摘要
燃烧加热器可用于高温高超声速风洞中高焓试验气流生成,为了实现总温、总压等参数模拟,需要对注入燃烧加热器的各组分气体流量进行控制.该文采用了临界流文丘里管用于注入燃烧加热器的空气、氧气和氢气流量控制,仿真结果表明,当文丘里管上下游压力比超过1.25后,其喉道形成音速截面,达到临界流状态,在喉道直径和气体介质不变的情况下,流入文丘里管的流量唯一取决于上游压力,通过对文丘里管上游压力的控制实现了注入燃烧加热器的各组分气体流量控制,应用于Φ600 mm高温高超声速风洞模拟参数控制,调试结果得出流量控制偏差小于±1.0％,满足了应用需求.
Abstract
Combustion heater can be used to generate high enthalpy test airflow in high temperature hypersonic wind tunnel.In order to simulate parameters such as total temperature and total pressure,it is necessary to control the flow of each component gas injected into combustion heater.The critical flow Venturi tube is used to control the flow of air,oxygen and hydrogen injected into the combustion heater.The simulation results show that when the pres-sure ratio between upstream and downstream of the Venturi tube exceeds 1.25,the sonic cross section of the Venturi tube reaches the critical flow state.Under the condition of constant throat diameter and gas medium,the flow into the Venturi tube only depends on the upstream pressure.By controlling the upstream pressure of the Venturi tube,the flow of each component injected into the combustion heater is controlled.It is applied to the simulation parame-ter control of Φ600 mm high temperature hypersonic wind tunnel.The debugging results show that the flow control deviation is less than 1.0％,which meets the application requirements.
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