1+1对转涡轮气动设计技术研究  

Aerodynamics design of two-stage counter-rotating turbine

作　　者：付超[1] 邹正平[1] 刘火星[1] 李维[2] 曾军[3] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京100191 [2]中国航空动力机械研究所,湖南株洲412002 [3]中国燃气涡轮研究院,四川成都610500

出　　处：《空气动力学学报》2012年第3期299-306,共8页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(50776003);国防重点实验室基金项目(9140C4103100903)

摘　　要：分析了对转涡轮方案的影响因素,推导了带导叶对转涡轮基元级速度三角形参数与涡轮效率和出功比的关系,进行了速度三角形的分析,得到了带导叶对转涡轮速度三角形的设计规律。为验证此规律,选取了基元级基本参数,在此基础上,进行了考虑冷却的1+1对转涡轮气动方案的设计;并利用三维数值模拟手段对所设计的气动方案进行了验证。结果表明,所完成的涡轮气动方案能够满足设计要求,且选取的速度三角形基本参数与数值模拟结果较为接近。The factors which had impact on the forms of counter-rotating turbine were analyzed in detail based on the characteristics of counter-rotating turbine. By analyzing the counter-rotating turbine velocity triangles and how the efficiency and work ratio varied by the parameters of the velocity triangles, the regular of how to select the velocity triangles of counter-rotating turbine was developed. A new counter-rotating turbine which had premeditated the coolant was designed. The results of 3D viscous numerical simulation show that the turbine meets the design requirements with a high efficiency, and the regular was tested an verified.

关 键 词：速度三角形 对转涡轮 气动设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]