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Transpiration cooling in the locality of a transverse fuel jet for supersonic combustorsThe objective of the current work was to determine the feasibility of transpiration cooling for the relief of the local heating rates in the region of a sonic, perpendicular, fuel jet of gaseous hydrogen. Experiments were conducted to determine the interaction between the cooling required and flameholding limits of a transverse jet in a high-enthalpy, Mach 3 flow in both open-jet and direct-connect test mode. Pulsed shadowgraphs were used to illustrate the flow field. Infrared thermal images indicated the surface temperatures, and the OH(-) emission of the flame was used to visualize the limits of combustion. Wall, static presures indicated the location of the combustion within the duct and were used to calculate the combustion efficiency. The results from both series of tests at facility total temperatures of 1700 K and 2000 K are presented.
Document ID
19900055723
Document Type
Conference Paper
Authors
Northam, G. Burton (NASA Langley Research Center Hampton, VA, United States)
Capriotti, Diego P. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Byington, Carl S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number
AIAA PAPER 90-2341
Distribution Limits
Public
Copyright
Other