Publication Date:
2019-07-13
Description:
Demonstration that the change in output of a cooled turbine blade row relative to the specific output of the uncooled blade row can be positive, negative, or zero, depending on the velocity, injection location, injection angle, and temperature of the coolant. Comparisons between the analytical results and experimental results for four different cases of coolant discharge, all at a coolant temperature ratio of unity, show good agreement for three cases, and rather poor agreement for the other.
Keywords:
PROPULSION SYSTEMS
Type:
AIAA PAPER 72-12
,
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 17, 1972 - Jan 19, 1972; San Diego, CA
Format:
text
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