【摘要】：壓氣機(jī)的性能和穩(wěn)定性與進(jìn)氣畸變息息相關(guān)。如果無視進(jìn)氣畸變的影響,就會使壓氣機(jī)的氣動性能惡化、效率和穩(wěn)定裕度降低,甚至誘發(fā)旋轉(zhuǎn)失速或喘振。因此,流場畸變的研究意義重大。本課題以某型高負(fù)荷超聲速軸流壓氣機(jī)的一級為研究對象,應(yīng)用全周非定常數(shù)值模擬的方法開展工作。重點研究設(shè)計工況下不同進(jìn)口總壓畸變條件時,動靜葉柵內(nèi)流場對畸變來流的響應(yīng)機(jī)制。 因為本文的研究對象為某型軸流式壓氣機(jī)一級的改型,其性能參數(shù)都較原型有所改變,所以就要重新繪制特性曲線。本文主要繪制90%、100%和110%設(shè)計轉(zhuǎn)速下的壓氣機(jī)特性曲線,并采用Fluent和Numeca兩種計算軟件進(jìn)行模擬,以便驗證數(shù)值模擬結(jié)果的軟件無關(guān)性。而后將數(shù)值模擬網(wǎng)格應(yīng)用自適應(yīng)功能加密,從總參數(shù)和關(guān)鍵截面內(nèi)流場驗證了網(wǎng)格無關(guān)性。 本文對于非定常問題的研究均采用標(biāo)記流道的方法,首先全面細(xì)致的探究了插板深度為進(jìn)口外徑(半徑)38.2%的畸變類型。結(jié)果表明,畸變會使得壓氣機(jī)時均質(zhì)量流量和等熵效率降低,并引起壓氣機(jī)可用穩(wěn)定裕度的損失。通過對一個周期各時間步流場的研究,著重揭示了動靜葉區(qū)域?qū)τ诨儊砹鞯姆嵌ǔｍ憫?yīng)。動葉區(qū)域,主要關(guān)注畸變影響下動葉流道中激波的結(jié)構(gòu)、強(qiáng)度、位置的變化；靜葉區(qū)域,重點分析畸變影響下靜葉流道分離規(guī)律。并且從機(jī)理上探究了動靜葉區(qū)域?qū)τ诨冺憫?yīng)的原因。 對多種不同插板深度畸變的研究表明,隨著插板深度的增加,壓氣機(jī)的時均質(zhì)量流量和效率會隨之下降。靜葉的流動分離主要集中在葉頂和葉根處,靜葉葉根處的分離會對葉頂分離產(chǎn)生抑制。當(dāng)插板深度大于一定的程度后,進(jìn)一步增加插板深度,只會使得動葉和靜葉區(qū)域完全畸變區(qū)的流道數(shù)目增加(單純范圍上的擴(kuò)大),而并不會加重單個流道的流動惡化程度。并且對于本文所研究的壓氣機(jī)來說,輪緣處的畸變更影響效率,而輪轂處的畸變更影響流量(即通流能力)。
[Abstract]:The performance and stability of the compressor are closely related to the intake distortion. If the effect of the intake distortion is ignored, the aerodynamic performance of the compressor is deteriorated, the efficiency and the stability margin are reduced, and even the rotating stall or surge is induced. Therefore, the research of flow field distortion is of great significance. In this paper, the first stage of a high-load supersonic axial-flow compressor is used as the research object, and the method of all-week unsteady numerical simulation is applied to carry out the work. In this paper, the response mechanism of the flow field in the dynamic and static cascade is studied. Because the research object of this paper is a modification of an axial-flow compressor stage, the performance parameters are changed with the prototype, so the characteristic curve is to be redrawn Line. This paper mainly draws 90%,100% and 110% of the compressor characteristic curves at the design speed, and uses Fluent and Numeca to simulate the software so as to verify the software of the numerical simulation results. And then the numerical simulation grid is applied to the self-adaptive function encryption, and the grid-independent is verified from the total parameters and the flow field in the critical cross-section. In this paper, the method of marking the flow channel is used in the study of the unsteady problem. First, the design of the depth of the flashboard as the inlet outer diameter (radius) of 38.2% is studied in a comprehensive and detailed way. The results show that the distortion can reduce the mass flow and isentropic efficiency at the time of the compressor and cause the compressor to have a stable margin. The results of the study on the flow field in each time of a cycle show the non-constant of the dynamic and dynamic lobe in the flow of the distorted flow. Constant response. The main focus on the structure, intensity and position of the shock wave in the moving blade flow channel under the influence of the distortion; the static blade area, and the main analysis of the distortion influence the static blade flow channel. From the mechanism, the effect of the dynamic and dynamic leaf area on the distortion is investigated. The results show that, with the increase of the depth of the flashboard, the mass flow and efficiency of the compressor at the time of the compressor The flow separation of the dead leaves is mainly concentrated at the tip of the leaves and the root of the leaves, and the separation of the leaves at the leaves of the leaves can be used to separate the leaves. The depth of the flashboard is further increased when the depth of the flashboard is greater than a certain degree, so that the number of flow channels in the completely distorted area of the moving blade and the stationary blade area is increased (the expansion in the pure range), and the flow of the single flow channel is not increased. the degree of dynamic deterioration. and for the compressor studied herein, the distortion at the rim is more effective and the distortion at the hub influences the flow (i. e.,
【學(xué)位授予單位】：大連海事大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2012
【分類號】：TH45

