夹福年,刘 涛,杨彩琼,冷林涛,蔡 云.前输出轴涡轴发动机高空台进气装置设计及验证[J].测控技术,2022,41(12):36-41
前输出轴涡轴发动机高空台进气装置设计及验证
Design and Verification of Intake Device for High-Altitude Simulation Test of Front Output Shaft Turbo-Shaft Engines
  
DOI:10.19708/j.ckjs.2022.12.007
中文关键词:  涡轴发动机  高空模拟试验  进气装置  不均匀度  吹风试验
英文关键词:turbo-shaft engine  high-altitude simulation test  air intake installation  unevenness  blowing test
基金项目:国家稳定支持项目(WDZC2021-1-3)
作者单位
夹福年 中国航发四川燃气涡轮研究院 
刘 涛 中国航发四川燃气涡轮研究院 
杨彩琼 中国航发四川燃气涡轮研究院 
冷林涛 中国航发四川燃气涡轮研究院 
蔡 云 中国航发四川燃气涡轮研究院 
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中文摘要:
      对某前输出轴涡轴发动机高空模拟试验进气装置进行了设计,通过三维数值仿真的方法对比分析了典型工况进气涡壳内有无整流装置情况下发动机进口的流场品质,确定在增加整流装置的情况下,发动机进口压力不均匀度小于1%,温度不均匀度小于1%。为降低进气装置压力损失,对进气装置进行了优化设计,仿真结果表明,在最大流量下,压损降低了30%。最后通过吹风试验验证了流场品质满足设计要求,解决了涡壳进气方式产生的流场畸变问题。同时将导管流量数据与导流盆流量数据进行对比,证明了导流盆测流量方案的合理性。该设计可在此类涡轴发动机高空模拟试验中推广运用。
英文摘要:
      The intake installation of a turbo-shaft engine with front output shaft is designed.By means of three-dimensional numerical simulation,the flow field quality at the inlet of the engine with and without the rectifying device in the inlet volute under typical working conditions is compared and analyzed.It is determined that the pressure unevenness at the inlet of the engine is less than 1% and the temperature unevenness is less than 1% when the rectifying device is added.In order to reduce the pressure loss of the intake installation,the intake installation is optimized.The simulation results show that the pressure loss is reduced by 30% under the maximum flow rate.Finally,the blowing test verifies that the flow field quality meets the design requirements,and solves the problem of flow field distortion caused by the inlet mode of the volute.Meanwhile,the comparison between the flow data of the conduit and diversion basin proves the rationality of the flow measurement scheme of the diversion basin.This design can be widely used in the high-altitude simulation test of this kind of turboshaft engine.
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