A cooling system and insulation concept for a Mach 5 cruise aircraft, using non-cryogenic fuel is presented. Catalytic endothermic reaction of petroleum fuel is used as the heat sink for engine cooling. A secondary closed-loop coolant circuit removes heat from the engine and transfers this heat to the catalytic reactor. Insulation on the engine flow path surfaces reduces the cooling requirements. A high temperature insulation system, which is capable of a surface temperature of 4000 F, is used for the combustor and nozzle. A complete closed-loop cooling system design is shown in detail. Main features of this system include a fuel preheater, a catalytic fuel reactor and engine wall cooling panels. A silicone-based liquid polymer, designed for extended use at 750 F, is used as the coolant. The preheater and reactor design are based on the results of recent experimental work sponsored by the USAF. The cooling panels are designed using a thermal fluid analysis computer program which was originally developed for the National Aero-Space Plane (NASP). Major components are analyzed structurally as well as thermally and weights are presented.
Cooling system and insulation concept for a Mach 5 turbo-ramjet aircraft
Kühlsystem und Isolationskonzept für ein Mach 5 Ramjet-Flugzeug
Joint Army-Navy-NASA-Air Force (JANNAF) Propulsion Meeting, 1990 ; 1 , Sep ; 191-201
1991
11 Seiten, 11 Bilder, 5 Tabellen, 11 Quellen
Conference paper
English
COOLING SYSTEM AND INSULATION CONCEPT FOR A MACH 5 TURBO-RAMJET AIRCRAFT
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