2.4m跨声速风洞TPS压力调节装置设计  

Design of TPS pressure regulating device in 2.4 m transonic wind tunnel

作　　者：范长海[1] 周洪[1] 周晓刚[1] 杜宁[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳622661

出　　处：《机械设计》2013年第10期80-83,共4页Journal of Machine Design

摘　　要：涡轮动力模拟器(TPS)试验是一种先进的进/排气一体化动力模拟试验技术,该技术能为大型军用运输机、战略轰炸机、大型民用飞机、巡航导弹等推进/机体一体化设计提供必须的试验平台和有力的技术支撑。其中,TPS压力调节装置主要是为TPS单元提供精确流量驱动气体的关键设备。文中介绍了2.4 m跨声速风洞TPS压力调节装置的原理、设计、实现及应用情况。试验结果表明,该系统运行稳定,工作可靠,TPS涡轮驱动气体的流量波动可以控制在0.001 kg/s以内,可应用于型号试验。The advanced testing technique with turbine pow- ered simulator （TPS） to simulate the aerodynamic effects of aircraft propulsion system can provide essential testing setup and strong technical support for the propulsion/airframe integration design of large-scale military aircraft, strategy bomber, large-scale civil air- craft and crui.se missile. The pressure regul.ati.ng device of TPS sup- plies steady driving air for TPS units. The basal principle, design, realization and run of TPS pressure regulating device in the 2.4 m transonic wind tunnel is introduced and the results show that the whole device is stable , reliable , the mass flow control accuracy of TPS driving air is within 0. 001 kg/s, the TPS pressure regulating device of the 2.4 m transonic wind tunnel can be used to develop the aircrafts.

关 键 词：TPS 数字阀 跨声速风洞 文氏管 

分 类 号：TH122[机械工程—机械设计及理论]