1+1/2对转涡轮模型试验件气动设计  

AERODYNAMIC DESIGN OF THE VANELESS COUNTER-ROTATING TURBINE

作　　者：季路成[1] 陈江[2] 项林[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080 [2]北京全三维动力公司,北京100080

出　　处：《工程热物理学报》2003年第6期943-946,共4页Journal of Engineering Thermophysics

基　　金：中国科学院知识创新工程项目(KGCX2-301);国家自然科学基金(No.59906012);国家重点基础研究发展规划项目(No.G1999022305)

摘　　要：本文在小函道比涡轮风扇发动机范围内,由高、低压轴功率匹配及先前研究结果确定了可行的1+1/2对转涡轮设计目标,进一步对模型试验件展开了气动设计和叶片造型。尽管设计未在实现目标方面进一步努力,但结合先前工作,建立了实用1+1/2对转涡轮设计的理论和技术基础,揭示出设计中存在的困难,指明了解决问题的方向和未来用于继续提升1+1/2对转涡轮的关键技术。The aerodynamic design of a test model of the vaneless counter-rotating turbine is presented. The object of the design is firstly determined by matching the powers needed to drive the high and the low pressure shafts in a turbofan engine with low by-pass ratio. Then the aerodynamic design and the blade generation are proceeded. Though the design has not been optimized, the theoretical basis of a practical vaneless counter-rotating turbine is founded, also the difficulties involved in the design process are revealed, and the ways to resolve the difficulties are designated. Finally, the key techniques to further more improve the performance are indicated.

关 键 词：无导叶对转涡轮 涡轮设计 超音出口涡轮叶栅 等效收扩叶型 三维造型 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]