Accession Number:

AD0260543

Title:

Experimental Investigation of an Air-Cooled Turbine Operating in a Turbojet Engine at Turbine Inlet Temperatures up to 2500 F.

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-07-01

Pagination or Media Count:

1.0

Abstract:

TO BE FEASIBLE. Combustors and turbine stator blades, in addition to turbine rotor blades, were critical components at these temperature levels. An average chordwise rotor blooling, Effec tiveness, C mbustion chambers, Air cooled. An air-cooled turbine with corrugated-insert type stator and rotor blades was operated in a modified production-model engine. Results indicated that operation of turbojet engines at turbine inlet temperatures up to 2500 F appears to be feasible. Combustors and turbine stator blades, in addition to turbine rotor blades, were critical components at these temperature levels. An average chordwise rotor blade temperature of 1300 F was maintained with a coolantto-gas weight-flow ratio of about 0.022 when the average turbine inlet temperature was 2500 F and coolant inlet temperat re was about 260 F. Leading-edge tip caps on the rotor blades improved the cooling of the leading-edge region. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE