Abstract: This paper presents the results of bleed characteristics of TA-6 gas turbine engine, which include the relations of pressure ratio of the compressor, presuure loss coefficient of the controlling valve, total pressure and temperature of the bleed flow with the quantity of bleed air at constant engine speed. The study shows that in a relative bleed air range of 9- 20% the air flow of the engine is almost constant, the variation of pressure ratio of the compressor is less than 5%, and the pressure and temperature of the bleed air are 1.27× 105-2.45×105Pa and about 473K respectively.

Key words: bleed air, engine, gas turbine