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US 5,149,018 AGranted
Cooling system for a hypersonic aircraft
AssigneeThe Boeing Company
InventorLarry T. Clark
Life of this patent
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Abstract
A cooling system for a hypersonic aircraft is disclosed which enables hypersonic flight using non-cryogenic fuels. The cooling system positions a primary heat exchanger at an external location on the aircraft which remains relatively cool during hypersonic flight. A working fluid is passed through the primary heat exchanger to the hot parts of a supersonic combustion ram jet engine.
Claims10
A cooling system for a hypersonic aircraft using non-cryogenic fuel and operable at speeds above Mach 3, comprising:
- an aircraft body having a relatively low temperature exterior portion whose surface temperature does not exceed approximately 1000.degree. Fahrenheit during flight at speeds of up to Mach 7;
- a ram-type, non-cryogenic engine for propelling the aircraft;
- an engine heat exchanger having a first heat exchange surface in contact with the engine and a second heat exchange surface exposed to a flow of a liquid metal;
- an aircraft heat exchanger manufactured of a material capable of operating at temperatures of up to only approximately 1800.degree. Fahrenheit, the aircraft heat exchanger being positioned in thermal contact with the relatively low temperature exterior portion of the aircraft body;
- and
- circulation means for circulating the liquid metal through the engine heat exchanger to the aircraft heat exchanger so that heat from the engine is dissipated by the aircraft exchanger to the surrounding atmosphere.
3 more elements
A method for cooling a ram-type jet engine using non-cryogenic fuel in a hypersonic aircraft, comprising the steps of:
- circulating a liquid metal working fluid through an engine heat exchanger having a first heat exchange surface in contact with said ram-type jet engine and a second heat exchange surface exposed to a flow of said liquid metal so that heat is transferred from the engine to the working fluid;
- positioning an aircraft heat exchanger in thermal contact with an external portion of the aircraft having a maximum temperature due to air friction during flight at speeds up to approximately Mach 7 of no more than approximately 1000.degree. F.;
- and
- circulating the working fluid through the engine heat to the aircraft heat exchanger so that heat from said engine is dissipated by said aircraft heat exchanger to the surrounding atmosphere.
1 more element
Dependencies are inferred from the claim text.