本文選題：葉輪機(jī)械 + 跨音壓氣機(jī)　； 參考：《中國(guó)科學(xué)院研究生院（工程熱物理研究所）》2011年碩士論文

【摘要】：先進(jìn)的渦輪動(dòng)力系統(tǒng)對(duì)風(fēng)扇/壓氣機(jī)氣動(dòng)性能的要求不斷提高,不斷發(fā)展和完善的設(shè)計(jì)方法及工具是完成日益苛刻的設(shè)計(jì)要求的重要保證。以粘性、全三維氣動(dòng)數(shù)值模擬為分析手段的設(shè)計(jì)技術(shù)日益成熟,而氣動(dòng)數(shù)值優(yōu)化設(shè)計(jì)在現(xiàn)代設(shè)計(jì)體系中發(fā)揮著越來(lái)越重要的作用,并已成為葉輪機(jī)械領(lǐng)域的研究熱點(diǎn)。本文以某單級(jí)跨音壓氣機(jī)為研究對(duì)象,以提高其壓比、效率和擴(kuò)大穩(wěn)定工作范圍為目標(biāo),對(duì)該壓氣機(jī)進(jìn)行了多目標(biāo)氣動(dòng)優(yōu)化,并著重分析了提高跨音級(jí)壓氣機(jī)氣動(dòng)性能的關(guān)鍵因素。 本文首先對(duì)原型壓氣機(jī)進(jìn)行全三維數(shù)值模擬,數(shù)值求解相對(duì)坐標(biāo)系下的三維、粘性Navier-Stokes雷諾平均方程,計(jì)算結(jié)果表明該數(shù)值方法能很好的預(yù)測(cè)跨音速軸流壓氣機(jī)的性能,保證了計(jì)算的可靠性。優(yōu)化設(shè)計(jì)系統(tǒng)分為三個(gè)模塊：參數(shù)化方法、全三維流場(chǎng)評(píng)價(jià)和尋優(yōu)算法。參數(shù)化采用Bezier曲線重構(gòu)原始?jí)簹鈾C(jī)幾何型線(子午通道、葉片),先后通過(guò)反算控制頂點(diǎn)和擬合尋優(yōu)以減小構(gòu)造曲線和原始型線的誤差,盡可能達(dá)到精確逼近的效果；全三維流場(chǎng)計(jì)算及評(píng)價(jià)目的是對(duì)設(shè)計(jì)參數(shù)進(jìn)行性能評(píng)估,以供優(yōu)化算法進(jìn)行優(yōu)劣比較并做出裁決；尋優(yōu)算法是設(shè)計(jì)系統(tǒng)的核心部分,它直接決定了尋優(yōu)的效率和效果,本文采用基于人工神經(jīng)網(wǎng)絡(luò)(ANN)和遺傳算法(GA)的復(fù)合尋優(yōu)策略。神經(jīng)網(wǎng)絡(luò)作為一種近似模型,用于縮小問(wèn)題的求解規(guī)模,遺傳算法作為一種模擬自然進(jìn)化機(jī)制的算法,理論上可以達(dá)到全局尋優(yōu),實(shí)際應(yīng)用中給定適當(dāng)?shù)膮?shù),遺傳算法可以在較大的設(shè)計(jì)空間內(nèi)搜索到良好的結(jié)果。 應(yīng)用該優(yōu)化設(shè)計(jì)系統(tǒng),本文首先針對(duì)葉片積疊線進(jìn)行優(yōu)化,旨在探索積疊線對(duì)跨音級(jí)壓氣機(jī)性能的影響。研究表明,彎掠設(shè)計(jì)可以改善葉輪機(jī)械內(nèi)部流動(dòng),調(diào)整激波位置和強(qiáng)度,使負(fù)荷在弦向和展向得以重新分配,具有重新組織流動(dòng)的效用。積疊線優(yōu)化表明,彎、掠兩個(gè)維度的聯(lián)合使用可以明顯的提高壓氣機(jī)的性能。壓氣機(jī)內(nèi)部的流動(dòng)狀況和負(fù)荷的分布還與二維葉型密切相關(guān),本文第二階段的三維優(yōu)化,既考慮積疊線,又兼顧葉型的修改,實(shí)現(xiàn)了壓氣機(jī)性能的進(jìn)一步提升。
[Abstract]:The requirements of the advanced turbine power system to the aerodynamic performance of the fan / compressor are increasing, and the continuous development and perfection of the design methods and tools are the important guarantee to complete the demanding design. The design technology of the viscous, all three-dimensional aerodynamic numerical simulation is increasingly mature, and the Aerodynamic Numerical Optimization Design is in the modern design. The system is playing a more and more important role and has become a hot research topic in the field of turbomachinery. In this paper, a single stage transonic compressor is taken as the research object to improve its pressure ratio, efficiency and expand the stable working range. The multi-objective aerodynamic optimization of the compressor is carried out, and the aerodynamic performance of the transonic compressor is emphatically analyzed. The key factor in energy.
In this paper, the three-dimensional numerical simulation of the prototype compressor is carried out, and the numerical solution of the three-dimensional and viscous Navier-Stokes Reynolds mean equation in the relative coordinate system is numerically solved. The calculation results show that the numerical method can predict the performance of the transonic axial compressor well and ensure the reliability of the calculation. The optimization design system is divided into three modules: parameterization The Bezier curve is used to reconstruct the geometric line of the original compressor (Meridian channel and blade) parameterized. The error of the structure curve and the original line is reduced by the inverse control vertex and the fitting optimization, and the effect of accurate forcing is achieved as much as possible. The performance evaluation of the design parameters is made for the optimization algorithm to compare and make a decision. The optimization algorithm is the core part of the design system. It directly determines the efficiency and effect of optimization. In this paper, a complex optimization strategy based on artificial neural network (ANN) and genetic algorithm (GA) is adopted. The genetic algorithm, as an algorithm to simulate the natural evolution mechanism, can achieve global optimization in theory. In practical application, the genetic algorithm can search for good results in a larger design space.
In this paper, the optimal design system is used to optimize the blade stacking line. The aim of this paper is to explore the effect of stacked line on the performance of the transonic compressor. The study shows that the bending design can improve the internal flow of the turbomachinery, adjust the position and strength of the shock wave, redistribute the load in the chord direction and direction, and have the effect of reorganizing the flow. The combined use of stacked line shows that the combined use of two dimensions can obviously improve the performance of the compressor. The flow status in the compressor and the distribution of the load are closely related to the two-dimensional leaf type. In this paper, the three-dimensional optimization of the second stage not only considers the stacking line, but also considers the modification of the blade type, thus realizing the further improvement of the compressor performance.
【學(xué)位授予單位】：中國(guó)科學(xué)院研究生院（工程熱物理研究所）
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2011
【分類號(hào)】：TH453

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