高压涡轮主动间隙热控制系统机匣传热特性试验

王鹏飞; 曾军; 李天禄; 郭文; 张靖周; 杨上峰

doi:10.13224/j.cnki.jasp.2018.01.020

高压涡轮主动间隙热控制系统机匣传热特性试验

doi: 10.13224/j.cnki.jasp.2018.01.020

1.
南京航空航天大学能源与动力学院,南京 210016；中国航空发动机集团有限公司四川燃气涡轮研究院,成都 610500
2.
中国航空发动机集团有限公司四川燃气涡轮研究院,成都 610500
3.
南京航空航天大学能源与动力学院,南京 210016

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出版历程
- 收稿日期: 2016-10-15
- 刊出日期: 2018-01-28

Test on heat transfer characteristics of high pressure turbine casing with active clearance control system

摘要

摘要: 设计了实际尺寸高压涡轮（HPT）主动间隙控制（ACC）系统机匣组件试验件,模拟ACC系统在高温、高压条件下的工作状态,研究了HPT机匣的温度分布规律,以及机匣温度随冷气雷诺数的响应特性,验证了供气总管及冲击冷却管的流动特性。结果显示：供气总管压力分布均匀,冲击冷却管从进气端至封闭末端的沿程压力逐渐升高,但管内压力随冲击冷却管开孔面积比的增大而接近一致；当ACC系统不工作和工作时,机匣周向单点温度与平均温度最大相对偏差分别为48%和58%；而在ACC系统工作时,随冷气雷诺数的变大,涡轮外机匣温度能显著降低,试验工况中,机匣各冷却部位平均温度的降幅可达16%～37%,达到预期效果。基于试验测试数据,验证并改进了HPT机匣组件换热分析模型,该模型具有较高精度和良好适用性。
- 涡轮机匣 /
- 主动间隙控制(ACC) /
- 压力分布 /
- 传热 /
- 温度分布
Abstract: Casing test specimen for high pressure turbine（HPT）active clearance control（ACC) system of trim size was designed. Operation of active clearance control system was simulated under high temperature and high pressure to verify the flow characteristics of cooling collector and impingement cooling pipes, and investigate the temperature distribution rules of HPT casing as well as responsive characteristics of casing temperature to cooling airflow. Results showed that the pressure distribution of air supply manifold was very even; for impingement cooling pipes, the pressure rose gradually from inlet to the end, but the pressure became consistent as the area of orifice on the pipe increased; the maximum relative deviation of circumferential temperature distribution of casing were 48% and 58%, for nonoperating and operating ACC system; when the ACC system was working, the temperature for turbine outer casing obviously decreased as cooling airflow increased; during the test, the average temperature for cooled parts on the casing decreased as much as 16%－37% up to expectation. Based on the test data, heat transfer model of HPT casing was validated and modified to be more precise and applicable.
- turbine casing /
- active clearance control（ACC） /
- pressure distribution /
- heat transfer /
- temperature distribution

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参考文献(18)

