Preliminary results of an altitude-wind-tunnel investigation of a TG-100 gas turbine-propeller engine :IV. Compressor and turbine performance characteristics

Saari, Martin J., Wallner, Lewis E.
naca-rm-e7j20
1947


As part of an investigation of the performance and operational characteristics of the TG-100A gas turbine-propeller engine, conducted in the Cleveland Altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 degrees to 2100 degrees R. The highest compressor pressure ratio obtained was 6.15 at a corrected air flow of 23.7 pounds per second and a corrected turbine-inlet temperature of 2475 degrees R. Peak adiabatic compressor efficiencies of about 77 percent were obtained near the value of corrected air flow corresponding to a corrected engine speed of 13,000 rpm. This maximum efficiency may be somewhat low, however, because of dirt accumulations on the compressor blades. A maximum adiabatic turbine efficiency of 81.5 percent was obtained at rated engine speed for all altitudes and turbine-inlet temperatures investigated.

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