Heat pipe cooling for scramjet engines. Final report
Liquid metal heat pipe cooling systems have been investigated for the combustor liner and engine inlet leading edges of scramjet engines for a missile application. The combustor liner is cooled by a lithium-TZM molybdenum annular heat pipe, which incorporates a separate lithium reservoir. Heat is initially absorbed by the sensible thermal capacity of the heat pipe and liner, and subsequently by the vaporization and discharge of lithium to the atmosphere. The combustor liner temperature is maintained at 3400 F or less during steady-state cruise. The engine inlet leading edge is fabricated as a sodium-superalloy heat pipe. Cooling is accomplished by radiation of heat from the aft surface of the leading edge to the atmosphere. The leading edge temperature is limited to 1700 F or less. It is concluded that heat pipe cooling is a viable method for limiting scramjet combustor liner and engine inlet temperatures to levels at which structural integrity is greatly enhanced.
- Research Organization:
- CCS Associates, Bethel Park, PA (USA)
- OSTI ID:
- 6158551
- Report Number(s):
- N-89-15351; NASA-CR-4036; NAS-1.26:4036; CCS-115
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
COMBUSTION CHAMBERS
COOLING
HEAT PIPES
RAMJET ENGINES
LINERS
LITHIUM
MOLYBDENUM BASE ALLOYS
PROGRESS REPORT
THERMAL RADIATION
TITANIUM ALLOYS
ALKALI METALS
ALLOYS
DOCUMENT TYPES
ELECTROMAGNETIC RADIATION
ELEMENTS
ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
METALS
MOLYBDENUM ALLOYS
RADIATIONS
420400* - Engineering- Heat Transfer & Fluid Flow
421000 - Engineering- Combustion Systems