跨声速低反力度压气机动叶性能优化研究

发布时间：2018-03-30 19:50

本文选题：跨声速　切入点：低反力度　出处：《哈尔滨工业大学》2015年硕士论文

【摘要】：低反力度吸附式压气机的设计思想为:在保证转子高效流动的条件下,应用主动流动控制技术对静子内部复杂的二次流动进行有效整合,从而实现整机高负荷设计。因此,对于此类型压气机,在兼顾附面层抽吸能力的前提下,如何设计出一高效、高负荷的转子将变得尤为重要。目前,关于低反力度转子的研究多基于亚声速来流,而在跨声速条件下,激波的存在使得转子内部流动更为复杂,几何构型变化将会对转子的气动性能产生怎样的影响是值得深入研究的,基于此原因,本文以某三级高负荷吸附式压气机首级跨声速转子作为研究对象,借助数值模拟的方法,详细地分析了几何参数变化、叶片三维造型对转子流场结构的影响,旨在进一步提升转子气动性能。首先,本文采用Rotor37转子进行数值模拟,以验证数值模拟软件NUMECA模拟结果的可靠性。在壁面y+处于湍流模型的适用范围的情况下,只改变网格数量来研究其对数值计算结果产生的影响,并和实验数据进行比较。结果表明,在网格数量超过77万以后,数值模拟的结果几乎不发生改变,NUMECA软件所模拟出来的结果的可靠性较高。其后,本文对等中径和等外径设计的转子的性能进行比较。比较结果表明,等中径设计的转子在全工况范围内效率比等外径设计的转子都要高,压比在设计点附近也比后者高,但喘振裕度比后者小,综合考虑压比和效率对等中径转子进行子午型线优化,优化结果表明,优化转子压比、效率和喘振裕度都有所提高。接着,本文对转子进行变间隙和稠度的研究。研究表明,随着间隙增加,压比、效率和喘振裕度会逐渐降低,转子的峰值效率和流量会随着稠度的增加而降低,而压比则逐渐增加。同时稠度增加会使激波前移,但会降低其强度。最后,本文对弯掠技术在转子中的应用进行研究。研究结果说明,前掠、反弯以及前掠和反弯联合的转子有利于提高转子的喘振裕度,同时能够保证其压比和效率在在一个很小的范围内变化。而正弯转子会使其压比、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.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V233

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