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作 者:邹宜霖[1] 艾延廷[1] 苏金友 ZOU Yi-lin;AI Yan-ting;SU Jin-you(Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System,Shenyang Aerospace University,Shenyang 110136,China;Key Laboratory on Aero-engine Altitude Simulation Technology,AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)
机构地区:[1]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,沈阳110136 [2]中国航发四川燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川绵阳621000
出 处:《燃气涡轮试验与研究》2020年第3期57-62,共6页Gas Turbine Experiment and Research
基 金:国家自然科学基金(11702177);辽宁省自然科学基金(20180550560)。
摘 要:航空发动机高空模拟试车台(简称高空台)动静架连接处存在气流泄漏或注入现象,导致低温试验时湿空气进入发动机,影响试验安全。针对该问题,根据理论分析和数值仿真,设计了一种基于中段进气的新型篦齿密封结构,建立了高空台动静架连接结构数值模型,分析了篦齿密封流场特性及泄漏特性。当进气口处于理想零泄漏状态时,控制口压力与进气口压力成正比;当控制口进气时,温度对封严效果基本无影响。本研究为减少高空模拟试车台动静架连接处主流道流量损失、提高试验安全系数,提供了一种新的高效密封结构。There exists air leakage or injection at the joint of the dynamic and static bench of the altitude simulation test facility,which results in the wet air entering the engine during the low temperature test and has effect on the safety of the test.Aiming at this problem,a new type of labyrinth seal structure based on mid-stage air intake was designed from both theoretical and numerical simulation aspects.The CFD model of the dynamic and static bench joint structure of the altitude simulation test facility was established.The flow field characteristics and leakage characteristics of the labyrinth seal were analyzed.When the inlet is in an ideal zero leakage state,control port pressure is proportional to inlet pressure.When the control port is worked,the temperature has little effect on the sealing effect.In order to reduce the flow loss of the main channel at the joint of the dynamic and static bench of the altitude simulation test bench and to improve the safety factor of the low temperature test,a new and efficient sealing structure has been designed.
关 键 词:航空发动机 高空模拟试车台 篦齿密封 流场特性 泄漏量 低温试验 CFD
分 类 号:V231.3[航空宇航科学与技术—航空宇航推进理论与工程]
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