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 張士杰,袁新,葉大均;低展弦比跨音速軸流風(fēng)扇轉(zhuǎn)子流場三維數(shù)值模擬[J];工程熱物理學(xué)報;2001年05期

2 張士杰,袁新,葉大均;跨音速軸流壓氣機(jī)級三維粘性流場全工況數(shù)值模擬[J];工程熱物理學(xué)報;2003年01期

3 李美林,林峰,陳靜宜,童志庭,聶超群;周向進(jìn)口畸變對壓氣機(jī)失速過程的影響[J];工程熱物理學(xué)報;2005年06期

4 李傳鵬;胡駿;王英鋒;趙勇;;進(jìn)氣畸變對壓氣機(jī)穩(wěn)定性的影響[J];工程熱物理學(xué)報;2006年05期

5 張靖煊;林峰;張宏武;聶超群;;旋轉(zhuǎn)進(jìn)口畸變與軸流壓氣機(jī)旋轉(zhuǎn)失速相關(guān)聯(lián)的模型與實驗探索[J];工程熱物理學(xué)報;2007年02期

6 蔣康濤,徐綱,張宏武,黃偉光,陳靜宜;單級跨音壓氣機(jī)整圈三維動靜葉干涉的數(shù)值模擬[J];航空動力學(xué)報;2002年05期

7 劉前智;雙級風(fēng)扇三維粘性非定常流動的數(shù)值解[J];航空動力學(xué)報;2003年06期

8 李傳鵬,胡駿;旋轉(zhuǎn)進(jìn)氣畸變對軸流壓氣機(jī)氣動穩(wěn)定性影響實驗研究[J];航空動力學(xué)報;2004年04期

9 鄭寧;鄒正平;徐力平;;風(fēng)扇進(jìn)氣畸變?nèi)S非定常數(shù)值模擬技術(shù)研究[J];航空動力學(xué)報;2007年01期

10 張靖煊;童志庭;聶超群;;低速軸流壓氣機(jī)進(jìn)口總壓畸變與旋轉(zhuǎn)失速關(guān)聯(lián)的實驗研究[J];航空動力學(xué)報;2007年05期

相關(guān)博士學(xué)位論文 前3條

1 蔣康濤;低速軸流壓氣機(jī)旋轉(zhuǎn)失速的數(shù)值模擬研究[D];中國科學(xué)院研究生院（工程熱物理研究所）;2004年

2 張靖煊;畸變條件下軸流壓氣機(jī)葉頂間隙流對流動失穩(wěn)影響的非定常機(jī)制[D];中國科學(xué)院研究生院（工程熱物理研究所）;2007年

3 孫鵬;總壓畸變對跨聲速風(fēng)扇流場結(jié)構(gòu)影響的全流道數(shù)值模擬[D];哈爾濱工業(yè)大學(xué);2007年

相關(guān)碩士學(xué)位論文 前3條

1 王春利;風(fēng)扇/壓氣機(jī)氣動穩(wěn)定性的數(shù)值模擬研究[D];西北工業(yè)大學(xué);2007年

2 賈海軍;軸流壓氣機(jī)跨聲速三維流場數(shù)值模擬[D];西北工業(yè)大學(xué);2006年

3 李亮;進(jìn)口總壓畸變穩(wěn)定性評定方法研究[D];南京航空航天大學(xué);2008年

，

本文編號：2434810