串联式TBCC进气道模态转换模拟器设计及其特性分析

发布时间：2018-01-02 01:13

本文关键词：串联式TBCC进气道模态转换模拟器设计及其特性分析　出处：《航空学报》2016年12期 　论文类型：期刊论文

【摘要】：为了实现涡轮基组合循环(TBCC)推进系统平稳模态转换过程的模拟,在前期风洞试验研究的基础上对串联式TBCC进气道模态转换模拟器进行重新设计。采用线性化及非对称的思路对该模拟器进行设计并对其特性展开数值仿真研究。结果表明:该模拟器不仅需要模拟发动机工况改变引起的背压变化,而且能通过流通截面面积线性变化,实现两个通道的流量分配。该装置的特点是能保证模态转换过程中每一点的涡轮/冲压通道的总堵塞比不变,使本文所研究的进气道在总堵塞比保持为65%时进行模态转换,结尾激波基本维持在喉道等直段内且进气道出口马赫数基本维持在0.30,流量系数基本为0.45,涡轮/冲压通道流量呈线性变化,与预期目标一致。
[Abstract]:In order to realize the simulation of steady mode conversion process of turbine-based combined cycle (TBCC) propulsion system. Based on the previous wind tunnel experiments, the series TBCC intake port modal conversion simulator was redesigned. The linearization and asymmetry of the simulator were used to design the simulator and its characteristics were simulated numerically. The results show that:. The simulator not only needs to simulate the change of back pressure caused by engine operating condition change. The flow distribution of the two channels can be realized by the linear variation of the flow section area. The characteristics of the device are that the total plugging ratio of the turbine / punching channel at each point in the mode conversion process is not changed. When the total clogging ratio of the inlet in this paper is maintained at 65, the end shock wave is basically maintained in the straight section of the throat and the Mach number of the inlet outlet is maintained at 0.30. The flow coefficient is 0.45, and the flow rate of turbine / punching channel changes linearly, which is consistent with the expected target.
【作者单位】：南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室;
【基金】：航空科学基金(2015ZB52016) 中央高校基本科研业务费(NS2015025)~~
【分类号】：V236
【正文快照】： 网络出版地址:www.cnki.net/kcms/detail/11.1929.V.20160330.1143.002.html引用格式:刘君,袁化成,葛宁.串联式TBCC进气道模态转换模拟器设计及其特性分析[J].航空学报,2016,37(12):3675-3684.LIUJ,YUAN H C,GE N.Design and flow characteristics analysis of mode transitio

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