[1]	LATTIME S B,STEINETZ B M.Highpressureturbine clearance control system:current practices and future directions［J］.Journal of Propulsion and Power,2004,20(2):302-311.
[2]	曾军,王鹏飞.民用航空发动机涡轮叶尖间隙主动控制技术分析［J］.航空科学技术,2012,134（2）:1-6.ZENG Jun,WANG Pengfei.Analysis on turbine active clearance control technology of civil aircraft engine［J］.Journal of Aeronautical Science and Technology,2012,134（2）:1-6.(in Chinese)
[3]	RICH S E,FASCHING W A.CF6 jet engine performance improvement:high pressure turbine active clearance control［R］.NASA CR-165556,1982.
[4]	GAFFIN W O.JT9D70/59 improved high pressure turbine active clearance control system［R］.NASA CR-159661,1979.
[5]	JAMBUNATHAN K,LAI E,MOSS M A,et al.A review of heat transfer data for single circular jet impingement［J］.International Journal of Heat and Fluid Flow,1992,13(2):106-115.
[6]	许全宏,林宇震,刘高恩.封闭空间内单孔冲击局部换热特性研究［J］.航空动力学报,2002,17（3）:341-343.XU Quanhong,LIN Yuzhen,LIU Gaoen.Investigation of impingemrnt heat transfer of single hole in a limited space［J］.Journal of Aerospace Power,2002,17（3）:341-343.(in Chinese)
[7]	GOLDSTEIN R J,BEHBAHANI A I.Impingement of a circular jet with and without crossflow［J］.International Journal of Heat Transfer,1982,25(9):1377-1382.
[8]	GOLDSTEIN R J,FRANEHETT M E.Heat transfer from a flat surface to an oblique impinging jet［J］.Journal of Heat Transfer,1988,110(2):84-90.
[9]	CHAMBERS A C,GILLESPIE R H.The effect of initial crossflow on the cooling performance of a narrow impingement channel［J］.Journal of Heat Transfer,2005,127(4):358-365.
[10]	张泽远,张靖周,杨卫华.半封闭通道射流冲击换热特性的实验［J］.航空动力学报,2006,21（4）:626-630.ZHANG Zeyuan,ZHANG Jingzhou,YANG Weihua.Convective heat transfer of jet impingement inside semiconfined channel［J］.Journal of Aerospace Power,2006,21（4）:626-630.(in Chinese)
[11]	FLORSCHUETZ L W,IAODA Y.Flow distribution and discharge coefficient for jet array impingement with initial crossflow［J］.Journal of Engineering for Power,1983,105(3):296-303.
[12]	FLORSCHUETZ L W,METZGER D E,SU C C.Heat transfer characteristics for jet array impingement with initial cross flow［R］.ASME Paper 83-GT-28,1983.
[13]	单文娟,毛军逵,李毅,等.斜向冲击强化换热特性试验［J］.航空动力学报,2013,28（3）:701-708.SHAN Wenjuan,MAO Junkui,LIYi,et al.Experimental on heat transfer characteristics with inclined impingement［J］.Journal of Aerospace Power,2013,28（3）:701-708.(in Chinese)
[14]	张井山,毛军逵,李毅,等.高压涡轮主动间隙控制机匣内部换热特性试验［J］.航空动力学报,2014,29（2）:299-304.ZHANG Jingshan,MAO Junkui,LI Yi,et al.Experimental on heat transfer characteristics inside the casing of high pressure turbine with active clearance control［J］.Journal of Aerospace Power,2014,29（2）:299-304.(in Chinese)
[15]	LIU Fangyuan,MAO Junkui.Experimental investigations about heat transfer characteristics of irregular impingement jet arrays in typical active clearance control system［R］.AIAA2015-2406,2015.
[16]	姜远刚,毛军逵,李毅,等.间隙主动控制系统中冷却空气管换热特性实验研究［J］.推进技术,2014,35（3）:365-371.JIANG Yuangang,MAO Junkui,LI Yi,et al.Experimental studies on heat transfer characteristics in air cooling pipe of turbine tip clearance control system［J］.Journal of Propulsion Technology,2014,35（3）:365-371.(in Chinese)
[17]	杜小琴,朱惠人,张宗卫,等.涡轮机匣壁面换热特性的数值计算［J］.航空工程进展,2010,1（4）：384-389.DU Xiaoqin,ZHU Huiren,ZHANG Zongwei,et al.Numerical study on the heat transfer characteristics of turbine casing［J］.Advances in Aeronautical Science and Engineering,2010,1（4）：384-389.（in Chinese）
[18]	张书华,张丽,朱惠人,等.涡轮机匣换热试验［J］.航空动力学报,2011,26（5）:1011-1016.ZHANG Shuhua,ZHANG Li,ZHU Huiren,et al.Experimental investigation of heat transfer characteristic in turbine casing［J］.Journal of Aerospace Power,2011,26（5）:1011-1016.(in Chinese)