Patent US5149018A successfully refreshed from Google Patents.
US5149018A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Cooling system for a hypersonic aircraft
Assignee: Boeing Co
•
Filing: 1990-05-17
•
Granted: 1992-09-22
•
Expires: 2010-05-17
Abstract
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.
Inventors
- 👤 Larry T. Clark
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 07:15
CPC Classifications
B; B64; B64C; B64C1/00; B64C1/38; Y; Y10; Y10S; Y10S165/00; Y10S165/908; Y10S60/00; Y10S60/912
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
157 words
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° 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° 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.
Claim 2
Dependent Claim
157 words
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° 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° 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.
Claim 3
Dependent Claim
45 words
The cooling system of claim 1, including a non-cryogenic fuel tank for non-cryogenic fuel, a fuel heat exchanger in the fuel tank fluidly connected in parallel with the engine and aircraft heat exchangers for using the heat capacity of the fuel to cool the engine.
Claim 4
Dependent Claim
53 words
The cooling system of claim 1 wherein the aircraft heat exchanger has a first panel having a plurality of grooves therein and a second panel fixedly attached to the first panel by diffusion bonding so that the grooves form channels which are fluidly connected to the engine heat exchanger and the circulation means.
Claim 5
Dependent Claim
27 words
The cooling system of claim 3 wherein the first panel has a thickness of approximately 0.050" and wherein the second panel has a thickness of approximately 0.020".
Claim 6
Dependent Claim
16 words
The cooling system of claim 1 wherein the liquid metal working fluid is a sodium-potassium alloy.
Claim 7
Dependent Claim
34 words
The cooling system of claim 1 wherein the circulation means has a flow rate of approximately nine lb/sec and wherein the aircraft heat exchanger has a surface area of approximately 200 ft 2 .
Claim 8
Independent Claim
139 words
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° 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.
Claim 9
Independent Claim
139 words
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° 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.
Claim 10
Dependent Claim
52 words
The method of claim 7, including the step of circulating at least some of the working fluid through a second heat exchanger which is in contact with the non-cryogenic fuel stored in the aircraft so that at least some of the heat energy generated in the engine is absorbed by the fuel.
Claim 11
Dependent Claim
24 words
The cooling system of claim 1 wherein said relatively low temperature exterior portion is an upper surface of a portion of said aircraft body.
Claim 12
Dependent Claim
51 words
The cooling system of claim 9 wherein said aircraft body includes a pair of wings having respective leading edges, and wherein said aircraft heat exchanger is in thermal contact with an upper surface of at least one of said wings at a location aft of the leading edge of said wing.
References Cited (Backward Citations)
US2133514A
Cited
US2291607A
Cited
US2330632A
Cited
US3550678A
Cited
US4273304A
Cited
US4505124A
Cited
US4804571A
Cited
US4687048A
Cited
US4776536A
Cited
US4986495A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-09-22 | 1996-03-23 | 1996-09-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-09-22 | 2000-03-23 | 2000-09-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-09-22 | 2004-03-23 | 2004-09-22 | $7700.00 | Window Closed / Lapsed |