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National Advisory Committee for Aeronautics, Research Memorandum - Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine - IV - Compressor and Turbine Performance Characteristics

As part of an investigation of the performance and operational
characteristics of the TG-lOOA gas turbine-propeller engine, con-
ducted. in the Cleveland altitude wind tunnel, the performance char—
acteristics of the compressor and the turbine were obtained. The
data presented were obtained at a compressor-inlet ram-pressure
ratio of 1.00 for altitudes from 5000 to 55,000 feet, engine speeds
from 8080 to 13,000 rpm, and turbine-inlet temperatures from 1400°
to 2100 R.

The highest compressor pressure ratio obtained was 6.15 at a
corrected air flow of 25.7 pounds per second and a corrected
turbine-inlet temperature of 24750 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
15,000 rpm. This mafinmm 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 tecmperatures investigated.

An investigation of the performance and operational charac-
teristics of a TG-lOOA gas turbine-propeller engine has been
conducted in the Cleveland altitude wind tunnel at the request of
the Army'Air Forces, Air Materiel Command. Engine performance
characteristics, windmilling characteristics, and pressure and tem-
perature distributions throughout the engine are presented in ref-
erences l, 2, and 5, respectively.

The performance of the compressor and the turbine are of
particular significance because very little altitude data have
been obtained on these component parts in a gas turbine—propeller
engine. Data were obtained at a compressor-inlet ram-pressure
ratio of 1.00 at altitudes from 5000 to 55,000 feet, engine speeds
from 8000 to 15,000 rpm, and turbine-inlet temperatures from
14000 to 21000 R. The compressor performance is presented as a
function of corrected engine air flow and corrected turbine-inlet
temperature. The turbine performance is presented as a function
of corrected turbine speed and corrected turbine-inlet temperature.