曹智顺,王洪斌,张树林,张联合,王小蒙,刘旭,葛宏志.落压比对航空发动机涡轮叶片流量特性的影响[J].航空发动机,2021,47(S1):32-39
落压比对航空发动机涡轮叶片流量特性的影响
Influence of Nozzle Pressure Ratio on Flow Characteristic of Aeroengine Turbine Blade
  
DOI:
中文关键词:  落压比  涡轮叶片  流量特性  气膜孔  影响因子  航空发动机
英文关键词:nozzle pressure ratio  turbine blade  flow characteristic  film hole  impact factor  aeroengine
基金项目:航空动力基础研究项目资助
作者单位E-mail
曹智顺,王洪斌,张树林,张联合,王小蒙,刘旭,葛宏志 中国航发沈阳发动机研究所沈阳110015 446383519@163.com 
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中文摘要:
      为了探明落压比对航空发动机涡轮叶片流量特性的影响,对试验坐标压比选择和气膜孔分布2个主要影响因素进行了 研究。忽略燃气及冷却空气温度的影响,依据涡轮叶片气膜孔出口静压将其分为3类。当涡轮叶片气膜孔以第1类或第2类为主 时,通过试验坐标压比的选择消除落压比对流量特性的影响;当涡轮叶片气膜孔以第3类或复合型为主时,利用2个不同落压比下 的流量特性,采用影响因子分析法可以获得任意落压比下的流量特性关系式。选用某型涡轮导向叶片进行不同落压比下的流量 特性试验,结果表明:理论分析结果与试验结果相差3%,二者具有较好的一致性。
英文摘要:
      In order to find out the influence of nozzle pressure ratio on flow characteristics of aeroengine turbine blade,two main influencing factors of test coordinate-pressure ratio selection and film hole distribution were studied. Ignoring the influence of gas and cool? ing air temperature,it was divided into three types according to the static pressure at the outlet of the film hole of turbine blade. When the film hole of turbine blade was dominated by first type or second type,the influence of nozzle pressure ratio on flow characteristics was elimi? nated by selecting the test coordinate-pressure ratio. When the film hole of turbine blade was dominated by third type or compound type, the flow characteristic relation under any nozzle pressure ratio could be obtained based on the flow characteristics of two different nozzle pressure ratios by using the impact factor analysis method. The flow characteristic test of a turbine guide blade was carried out under differ? ent nozzle pressure ratio. The results show that the theoretical analysis results are 3% different from the test results,and they are in good agreement.
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