一种涡轮叶尖间隙控制技术  

A tip clearance control technology for turbine

作　　者：杨家礼[1] 涂孟罴[1] 张亿力[1] 张立章[1] 阳诚武[2] 

机构地区：[1]中国航空工业集团公司中国航空动力机械研究所,湖南株洲412002 [2]中国科学院大学,北京100190

出　　处：《航空动力学报》2014年第9期2195-2201,共7页Journal of Aerospace Power

基　　金：国家高技术研究发展计划(2008AA050502)

摘　　要：基于涡轮叶尖间隙的变化机理,设计了一种冷气自动调节机构,该机构无需其他外界动力,可根据工况的变化而自动调节冷气限流嘴的节流面积,控制涡轮外环冷气量,以控制涡轮外环的直径,从而有效控制涡轮叶尖间隙的变化趋势,维持涡轮叶尖间隙在合理范围.对3个不同工况涡轮采用与未采用涡轮叶尖间隙控制机构分别进行了计算,结果表明:采用涡轮叶尖间隙控制机构的涡轮叶尖间隙随工况变化的变化率为6.5%,未采用涡轮叶尖间隙控制机构的涡轮叶尖间隙随工况变化的变化率为20%.因此,采用该机构可以达到控制涡轮叶尖间隙变化的目的.Based on the theory of turbine tip clearance change, a structure was devel- oped to adjust the choke acreage of the cooling air flow throttle automatically without other drivers, and the cooling air of turbine casing was controlled to regulate the turbine casing diameter. So the turbine tip clearance was limited in a certain range and its trend was con- trolled effectively. Three cases were simulated for a general turbine with or without turbine tip clearance control structure. The results show that the turbine tip clearance control struc- ture can adjust the cooling air for turbine casing and the change rate of turbine tip clearance is 6.5 %, however, the change rate of the turbine tip clearance without the structure is 20 %. So the structure is beneficial to control the change of turbine tip clearance.

关 键 词：燃气轮机 叶尖间隙 限流嘴 涡轮外环 冷气量 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]