Effect of blade-tip crossover passages on natural-convection water-cooling of gas-turbine blades /
by Charles F. Zalabak and Arthur N. Curren.

Description

Main Author

Zalabak, Charles F.

Related Names

Curren, Arthur N.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington [D.C.] : National Advisory Committee for Aeronautics, [1956]

Subjects

Heat > Heat / Convection, Natural.
Heat > Heat / Transmission.
Aircraft gas-turbines > Aircraft gas-turbines / Blades > Aircraft gas-turbines / Blades / Cooling.

Summary

A water-cooled turbine was fabricated and tested to determine the effect of a connecting passage at the turbine rotor blade tip between a radial coolant passage 0.10 inch in diameter (length-diameter ratio = 25.5) and radial coolant passages in the legnth-diameter range of 5.1 to 20.4. Coolant flow through the connecting passage is induced by free-convection forces in the radial passages.

Note

"Declassified October 31, 1958."
"March 2, 1956."
Cover title.

Physical Description

28 p. : ill. ; 27 cm.

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