本文選題：跨聲速　切入點：低反力度　出處：《哈爾濱工業(yè)大學》2015年碩士論文

【摘要】：低反力度吸附式壓氣機的設(shè)計思想為:在保證轉(zhuǎn)子高效流動的條件下,應用主動流動控制技術(shù)對靜子內(nèi)部復雜的二次流動進行有效整合,從而實現(xiàn)整機高負荷設(shè)計。因此,對于此類型壓氣機,在兼顧附面層抽吸能力的前提下,如何設(shè)計出一高效、高負荷的轉(zhuǎn)子將變得尤為重要。目前,關(guān)于低反力度轉(zhuǎn)子的研究多基于亞聲速來流,而在跨聲速條件下,激波的存在使得轉(zhuǎn)子內(nèi)部流動更為復雜,幾何構(gòu)型變化將會對轉(zhuǎn)子的氣動性能產(chǎn)生怎樣的影響是值得深入研究的,基于此原因,本文以某三級高負荷吸附式壓氣機首級跨聲速轉(zhuǎn)子作為研究對象,借助數(shù)值模擬的方法,詳細地分析了幾何參數(shù)變化、葉片三維造型對轉(zhuǎn)子流場結(jié)構(gòu)的影響,旨在進一步提升轉(zhuǎn)子氣動性能。首先,本文采用Rotor37轉(zhuǎn)子進行數(shù)值模擬,以驗證數(shù)值模擬軟件NUMECA模擬結(jié)果的可靠性。在壁面y+處于湍流模型的適用范圍的情況下,只改變網(wǎng)格數(shù)量來研究其對數(shù)值計算結(jié)果產(chǎn)生的影響,并和實驗數(shù)據(jù)進行比較。結(jié)果表明,在網(wǎng)格數(shù)量超過77萬以后,數(shù)值模擬的結(jié)果幾乎不發(fā)生改變,NUMECA軟件所模擬出來的結(jié)果的可靠性較高。其后,本文對等中徑和等外徑設(shè)計的轉(zhuǎn)子的性能進行比較。比較結(jié)果表明,等中徑設(shè)計的轉(zhuǎn)子在全工況范圍內(nèi)效率比等外徑設(shè)計的轉(zhuǎn)子都要高,壓比在設(shè)計點附近也比后者高,但喘振裕度比后者小,綜合考慮壓比和效率對等中徑轉(zhuǎn)子進行子午型線優(yōu)化,優(yōu)化結(jié)果表明,優(yōu)化轉(zhuǎn)子壓比、效率和喘振裕度都有所提高。接著,本文對轉(zhuǎn)子進行變間隙和稠度的研究。研究表明,隨著間隙增加,壓比、效率和喘振裕度會逐漸降低,轉(zhuǎn)子的峰值效率和流量會隨著稠度的增加而降低,而壓比則逐漸增加。同時稠度增加會使激波前移,但會降低其強度。最后,本文對彎掠技術(shù)在轉(zhuǎn)子中的應用進行研究。研究結(jié)果說明,前掠、反彎以及前掠和反彎聯(lián)合的轉(zhuǎn)子有利于提高轉(zhuǎn)子的喘振裕度,同時能夠保證其壓比和效率在在一個很小的范圍內(nèi)變化。而正彎轉(zhuǎn)子會使其壓比、效率和喘振裕度都降低。
[Abstract]:The design idea of low counterforce adsorption compressor is as follows: under the condition of ensuring the efficient flow of the rotor, the active flow control technology is used to effectively integrate the complex secondary flow inside the stator so as to realize the design of the whole machine with high load. For this type of compressor, it is very important to design a rotor with high efficiency and high load on the premise of taking into account the suction capacity of the boundary layer. At present, the research on the low counterforce rotor is based on the subsonic flow. However, under the condition of transonic velocity, the existence of shock wave makes the flow inside the rotor more complicated, and the influence of the geometric configuration on the aerodynamic performance of the rotor is worthy of further study. In this paper, the first stage transonic rotor of a three-stage high load adsorption compressor is taken as the research object. By means of numerical simulation, the effects of geometric parameters and blade 3D modeling on the rotor flow field structure are analyzed in detail. The purpose of this paper is to further improve the aerodynamic performance of the rotor. Firstly, the Rotor37 rotor is used for numerical simulation to verify the reliability of the simulation results of the numerical simulation software NUMECA. When the wall y is in the applicable range of the turbulence model, Only the number of meshes is changed to study its effect on the numerical results, and the results are compared with experimental data. The results show that after the number of meshes exceeds 770000, The results of numerical simulation hardly change the reliability of the results simulated by NUMECA software. Then, the performances of the rotor designed with equal middle diameter and equal outer diameter are compared in this paper. The rotor designed with isometric diameter has higher efficiency and higher pressure ratio near the design point than the rotor designed with equal outer diameter in the whole working condition, but the surge margin is smaller than that of the latter. Considering the pressure ratio and the efficiency of the rotor, the meridian profile optimization is carried out. The optimization results show that the optimization of the rotor pressure ratio, the efficiency and the surge margin are improved. Then, the variable clearance and consistency of the rotor are studied in this paper. With the increase of clearance, the pressure ratio, efficiency and surge margin will gradually decrease, the peak efficiency and flow rate of rotor will decrease with the increase of consistency, while the pressure ratio will gradually increase. At the same time, the increase of consistency will make the shock wave move forward. Finally, this paper studies the application of bending swept technology in rotor. The results show that the forward, reverse bending and the combination of forward and backward bending can improve the surge margin of the rotor. At the same time, the pressure ratio and efficiency can be changed in a very small range, while the positive bending rotor will reduce the pressure ratio, efficiency and surge margin.
【學位授予單位】：哈爾濱工業(yè)大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V233

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本文編號：1687394