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Temperature and flow measurements on near-freezing aviation fuels in a wing-tank modelFreezing behavior, pumpability, and temperature profiles for aviation turbine fuels were measured in a 190-liter tank chilled to simulate internal temperature gradients encountered in commercial airplane wing tanks. When the bulk of the fuel was above the specification freezing point, pumpout of the fuel removed all fuel except a layer adhering to the bottom chilled surfaces, and the unpumpable fraction depended on the fuel temperature near these surfaces. When the bulk of the fuel was at or below the freezing point, pumpout ceased when solids blocked the pump inlet, and the unpumpable fraction depended on the overall average temperature.
Document ID
19800005013
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Friedman, R. (NASA Lewis Research Center Cleveland, OH, United States)
Stockemer, F. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1980
Subject Category
Propellants And Fuels
Report/Patent Number
E-156
NASA-TM-79285
Meeting Information
Meeting: Intern. Gas Turbine Conf.
Location: New Orleans
Start Date: March 9, 1980
End Date: March 13, 1980
Sponsors: ASME
Accession Number
80N13268
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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