發(fā)布時(shí)間：2018-06-03 02:03

  本文選題：溫度畸變發(fā)生器 + 氫燃料��； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：溫度畸變發(fā)生器是航空發(fā)動(dòng)機(jī)研制過程中評定發(fā)動(dòng)機(jī)氣動(dòng)穩(wěn)定性的重要設(shè)備之一,要求其能準(zhǔn)確模擬各類溫度畸變源的工作范圍,研究溫度畸變發(fā)生器畸變特性對航空發(fā)動(dòng)機(jī)的設(shè)計(jì)及其穩(wěn)定性評定具有重要的意義。本文以小流量航空發(fā)動(dòng)機(jī)溫度畸變發(fā)生器的工程應(yīng)用為背景,采用數(shù)值模擬及試驗(yàn)的方法,開展小流量航空發(fā)動(dòng)機(jī)溫度畸變發(fā)生器的設(shè)計(jì)及工作特性研究,主要研究成果包括:(1)以小流量航空發(fā)動(dòng)機(jī)進(jìn)口參數(shù)為設(shè)計(jì)參數(shù),針對以氫氣為燃料、空氣為氧化劑的氫燃燒式溫度畸變發(fā)生器,設(shè)計(jì)了火焰穩(wěn)定器和噴氫桿,噴氫桿包括順噴和逆噴兩種方案,并進(jìn)行了數(shù)值模擬,結(jié)果表明兩種方案均能穩(wěn)定工作。(2)針對氫燃燒式溫度畸變發(fā)生器的單個(gè)穩(wěn)定器模型和周向90°范圍模型進(jìn)行了穩(wěn)態(tài)點(diǎn)火試驗(yàn)研究,通過單個(gè)穩(wěn)定器模型的試驗(yàn)表明火焰穩(wěn)定器具有良好的穩(wěn)焰能力,隨著供氫壓力的升高,溫升值也逐漸增大,隨著進(jìn)口流量增加貧油點(diǎn)熄火極限逐漸增加;通過周向90°范圍模型的試驗(yàn)研究表明,順噴和逆噴結(jié)構(gòu)總壓恢復(fù)系數(shù)均大于0.98,總壓不均勻度均小于2%,兩種結(jié)構(gòu)的溫度分布不均勻度均在15%以下,且順噴結(jié)構(gòu)獲得的溫升值大于逆噴結(jié)構(gòu)獲得的溫升值。(3)建立單個(gè)穩(wěn)定器的計(jì)算模型,采用數(shù)值模擬方法研究了其穩(wěn)態(tài)燃燒過程,其中燃燒化學(xué)反應(yīng)模型采用總包反應(yīng)和9組分20步的氫氣基元反應(yīng)進(jìn)行對比研究,并與試驗(yàn)結(jié)果進(jìn)行對比。結(jié)果表明基元反應(yīng)結(jié)果與試驗(yàn)結(jié)果相近,因而選取基元反應(yīng)為化學(xué)反應(yīng)模型。建立不同周向范圍及加入壓氣機(jī)的氫燃燒式溫度畸變發(fā)生器的計(jì)算模型,研究氫燃燒式溫度畸變發(fā)生器穩(wěn)態(tài)和非穩(wěn)態(tài)燃燒過程。結(jié)果表明:溫度畸變場的溫升值和溫度不均勻度變化在距離穩(wěn)定器600mm的截面位置開始趨于穩(wěn)定,經(jīng)過壓氣機(jī)之后,畸變場畸變強(qiáng)度減小,溫度周向不均勻度也略微減小,高溫區(qū)范圍變化不大,但位置發(fā)生了明顯的偏移,同時(shí)發(fā)現(xiàn)較高的溫度畸變會(huì)在壓氣機(jī)出口誘發(fā)產(chǎn)生漩渦,造成壓氣機(jī)內(nèi)流動(dòng)不穩(wěn)定;相間位置的兩個(gè)加熱單元工作時(shí)獲得的高溫區(qū)范圍略大于相鄰位置獲得高溫區(qū)范圍;供氫壓力越大,溫升率越大,而緩沖容積越大,溫升率越小。(4)探索了熱射流式溫度畸變發(fā)生器初步方案設(shè)計(jì),采用數(shù)值模擬方法對設(shè)計(jì)模型進(jìn)行了初步研究。在熱流進(jìn)口溫度為1500K的條件下,熱射流式溫度畸變發(fā)生器能在出口獲得300K的面平均溫升,溫度不均勻度在15%以內(nèi)。
[Abstract]:Temperature distortion generator is one of the important equipments for evaluating the aero-engine aerodynamic stability in the development of aero-engine. It is required to simulate the working range of all kinds of temperature distortion sources accurately. It is of great significance to study the distortion characteristics of temperature distortion generator for the design and stability evaluation of aeroengine. In this paper, based on the engineering application of small flow aero-engine temperature distortion generator, the design and working characteristics of small flow aero-engine temperature distortion generator are studied by numerical simulation and test. The main research results include: (1) taking the inlet parameters of small flow aeroengine as design parameters, a flame stabilizer and a hydrogen injection rod are designed for the hydrogen combustion temperature distortion generator with hydrogen as fuel and air as oxidant. The hydrogen injection rod consists of two schemes, one is the direct injection and the other is the reverse jet, and the numerical simulation is carried out. The results show that both schemes can work stably. (2) A steady ignition experiment is carried out for a single stabilizer model and a circumferential 90 擄range model for a hydrogen combustion temperature distortion generator. The experiments of a single stabilizer model show that the flame stabilizer has a good flame stabilizer ability, with the increase of hydrogen supply pressure, the temperature rise gradually increases, and the limit of quenching of lean oil point increases with the increase of inlet flow rate. The experimental results of the circumferential 90 擄range model show that the total pressure recovery coefficient is greater than 0.98, the total pressure unevenness is less than 2, and the temperature distribution unevenness of the two structures is below 15%. Moreover, the temperature rise obtained by the injection structure is higher than that obtained by the reverse jet structure. (3) the calculation model of a single stabilizer is established, and the steady combustion process of the stabilizer is studied by means of numerical simulation. The combustion chemical reaction model was compared with the experimental results by using the total package reaction and the hydrogen radical reaction of 9 components and 20 steps. The results show that the results of the elementary reaction are close to the experimental results, so the elementary reaction is chosen as the chemical reaction model. The calculation model of hydrogen combustion temperature distortion generator with different circumferential range and compressor was established to study the steady and unsteady combustion process of hydrogen combustion temperature distortion generator. The results show that the temperature appreciation of temperature distortion field and the variation of temperature inhomogeneity begin to stabilize in the section position of the distance stabilizer 600mm. After the compressor, the distortion intensity of the distortion field decreases and the temperature circumferential unevenness decreases slightly. The range of high temperature has little change, but the position has obvious deviation. At the same time, it is found that the higher temperature distortion will induce vortex at the compressor outlet, resulting in the flow instability in the compressor. The range of the high temperature region obtained by the two heating units at the interphase position is slightly larger than that obtained from the adjacent position. The higher the hydrogen supply pressure, the greater the temperature rise rate and the larger the buffer volume. The lower the temperature rise rate is, the preliminary scheme design of the thermal jet temperature distortion generator is explored, and the design model is studied by numerical simulation method. At the inlet temperature of 1500K, the thermal jet temperature distortion generator can obtain an average temperature rise of 300K at the outlet, and the temperature inhomogeneity is less than 15%.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V263.3

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本文編號(hào)：1971039