摘要
为满足新型吸气式发动机研制对于试验系统高压大流量超声速来流模拟条件下气体流量的准确测量和现场校准的迫切需求,设计了一套基于高压、大流量p.V.T.t法和比较法的流量现场校准装置(以下简称现场校准装置),通过原级p.V.T.t法与次级标准音速喷嘴相结合的方式,实现了压力3~23 MPa和流量1~60 kg/s条件下音速喷嘴流量系数的校准、溯源和试验系统空气流量准确测量,高压空气大流量现场校准装置扩展不确定度为0.84%。
A flow field calibration facility based on high pressure mass flow p. V. T. t method and the comparing method （hereafter referred to as on-line calibration facility） was designed to meet the ur- gent demand of air-breathing engine testing system to achieve accurate measurement and field calibra- tion of high-pressure large flow supersonic air. By integrating the primary p. V. T. t method and the sec- ondary standard-sonic nozzle, this facility effectuates calibration, traceability and accurate measure- ment of air flow coefficient of the sonic nozzle under the conditions of pressure range of 3 - 23 MPa and flow range of 1 -60 kg/s. The extended uncertainty of the on-line calibration facility is 0. 84%.
出处
《火箭推进》
CAS
2017年第5期69-73,共5页
Journal of Rocket Propulsion
基金
国防军工技术基础2015年科研项目(JSJC2013203A001)
