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Heat pipe radiation cooling of advanced hypersonic propulsion system componentsHeat transfer, heat pipe, and system studies were performed to assess the newly proposed heat pipe radiation cooling (HPRC) concept. With an HPRC system, heat is removed from the ramburner and nozzle of a hypersonic aircraft engine by a surrounding, high-temperature, heat pipe nacelle structure, transported to nearby external surfaces, and rejected to the environment by thermal radiation. With HPRC, the Mach number range available for using hydrocarbon fuels for aircraft operation extends into the Mach 4 to Mach 6 range, up from the current limit of about Mach 4. Heat transfer studies using a newly developed HPRC computer code determine cooling system and ramburner and nozzle temperatures, heat loads, and weights for a representative combined-cycle engine cruising at Mach 5 at 80,000 ft altitude. Heat pipe heat transport calculations, using the Los Alamos code HTPIPE, reveal that adequate heat trasport capability is available using molybdenum-lithium heat pipe technology. Results show that the HPRC system radiator area is limited in size to the ramburner-nozzle region of the engine nacelle; reasonable system weights are expected; hot section temperatures are consistent with advanced structural materials development goals; and system impact on engine performance is minimal.
Document ID
19910057136
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Martin, R. A.
(Los Alamos National Lab. NM, United States)
Keddy, M.
(Los Alamos National Lab. NM, United States)
Merrigan, M. A.
(Los Alamos National Laboratory NM, United States)
Silverstein, C. C.
(CCS Associates Bethel Park, PA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 91-2358
Accession Number
91A41759
Funding Number(s)
CONTRACT_GRANT: NASA ORDER C-30002-M
Distribution Limits
Public
Copyright
Other

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