上面级发动机小功率冲击式涡轮性能试验研究
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摘要
设计了一种适用于小功率冲击式涡轮性能试验方案,该方案由燃气路和水路组成,通过酒精发生器获取高温高压空气驱动涡轮转动,泵为水介质增压作为负载进行涡轮性能试验,保证了试验涡轮状态与真实产品状态的一致性。以涡轮相似换算准则为基础在试验系统能力允许的范围内设计试验工况。本涡轮性能试验方案利用泵水力性能核算涡轮输出功,根据实测的涡轮压力、温度等参数,最终获得涡轮效率随涡轮速比变化的性能曲线。通过设计考台试验件及考验方法,确保试验系统参数测量的稳定可靠。经某上面级发动机涡轮泵作为试验对象验证,采用该试验方案可以获取涡轮效率。同时3件试验涡轮转子的性能试验结果对比表明该上面级发动机涡轮转子性能一致。
A test scheme suitable for performance test of the low-power impact turbo was designed.This scheme is composed of gas and water paths,by which high pressure and high temperature gas is obtained to drive the turbo by an air/alcohol generator,and a pump increases the water pressure as load for the turbo performance test to ensure that the state of the turbo under test is in conformity with the state of the actual turbopump products.The operating condition of test is designed in the allowable range of the testing system capacity based on the turbo similarity conversion criterion.The output work of the turbo can be calculated with the pump hydraulic experimental data,and the correlation of the turbo efficiency arid the turbo speed ratio can be obtained according to the measured turbo pressure,temperature and other parameters.The calibration test pieces,and methods are designed to ensure the stability and the reliability of test parameters.Taking the turbopump of a certain type of upper stage liquid rocket engine as the test object,the turbo efficiency is got with this test scheme.The test results of the three testing turbo rotors also show that the performances of the turbo rotors are consistent.
A test scheme suitable for performance test of the low-power impact turbo was designed.This scheme is composed of gas and water paths,by which high pressure and high temperature gas is obtained to drive the turbo by an air/alcohol generator,and a pump increases the water pressure as load for the turbo performance test to ensure that the state of the turbo under test is in conformity with the state of the actual turbopump products.The operating condition of test is designed in the allowable range of the testing system capacity based on the turbo similarity conversion criterion.The output work of the turbo can be calculated with the pump hydraulic experimental data,and the correlation of the turbo efficiency arid the turbo speed ratio can be obtained according to the measured turbo pressure,temperature and other parameters.The calibration test pieces,and methods are designed to ensure the stability and the reliability of test parameters.Taking the turbopump of a certain type of upper stage liquid rocket engine as the test object,the turbo efficiency is got with this test scheme.The test results of the three testing turbo rotors also show that the performances of the turbo rotors are consistent.
引文
[1]任汉芬,夏德新,译.液体火箭发动机涡轮泵装置原理与计算[M].北京:航天工业总公司第十一研究所(京),1999.
[2]张贵田,高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[3]于龙淮,周德山,译.航空航天工程中的小流量泵[M].北京:宇航出版社,1993.
[4]Jouini D B M,SJOLANDER S A.Midspan flow-field measurements for two transonic linear turbine cascade at off-design conditions[J].ASME journal of turbomach,2002,124:176-186.
[5]逯婉若,黄智勇.涡轮性能实验研究[J].火箭推进,2004,30(6):11-14.LU Wanruo,HUANG Zhiyong.Experimental investagation of turbine performance[J].Journal of rocket pro pulsion,2004,30(6):11-14.
[6]赵哲,刘宝琴.燃气涡轮性能试验台的控制因素敏感度分析[J].火箭推进,2009,35(5):56-59.ZHAO Zhe,LIU Baoqin.Sensitivity analysis of controlling elements on a gas turbine performance test bench[J].Journal of rocket propulsion,2009,35(5):56-59.
[7]秦立森,赵晓路.IET短周期涡轮实验台模拟高空涡轮性能试验研究[J].工程热物理学报,2009(1):47-52.
[2]张贵田,高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[3]于龙淮,周德山,译.航空航天工程中的小流量泵[M].北京:宇航出版社,1993.
[4]Jouini D B M,SJOLANDER S A.Midspan flow-field measurements for two transonic linear turbine cascade at off-design conditions[J].ASME journal of turbomach,2002,124:176-186.
[5]逯婉若,黄智勇.涡轮性能实验研究[J].火箭推进,2004,30(6):11-14.LU Wanruo,HUANG Zhiyong.Experimental investagation of turbine performance[J].Journal of rocket pro pulsion,2004,30(6):11-14.
[6]赵哲,刘宝琴.燃气涡轮性能试验台的控制因素敏感度分析[J].火箭推进,2009,35(5):56-59.ZHAO Zhe,LIU Baoqin.Sensitivity analysis of controlling elements on a gas turbine performance test bench[J].Journal of rocket propulsion,2009,35(5):56-59.
[7]秦立森,赵晓路.IET短周期涡轮实验台模拟高空涡轮性能试验研究[J].工程热物理学报,2009(1):47-52.