- (2) communicating the fuel through a first liquid-to-liquid heat exchanger system operable at a first maximum temperature;
- (3) communicating the deoxygenated fuel through a second liquid-to-liquid heat exchanger system operable at a second maximum temperature, said second maximum temperature greater than said first maximum temperature;
- communicating the deoxygenated fuel and an oil through the second liquid-to-liquid heat exchanger, the oil effective above approximately 325 degrees Fahrenheit and permitting the deoxygenated fuel to exceed 325 degrees Fahrenheit.
A method of thermal management within an aircraft fuel system comprising the steps of:
- (1) communicating fuel from aircraft fuel tank;
- (2) deoxygenating the fuel on-board the aircraft to provide a deoxygenated fuel;
- (3) communicating the fuel through a first liquid-to-liquid heat exchanger system in communication with a first oil loop operable at a first maximum temperature;
- (4) communicating the deoxygenated fuel through a second liquid-to-liquid heat exchanger system in communication with a second oil loop operable at a second maximum temperature after said steps (2) and (3), said second maximum temperature greater than said first maximum temperature;
- communicating the deoxygenated fuel and an oil effective above approximately 325 degrees Fahrenheit in the second oil loop through the second liquid-to-liquid heat exchanger;
- and permitting the deoxygenated fuel to exceed a temperature of approximately 325 degrees Fahrenheit.
A method of thermal management within an aircraft fuel system comprising the steps of:
- (1) deoxygenating the fuel on-board the aircraft to provide a deoxygenated fuel;
- (2) communicating the fuel through a first liquid-to-liquid heat exchanger system in communication with a first oil loop operable at a temperature below approximately 325 degrees Fahrenheit;
- and
- (3) communicating the deoxygenated fuel through a second liquid-to-liquid heat exchanger system in communication with a second oil loop operable at a temperature above approximately 325 degrees Fahrenheit after said steps (1) and (2) and permitting the deoxygenated fuel to exceed a temperature of approximately 325 degrees Fahrenheit.
Dependencies are inferred from the claim text.