Publication Date:
2019-07-13
Description:
The results of an analytical study to determine the effect of changes in the amount, velocity, injection location, injection angle, and temperature of coolant flow on blade row performance are presented. The results show 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. 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. To further test the validity of the method, more experimental data is needed, particularly at different coolant temperature ratios.
Keywords:
THERMODYNAMICS AND COMBUSTION
Type:
NASA-TM-X-67960
,
E-6667
,
Aerospace Meeting; Jan 17, 1972 - Jan 19, 1972; San Diego, CA; United States
Format:
application/pdf
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