發(fā)布時(shí)間：2018-03-16 23:38

  本文選題：高壓壓氣機(jī)　切入點(diǎn)：數(shù)值模擬　出處：《上海交通大學(xué)》2012年碩士論文　論文類型：學(xué)位論文

【摘要】：軸流壓氣機(jī)作為航空燃?xì)鉁u輪發(fā)動(dòng)機(jī)的核心部件之一,其運(yùn)行效率和穩(wěn)定性對(duì)發(fā)動(dòng)機(jī)的性能起著重要影響。從發(fā)動(dòng)機(jī)的高壓壓氣機(jī)中進(jìn)行引氣,是保證發(fā)動(dòng)機(jī)正常運(yùn)行和滿足飛機(jī)飛行需求的必要環(huán)節(jié)。從壓氣機(jī)引出壓力、溫度不同的空氣,可用于機(jī)艙供氣、飛機(jī)防冰、渦輪冷卻、間隙密封、提供油箱及附件設(shè)備的高壓環(huán)境等多個(gè)方面。同時(shí),在發(fā)動(dòng)機(jī)啟動(dòng)、停機(jī)以及非設(shè)計(jì)工況運(yùn)行時(shí),合理的引氣可以有效防止機(jī)組發(fā)生失速和喘振。引氣無疑會(huì)改變壓氣機(jī)的工作狀態(tài),從而影響發(fā)動(dòng)機(jī)的工作狀態(tài)。因此,為了保障發(fā)動(dòng)機(jī)的正常工作,有必要研究引氣對(duì)壓氣機(jī)的影響。 本文利用流場(chǎng)數(shù)值模擬軟件,以三級(jí)半軸流高壓壓氣機(jī)為研究對(duì)象,探索了引氣結(jié)構(gòu)、位置和引氣流量對(duì)壓氣機(jī)性能和流場(chǎng)的影響。首先,為保證數(shù)值計(jì)算過程的穩(wěn)定性以及結(jié)果的準(zhǔn)確性,綜合考察了網(wǎng)格規(guī)模、拓?fù)湫问健⒉罘指袷胶屯牧髂Ｐ蛯?duì)數(shù)值計(jì)算過程的影響,在此基礎(chǔ)上確定了后續(xù)引氣研究中采用的網(wǎng)格、差分格式和湍流模型。 其次,研究了無引氣和有引氣情形下壓氣機(jī)的性能和流場(chǎng)。結(jié)果表明,引氣使主流進(jìn)口流量增大,主流出口流量減小;壓氣機(jī)的等熵效率增大、總壓比減小。引氣吸除了端壁附近的高熵流體,明顯改善了引氣位置相鄰的兩列葉片在葉頂區(qū)域的損失。引氣還明顯地改變了下游葉片的進(jìn)口氣流角,從而改變了級(jí)與級(jí)間的匹配特性。 再次,為研究引氣結(jié)構(gòu)和引氣位置的影響,構(gòu)建了通流面積相同、但進(jìn)口形狀和引氣位置不同的引氣槽。數(shù)值計(jì)算的結(jié)果表明:引氣位置對(duì)壓氣機(jī)性能的影響較為顯著。在不同的周向引氣位置中,在葉片尾緣下游引氣的影響最好,在壓力面?zhèn)纫龤獾挠绊懽畈睢Ｔ诓煌妮S向位置中,在級(jí)與級(jí)之間引氣的影響較好,在葉柵流道中間引氣的影響較差。 最后,探索了壓氣機(jī)性能和流場(chǎng)的變化與引氣流量間的關(guān)系。結(jié)果表明:引氣流量對(duì)壓氣機(jī)性能的影響受到壓氣機(jī)本身所處工作點(diǎn)的影響:在高轉(zhuǎn)速下,效率隨著引氣流量的增大而明顯地增大,而在低轉(zhuǎn)速下,效率并沒有隨引氣流量的增大而明顯地增大。
[Abstract]:As one of the core components of the aeronautical gas turbine engine, the axial flow compressor has an important effect on the performance of the engine. It is necessary to ensure the normal operation of the engine and meet the flight requirements of the aircraft. The pressure is extracted from the compressor and the air at different temperatures can be used in the engine room for air supply, aircraft anti-ice, turbine cooling, clearance sealing, Provides high pressure environment for fuel tank and accessories. At the same time, when engine starts, stops and runs off-design, Reasonable air entrapment can effectively prevent the stall and surge of the unit. The exhaust will undoubtedly change the working state of the compressor and thus affect the working state of the engine. Therefore, in order to ensure the normal operation of the engine, It is necessary to study the effect of air entrainment on compressor. In this paper, the effects of entrainment structure, position and flow rate on the performance and flow field of a three-stage semi-axial high pressure compressor are studied by using the numerical simulation software of flow field. In order to ensure the stability of the numerical calculation process and the accuracy of the results, the effects of grid size, topological form, difference scheme and turbulence model on the numerical calculation process are comprehensively investigated. On this basis, the mesh, difference scheme and turbulence model used in the subsequent air-entraining research are determined. Secondly, the performance and flow field of compressor without and without air entrainment are studied. The results show that the main stream inlet flow rate increases, the mainstream outlet flow rate decreases, and the isentropic efficiency of compressor increases. The total pressure ratio is reduced. The high entropy fluid near the end wall is sucked by the entrainer, which obviously improves the loss of the two rows of blades adjacent to the entrainment position in the top of the blade. The inlet air angle of the downstream blade is also obviously changed by the air entrainment. Thus, the matching property between stages is changed. Thirdly, in order to study the influence of entrainment structure and air entrainment position, the same flow passage area was constructed. The numerical results show that the influence of the entrainment position on the compressor performance is significant. In the different circumferential air entrainment positions, the air entraining at the lower edge of the blade tail edge is the best. In different axial positions, the effect of air entraining between stages and stages is better than that between cascades. Finally, the relationship between the performance of compressor and the variation of flow field and air entrainment flow rate is explored. The results show that the effect of air entrainment flow on compressor performance is affected by the working point of the compressor itself: at high speed, The efficiency increases obviously with the increase of the entrainment flow rate, but does not increase obviously with the increase of the entrainment flow rate at low rotational speed.
【學(xué)位授予單位】：上海交通大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2012
【分類號(hào)】：TH45

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本文編號(hào)：1622223