航空学报 > 1993, Vol. 14 Issue (8): 424-426

TA-6发动机的引气特性

王琴芳, 马申义   

  1. 南京航空航天大学航空动力系,南京 210016
  • 收稿日期:1992-03-17 修回日期:1992-09-05 出版日期:1993-08-25 发布日期:1993-08-25

BLEED CHARACTERISTICS OF TA-6 ENGINE

Wang Qin-fang, Ma Shen-yi   

  1. Aero. Power Dept. Nanjing University of Aeronautics and Astronautics, Nanjing, 210016
  • Received:1992-03-17 Revised:1992-09-05 Online:1993-08-25 Published:1993-08-25

摘要: 在TA-6发动机的压气机出口处引气,得到了发动机转速不变条件件下压气机增压比、引气阀压力损失系数、引气管内气流总压和引气气流温度与引气量之间的关系。研究表明,相对引气量在9~22%范围内变化时,TA-6发动机流量几乎不变,压气机增压比变化仅5%,引气压力为1.27×10~2~2.45×10~5Pa,引气温度约473K。所得结果可为燃气涡轮装置引气设计提供参考。

关键词: 引气, 发动机, 燃气涡轮

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