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Thermodynamic performance testing of the orbiter flash evaporator systemSystem level testing of the space shuttle orbiter's development flash evaporator system (FES) was performed in a thermal vacuum chamber capable of simulating ambient ascent, orbital, and entry temperature and pressure profiles. The test article included the evaporator assembly, high load and topping exhaust duct and nozzle assemblies, and feedwater supply assembly. Steady state and transient heat load, water pressure/temperature and ambient pressure/temperature profiles were imposed by especially designed supporting test hardware. Testing in 1978 verified evaporator and duct heater thermal design, determined FES performance boundaries, and assessed topping evaporator plume characteristics. Testing in 1979 combined the FES with the other systems in the orbiter active thermal control subsystem (ATCS). The FES met or exceeded all nominal and contingency performance requirements during operation with the integrated ATCS. During both tests stability problems were encountered during steady state operations which resulted in subsequent design changes to the water spray nozzle and valve plate assemblies.
Document ID
19810005631
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jaax, J. R.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Melgares, M. A.
(United Technologies Corp. Houston, Tex., United States)
Frahm, J. P.
(Rockwell International Houston, Tex., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Publication Information
Publication: The 11th Space Simulation Conf.
Subject Category
Space Transportation
Accession Number
81N14143
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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