Experimental Investigation of an Air-Cooled Turbine Operating in a Turbojet Engine at Turbine Inlet Temperatures up to 2500 F.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1961
- Accession Number
- AD0260543
Entities
People
- Reeves P. Cochran
- Robert P. Dengler
Organizations
- National Aeronautics and Space Administration