重型燃气轮机压气机叶片的叶型叶栅设计

发布时间：2018-01-26 09:54

本文关键词： 重型燃气轮机跨音速叶型设计叶栅设计　出处：《华北电力大学(北京)》2016年硕士论文　论文类型：学位论文

【摘要】：电力工业是国民经济发展的基础。为了提高火力发电效率,调整能源结构,国家大力引进和发展燃气轮机电机组及其相关技术。随着重型燃气轮机在电力行业的份额增加,其压气机跨音速叶片的叶型叶栅国产化研究具有重要意义。本文主要研究工作有：1)对传统的NACA65(National Advisory Committee for Aeronautics)叶型进行数值模拟分析,并利用弯道方法根据仿真结果对其进行型线修改设计；探索并验证了压气机叶片的叶型设计方法与流程。2)研究了跨音速叶型工作特点与要求,基于贝塞尔曲线设计叶型上下型线、基于椭圆弧构造前后缘型线；经大量尝试生成了多种跨音速叶型,并对其中有代表性的四种进行了详细的空气动力学仿真分析对比,有如下规律：在跨音速流中,弯叶型更易产生斜激波,压力分布更稳定均衡,不易产生附面层分离。最大厚度位置能影响激波的产生的位置,将最大厚度位置在一定范围内后移,激波也能随之后移。3)以提高叶栅静压增压比,减少损失系数为目标,对这四类跨音速叶型的叶栅进行速度特性和功角特性仿真比较,得到规律如下：在跨音速叶栅中,同一种叶栅内,速度特性表现为静压增压比随马赫数增大先升高后下降,总压恢复系数逐渐降低,损失系数逐步上升并平稳,攻角特性表现为从负到正的变化过程中,静压增压比先升高后下降,总压恢复系数先升高后平稳再下降,损失系数先下降后平稳再上升。本文经过大量仿真实验与设计,确定叶型厚度较小、上下型线弯曲度均较大、叶型最大厚度位置靠后的叶型,即第四号叶型为设计结果,能满足重型燃气轮机压气机跨音速叶片的工作需求。
[Abstract]:The electric power industry is the foundation of the national economy development. In order to improve the efficiency of thermal power generation, adjust the energy structure. The country has made great efforts to introduce and develop gas turbine motor sets and related technologies. With the increase of the share of heavy gas turbines in the power industry. It is of great significance to study the localization of the transonic blades of its compressor. The main work of this paper is to study the traditional NACA 65 (1). The leaf profile of National Advisory Committee for Aeronautics was numerically simulated. And the curve method is used to modify the profile according to the simulation results. The working characteristics and requirements of transonic blade profile were studied. The upper and lower profile of blade profile was designed based on Bezier curve and the front and back edge profile of compressor blade was constructed based on elliptical arc. After a large number of attempts to generate a variety of transonic blade, and the representative of four of the detailed aerodynamics simulation analysis and comparison, there are the following laws: in transonic flow, curved blade is more likely to produce oblique shock waves. The pressure distribution is more stable and balanced, and it is not easy to produce boundary layer separation. The position of maximum thickness can affect the position of shock wave, and the position of maximum thickness can be moved backward in a certain range. Shock wave can also move backward. 3) in order to improve the static pressure booster ratio and reduce the loss coefficient, the velocity characteristics and power angle characteristics of these four transonic cascades are simulated and compared. The results are as follows: in the transonic cascade, the velocity characteristic of the same cascade is that the hydrostatic pressure booster ratio increases first and then decreases with the increase of Mach number, the total pressure recovery coefficient decreases gradually, and the loss coefficient increases steadily. The characteristic of angle of attack is from negative to positive, the ratio of static pressure booster first increases and then decreases, and the total pressure recovery coefficient increases first and then decreases steadily. After a large number of simulation experiments and design, it is determined that the blade shape is smaller, the curve of upper and lower profile is larger, and the position of the maximum thickness of the blade shape is lower than that of the back blade. The design result of the fourth blade can satisfy the transonic blade requirement of the heavy gas turbine compressor.
【学位授予单位】：华北电力大学(北京)
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：TK473

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