【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(huì)使壓氣機(jī)的氣動(dòng)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(chǎng)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(jí)為研究對(duì)象,應(yīng)用全周非定常數(shù)值模擬的方法開展工作。重點(diǎn)研究設(shè)計(jì)工況下不同進(jìn)口總壓畸變條件時(shí),動(dòng)靜葉柵內(nèi)流場(chǎng)對(duì)畸變來流的響應(yīng)機(jī)制。 因?yàn)楸疚牡难芯繉?duì)象為某型軸流式壓氣機(jī)一級(jí)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(jì)轉(zhuǎn)速下的壓氣機(jī)特性曲線,并采用Fluent和Numeca兩種計(jì)算軟件進(jìn)行模擬,以便驗(yàn)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(chǎng)驗(yàn)證了網(wǎng)格無關(guān)性。 本文對(duì)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(huì)使得壓氣機(jī)時(shí)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(duì)一個(gè)周期各時(shí)間步流場(chǎng)的研究,著重揭示了動(dòng)靜葉區(qū)域?qū)τ诨儊砹鞯姆嵌ǔｍ憫?yīng)。動(dòng)葉區(qū)域,主要關(guān)注畸變影響下動(dòng)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(diǎn)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(dòng)靜葉區(qū)域?qū)τ诨冺憫?yīng)的原因。 對(duì)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(shí)均質(zhì)量流量和效率會(huì)隨之下降。靜葉的流動(dòng)分離主要集中在葉頂和葉根處,靜葉葉根處的分離會(huì)對(duì)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(huì)使得動(dòng)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(huì)加重單個(gè)流道的流動(dòng)惡化程度。并且對(duì)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(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)：2434810