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, to simulate internal temperature gradients encountered in commercial airplane wing tanks. Two low-temperature situations were observed. Where the bulk of the fuel is above the specification freezing point, pumpout of the fuel removes all fuel except a layer adhering to the bottom chilled surfaces, and the unpumpable fraction depends on the fuel temperature near these surfaces. Where the bulk of the fuel is at or below the freezing point, pumpout ceases when solids block the pump inlet, and the unpumpable fraction depends on the overall average temperature.
Document ID
19800058023
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Friedman, R. (NASA Lewis Research Center Cleveland, Ohio, United States)
Stockemer, F. J. (Lockheed-California Co. Burbank, Calif., United States)
Date Acquired
August 10, 2013
Publication Date
March 1, 1980
Subject Category
Propellants And Fuels
Report/Patent Number
ASME PAPER 80-GT-63
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: New Orleans, LA
Start Date: March 10, 1980
End Date: March 13, 1980
Sponsors: American Society of Mechanical Engineers