多级轴流压气机级设计技术及气动性能研究
发布时间：2018-10-11 08:44
【摘要】：轴流式压气机不但是燃气轮机的三大核心部件之一,而且作为单独的动力设备在工业、能源、化工等行业中具有举足轻重的作用；所以压气机的设计一直以来都受到了高度的重视。在多级轴流压气机新的设计中,为了缩短设计周期、增加设计可靠性、降低设计成本,经常在现有压气机的基础上进行加零级设计来增加质量流量或提高压比从而得到满足新要求的压气机。 本文分析了原压气机的性能、加级要求以及基于相似准则的加零级设计基本原理；讨论了压气机加零级的设计流程以及加级匹配点的选择、零级压比和通流的确定,并在此基础上进行了压气机零级的一维设计,从而得到零级各个截面的参数；通过零级的平面叶型选择、对称叶型厚度分布及中弧线的确定、叶型的扭转设计等步骤完成了零级叶栅的三维设计 利用CFD计算软件对所设计零级以及压气机加级前后共15条特性曲线各个工况点进行了计算。文章首先分析了因蜗壳造成的进气不均匀的影响、压气机加级前后总体性能以及所设计零级的总体性能；并从相对气流角、绝对气流角、总压压比、反动度、折合流量、折合转速等方面分析了加级前后的匹配情况;然后通过叶片型面静压分布、径向加功量分布讨论了叶片载荷的问题；通过叶片表面流线、S1流面的流线和马赫数的比较分析了流场性能；通过叶顶泄露以及熵的比较,分析了压气机中损失的情况；最后分析了非设计工况下压气机加级前后的性能比较。通过以上分析可以看出,压气机加零级后质量流量满足了新的工作条件的要求,并具有良好的整体匹配性能,原压气机的流动状况得到了改善,加级后的压气机具有更好的运行稳定性。
[Abstract]:Axial flow compressor is not only one of the three core components of gas turbine, but also plays an important role in industrial, energy, chemical and other industries as a separate power equipment. So the design of compressor has been highly valued. In the new design of multistage axial flow compressor, in order to shorten the design period, increase the design reliability and reduce the design cost, The zero stage design is often carried out on the basis of the existing compressor to increase the mass flow rate or increase the pressure ratio to obtain a compressor that meets the new requirements. In this paper, the performance of the original compressor, the requirements of the adding stage and the basic principle of the zero-adding stage design based on the similarity criterion are analyzed, and the design flow of the zero-adding stage of the compressor and the selection of the matching point, the determination of the zero-stage pressure ratio and the flow passage are discussed. On this basis, the one-dimensional design of the zero stage of the compressor is carried out, and the parameters of each section of the zero stage are obtained, and the thickness distribution of the symmetrical blade and the determination of the middle arc are obtained through the plane blade shape selection of the zero stage. The three dimensional design of the zero cascade was completed by the torsional design of the blade shape. The design of zero stage and the compressor before and after the addition of the zero stage were calculated by using the CFD calculation software, and 15 characteristic curves were calculated at each working point of the designed zero stage and the compressor before and after the addition of the zero stage. This paper first analyzes the influence of the inlet air inhomogeneity caused by the volute, the overall performance of the compressor before and after adding the stage and the overall performance of the designed zero stage, and analyzes the relative air flow angle, the absolute air flow angle, the total pressure ratio, the reaction degree and the equivalent flow rate. The matching situation before and after adding grade is analyzed in the aspects of reduced speed and so on, and then the problem of blade load is discussed through the static pressure distribution of blade profile and radial power addition distribution. The flow field performance is analyzed by comparing the streamlines and Mach numbers on the surface of the blade, S1 and the blade surface, and the loss in the compressor is analyzed by comparing the leakage of the blade top and the entropy. Finally, the performance comparison of compressor before and after adding stage under off-design condition is analyzed. Through the above analysis, it can be seen that the mass flow rate of the compressor after adding zero stage meets the requirements of the new working conditions, and has good overall matching performance, and the flow condition of the original compressor has been improved. The added stage compressor has better operation stability.
【学位授予单位】：哈尔滨工程大学
【学位级别】：硕士
【学位授予年份】：2011
【分类号】：TH453
[Abstract]:Axial flow compressor is not only one of the three core components of gas turbine, but also plays an important role in industrial, energy, chemical and other industries as a separate power equipment. So the design of compressor has been highly valued. In the new design of multistage axial flow compressor, in order to shorten the design period, increase the design reliability and reduce the design cost, The zero stage design is often carried out on the basis of the existing compressor to increase the mass flow rate or increase the pressure ratio to obtain a compressor that meets the new requirements. In this paper, the performance of the original compressor, the requirements of the adding stage and the basic principle of the zero-adding stage design based on the similarity criterion are analyzed, and the design flow of the zero-adding stage of the compressor and the selection of the matching point, the determination of the zero-stage pressure ratio and the flow passage are discussed. On this basis, the one-dimensional design of the zero stage of the compressor is carried out, and the parameters of each section of the zero stage are obtained, and the thickness distribution of the symmetrical blade and the determination of the middle arc are obtained through the plane blade shape selection of the zero stage. The three dimensional design of the zero cascade was completed by the torsional design of the blade shape. The design of zero stage and the compressor before and after the addition of the zero stage were calculated by using the CFD calculation software, and 15 characteristic curves were calculated at each working point of the designed zero stage and the compressor before and after the addition of the zero stage. This paper first analyzes the influence of the inlet air inhomogeneity caused by the volute, the overall performance of the compressor before and after adding the stage and the overall performance of the designed zero stage, and analyzes the relative air flow angle, the absolute air flow angle, the total pressure ratio, the reaction degree and the equivalent flow rate. The matching situation before and after adding grade is analyzed in the aspects of reduced speed and so on, and then the problem of blade load is discussed through the static pressure distribution of blade profile and radial power addition distribution. The flow field performance is analyzed by comparing the streamlines and Mach numbers on the surface of the blade, S1 and the blade surface, and the loss in the compressor is analyzed by comparing the leakage of the blade top and the entropy. Finally, the performance comparison of compressor before and after adding stage under off-design condition is analyzed. Through the above analysis, it can be seen that the mass flow rate of the compressor after adding zero stage meets the requirements of the new working conditions, and has good overall matching performance, and the flow condition of the original compressor has been improved. The added stage compressor has better operation stability.
【学位授予单位】：哈尔滨工程大学
【学位级别】：硕士
【学位授予年份】：2011
【分类号】：TH453
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