本文關(guān)鍵詞：串聯(lián)式TBCC進(jìn)氣道模態(tài)轉(zhuǎn)換模擬器設(shè)計(jì)及其特性分析　出處：《航空學(xué)報(bào)》2016年12期 　論文類型：期刊論文

  更多相關(guān)文章： 吸氣式高超聲速推進(jìn)系統(tǒng) 渦輪基組合循環(huán)(TBCC) 串聯(lián)式TBCC進(jìn)氣道 模態(tài)轉(zhuǎn)換模擬器 風(fēng)洞試驗(yàn)

【摘要】：為了實(shí)現(xiàn)渦輪基組合循環(huán)(TBCC)推進(jìn)系統(tǒng)平穩(wěn)模態(tài)轉(zhuǎn)換過(guò)程的模擬,在前期風(fēng)洞試驗(yàn)研究的基礎(chǔ)上對(duì)串聯(lián)式TBCC進(jìn)氣道模態(tài)轉(zhuǎn)換模擬器進(jìn)行重新設(shè)計(jì)。采用線性化及非對(duì)稱的思路對(duì)該模擬器進(jìn)行設(shè)計(jì)并對(duì)其特性展開(kāi)數(shù)值仿真研究。結(jié)果表明:該模擬器不僅需要模擬發(fā)動(dòng)機(jī)工況改變引起的背壓變化,而且能通過(guò)流通截面面積線性變化,實(shí)現(xiàn)兩個(gè)通道的流量分配。該裝置的特點(diǎn)是能保證模態(tài)轉(zhuǎn)換過(guò)程中每一點(diǎn)的渦輪/沖壓通道的總堵塞比不變,使本文所研究的進(jìn)氣道在總堵塞比保持為65%時(shí)進(jìn)行模態(tài)轉(zhuǎn)換,結(jié)尾激波基本維持在喉道等直段內(nèi)且進(jìn)氣道出口馬赫數(shù)基本維持在0.30,流量系數(shù)基本為0.45,渦輪/沖壓通道流量呈線性變化,與預(yù)期目標(biāo)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.
【作者單位】： 南京航空航天大學(xué)能源與動(dòng)力學(xué)院江蘇省航空動(dòng)力系統(tǒng)重點(diǎn)實(shí)驗(yàn)室;
【基金】：航空科學(xué)基金(2015ZB52016) 中央高校基本科研業(yè)務(wù)費(fèi)(NS2015025)~~
【分類號(hào)】：V236
【正文快照】： 網(wǎng)絡(luò)出版地址:www.cnki.net/kcms/detail/11.1929.V.20160330.1143.002.html引用格式:劉君,袁化成,葛寧.串聯(lián)式TBCC進(jìn)氣道模態(tài)轉(zhuǎn)換模擬器設(shè)計(jì)及其特性分析[J].航空學(xué)報(bào),2016,37(12):3675-3684.LIUJ,YUAN H C,GE N.Design and flow characteristics analysis of mode transitio

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