本文關(guān)鍵詞：外并聯(lián)式TBCC組合發(fā)動(dòng)機(jī)的建模與特性分析　出處：《哈爾濱工業(yè)大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： TBCC組合發(fā)動(dòng)機(jī) 發(fā)動(dòng)機(jī)建模 渦輪發(fā)動(dòng)機(jī) 沖壓發(fā)動(dòng)機(jī) 轉(zhuǎn)級(jí)過(guò)程 控制規(guī)律

【摘要】：TBCC組合發(fā)動(dòng)機(jī)由于其地面自起動(dòng)、工作馬赫數(shù)范圍寬、可重復(fù)使用等優(yōu)點(diǎn)已成為雙級(jí)入軌(TSTO)中最有希望的第一級(jí)動(dòng)力系統(tǒng)。而外并聯(lián)式TBCC組合發(fā)動(dòng)機(jī)由于其渦輪發(fā)動(dòng)機(jī)和沖壓發(fā)動(dòng)機(jī)有相互獨(dú)立的工作通道而具有更好的可控性已成為主流研究對(duì)象。本文通過(guò)建立外并聯(lián)式TBCC組合發(fā)動(dòng)機(jī)模型對(duì)發(fā)動(dòng)機(jī)特性隨發(fā)動(dòng)機(jī)控制變量的變化規(guī)律和發(fā)動(dòng)機(jī)的控制規(guī)律進(jìn)行了研究。首先,根據(jù)組合發(fā)動(dòng)機(jī)在飛行包線上三個(gè)不同工作模態(tài),建立了組合發(fā)動(dòng)機(jī)不同工模態(tài)發(fā)動(dòng)機(jī)模型和組合發(fā)動(dòng)機(jī)模型。對(duì)于渦輪發(fā)動(dòng)機(jī)模態(tài),根據(jù)渦輪發(fā)動(dòng)機(jī)的組成由渦輪發(fā)動(dòng)機(jī)的部件模型組合得到渦輪發(fā)動(dòng)機(jī)模型。對(duì)于沖壓發(fā)動(dòng)機(jī)模態(tài),根據(jù)沖壓發(fā)動(dòng)機(jī)在超燃模態(tài)、亞燃模態(tài)和進(jìn)氣道不起動(dòng)3種模態(tài)時(shí)發(fā)動(dòng)機(jī)的流場(chǎng)特性建立了沖壓發(fā)動(dòng)機(jī)模型。轉(zhuǎn)級(jí)模態(tài)通過(guò)渦輪發(fā)動(dòng)機(jī)和沖壓發(fā)動(dòng)機(jī)進(jìn)氣道面積變化的配合特點(diǎn)組合得到組合發(fā)動(dòng)機(jī)模型。然后,根據(jù)得到的發(fā)動(dòng)機(jī)模型,仿真分析了組合發(fā)動(dòng)機(jī)在飛行包線不同工作模態(tài)時(shí)發(fā)動(dòng)機(jī)特性隨發(fā)動(dòng)機(jī)控制變量的變化規(guī)律。在渦輪發(fā)動(dòng)機(jī)模態(tài),分析了壓氣機(jī)喘振裕度、壓氣機(jī)增壓比和發(fā)動(dòng)機(jī)推力等參數(shù)隨渦輪轉(zhuǎn)速、加力方式和尾噴管喉部截面面積的變化規(guī)律。在沖壓發(fā)動(dòng)機(jī)模態(tài),分析了沖壓發(fā)動(dòng)機(jī)模態(tài)轉(zhuǎn)換對(duì)應(yīng)的4種臨界狀態(tài)時(shí)的燃油當(dāng)量比、喉道比和進(jìn)氣道擴(kuò)張比的空間分布規(guī)律以及亞燃和超燃模態(tài)時(shí)燃燒室出口溫度和發(fā)動(dòng)機(jī)推力隨燃油當(dāng)量比、喉道比和進(jìn)氣道擴(kuò)張比的變化規(guī)律。轉(zhuǎn)級(jí)模態(tài)則是分析了渦輪發(fā)動(dòng)機(jī)進(jìn)氣道開(kāi)度改變時(shí)渦輪發(fā)動(dòng)機(jī)特性的變化規(guī)律。最后根據(jù)建立的發(fā)動(dòng)機(jī)模型和發(fā)動(dòng)機(jī)特性分析結(jié)果,利用模型建立了發(fā)動(dòng)機(jī)模型穩(wěn)態(tài)狀態(tài)參數(shù)數(shù)據(jù)庫(kù)。利用數(shù)據(jù)庫(kù)對(duì)選定的發(fā)動(dòng)機(jī)推力設(shè)計(jì)規(guī)律在一定的約束條件下進(jìn)行了組合發(fā)動(dòng)機(jī)不同工作模態(tài)控制規(guī)律設(shè)計(jì),以及在對(duì)應(yīng)控制規(guī)律下發(fā)動(dòng)機(jī)特性的變化規(guī)律分析,利用所得控制規(guī)律對(duì)組合發(fā)動(dòng)機(jī)模型進(jìn)行了驗(yàn)證。
[Abstract]:TBCC engine due to the ground from the start, Maher number range, can be reused has become a dual stage to orbit (TSTO) first stage power system is the most hopeful. But because of the combination of parallel type TBCC engine turbine engine and ramjet engine working channel is independent and has better controllability has become the main research object. Through the establishment of external parallel TBCC engine model of engine control characteristics with the change rule of the engine and engine control variables are studied. Firstly, based on a combination of engine in envelope three different modes, a combination of different working modes of engine engine model and combined engine model for the turbine engine mode, according to the composition of the turbine engine by turbine engine mode by a combination of component model of turbine engine Type. For ramjet mode, according to the ramjet engine in supersonic combustion mode, ramjet mode and unstart 3 flow characteristics of engine modal established ramjet model. With the combination of modal transfer characteristics of turbine engine and ramjet inlet area change combined engine model. Then, according to the engine models. And simulation analysis of the combined engine in the flight envelope of different working modes when the engine performance changes with engine control variables. In the modal analysis of the turbine engine, compressor surge margin, compressor pressure ratio and engine thrust parameters such as turbine speed, variation of loading method and nozzle throat area. In ramjet mode analysis of the equivalent of 4, fuel ramjet mode transition critical state corresponding to the ratio of the throat and into the channel The spatial distribution of airway expansion ratio and ramjet and scramjet mode when the exit temperature of the combustor and the thrust of the engine with fuel equivalence ratio, variation ratio and expansion ratio of the laryngeal inlet. Transfer is analyzed the modal characteristics of turbine engine turbine engine inlet opening changes. Finally, according to the engine and engine model the characteristics of the analysis results, using the model of engine model steady state parameter database. Using the database engine thrust design rules selected under certain constraints of control law designing combined engine in different working modes, and the analysis of characteristics of engine in the corresponding control law under the changing rules of the control law was verified the combination of the engine model.

【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：TK401

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