压气机叶型反问题设计技术研究
发布时间：2018-10-08 18:42
【摘要】：叶轮机械叶片设计中通常采用的方法有正问题设计方法和反问题设计方法。正问题设计中设计人员通过分析设计要求，选择性能相近的叶型作为初始叶型，通过CFD或试验方法分析初始叶型气动性能，如果其不满足设计要求，，则根据相关经验或给定的优化准则反复修改叶型，直到其达到要求。正问题方法具有过程简单、易于实现等优点，但设计过程要耗费大量时间和成本。反问题设计中，设计人员根据设计要求给出流场中某些气动参数，通过气动参数与几何造型间的物理关系得到实现该流动特征的叶型。因此反问题设计的优势在于设计效率较高、对设计人员经验依赖较少。本文在冯卡门流体研究所（VKI）相关研究的基础上开展了叶片反问题设计方法的研究。全文研究内容主要包括以下几个方面： （1）构建了叶型无粘反问题设计流程，对其中的关键技术——基于特征变量边界理论的渗透边界、叶型修正技术进行了原理分析，并在课题组自主开发的计算流体力学软件NAPA中完成了渗透边界、叶型修正模块等无粘反问题设计组成部分的程序实现，从而实现了叶型反问题设计。 （2）对以下3类9个具有不同流动特点的管道及叶栅算例进行了反问题设计：1）无转折的曲壁面通道，如bump管道，二维拉瓦尔喷管；2）模拟单叶栅通道流动的转弯扩张通道；3）双圆弧叶型构成的平面叶栅。分别在气流无转折及气流发生转折的亚声速流动、存在激波的跨声速流动中逐步验证该无粘反问题设计方法的准确性。 （3）针对反问题设计方法实际使用时可能出现的目标流动与初始流动的流场结构间存在较大差异的情况，改进了渗透边界的处理方法，并在消除叶栅流动中槽道激波的反问题设计算例中进行了验证。 （4）把无粘反问题设计方法推广到粘性流动中，构建了叶型粘性反问题设计流程。在双圆弧叶型的亚声速流动中进行了粘性反问题设计的验证。改进了粘性反问题设计过程中无粘目标压力分布的预估方法，使之适用于存在激波的流动，并在存在激波的叶栅流动中进行了验证。 （5）针对NASALewis研究中心设计的一款两级风扇的第二级转子叶片叶中截面的叶型，应用本文构建的反问题设计技术进行了改进设计。改进后的叶型，在进口流动条件一致，保证叶型载荷不减小的前提下，流动损失减小。计算表明在来流马赫数1.02时，改进后的叶型其载荷较初始叶型提高2.2%，静压升系数提高9.4%，总压损失减小1.47%。
[Abstract]:The methods used in blade design of impeller machinery include forward problem design method and inverse problem design method. In the forward problem design, the designers choose the blade shape with similar performance as the initial blade shape by analyzing the design requirements, and analyze the aerodynamic performance of the initial blade shape by CFD or test method, if it does not meet the design requirements, The leaf profile is modified repeatedly according to relevant experience or given optimization criteria until it meets the requirements. The forward problem method has the advantages of simple process and easy implementation, but the design process needs a lot of time and cost. In inverse problem design, some aerodynamic parameters in the flow field are given according to the design requirements, and the blade profile of the flow characteristic is obtained by the physical relationship between the aerodynamic parameters and the geometric modeling. Therefore, the advantage of inverse problem design lies in its high design efficiency and less dependence on the designer's experience. In this paper, the design method of blade inverse problem is studied on the basis of the (VKI) research of von Carmen fluid Research Institute. The main contents of this paper are as follows: (1) the design process of blade inviscid inverse problem is constructed, and the infiltration boundary based on characteristic variable boundary theory is discussed. The principle of blade shape correction technology is analyzed, and the program of non-viscous inverse problem design, such as seepage boundary and blade shape correction module, is implemented in the computational fluid dynamics software NAPA, which is developed by the research group. Thus, the design of blade shape inverse problem is realized. (2) for the following three types of pipes and cascades with different flow characteristics, inverse problem design: 1) curved wall channel without turning, such as bump pipe, two-dimensional Laval nozzle, 2) turn expansion channel simulating flow in single cascade channel; 3) a planar cascade with double arc blades. The accuracy of the design method is verified step by step in the transonic flow with shock wave and the subsonic flow with no turning or turning of the flow. (3) in view of the large difference between the structure of the target flow and the flow field of the initial flow when the inverse problem design method is used in practice, the method of dealing with the permeation boundary is improved. The design example of the inverse problem of eliminating the channel shock in cascade flow is verified. (4) the inviscid inverse problem design method is extended to viscous flow, and the design flow of blade viscous inverse problem is constructed. The design of viscous inverse problem is verified in subsonic flow with double arc blades. The method of predicting the pressure distribution of non-viscous target in the design process of viscous inverse problem is improved to make it suitable for the flow with shock wave, and it is verified in the cascade flow with shock wave. (5) aiming at the blade profile of the second stage rotor blade of a two-stage fan designed by NASALewis Research Center, the inverse problem design technique constructed in this paper is used to improve the design. The flow loss of the improved blade is reduced on the premise that the inlet flow condition is the same and the load of the blade shape is not reduced. The calculation results show that the load of the improved blade shape is increased by 2.2 than that of the initial blade shape, the static pressure rising coefficient is increased by 9.4and the total pressure loss is reduced by 1.47m when the Mach number is 1.02.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2012
【分类号】：TH45
本文编号：2257862
[Abstract]:The methods used in blade design of impeller machinery include forward problem design method and inverse problem design method. In the forward problem design, the designers choose the blade shape with similar performance as the initial blade shape by analyzing the design requirements, and analyze the aerodynamic performance of the initial blade shape by CFD or test method, if it does not meet the design requirements, The leaf profile is modified repeatedly according to relevant experience or given optimization criteria until it meets the requirements. The forward problem method has the advantages of simple process and easy implementation, but the design process needs a lot of time and cost. In inverse problem design, some aerodynamic parameters in the flow field are given according to the design requirements, and the blade profile of the flow characteristic is obtained by the physical relationship between the aerodynamic parameters and the geometric modeling. Therefore, the advantage of inverse problem design lies in its high design efficiency and less dependence on the designer's experience. In this paper, the design method of blade inverse problem is studied on the basis of the (VKI) research of von Carmen fluid Research Institute. The main contents of this paper are as follows: (1) the design process of blade inviscid inverse problem is constructed, and the infiltration boundary based on characteristic variable boundary theory is discussed. The principle of blade shape correction technology is analyzed, and the program of non-viscous inverse problem design, such as seepage boundary and blade shape correction module, is implemented in the computational fluid dynamics software NAPA, which is developed by the research group. Thus, the design of blade shape inverse problem is realized. (2) for the following three types of pipes and cascades with different flow characteristics, inverse problem design: 1) curved wall channel without turning, such as bump pipe, two-dimensional Laval nozzle, 2) turn expansion channel simulating flow in single cascade channel; 3) a planar cascade with double arc blades. The accuracy of the design method is verified step by step in the transonic flow with shock wave and the subsonic flow with no turning or turning of the flow. (3) in view of the large difference between the structure of the target flow and the flow field of the initial flow when the inverse problem design method is used in practice, the method of dealing with the permeation boundary is improved. The design example of the inverse problem of eliminating the channel shock in cascade flow is verified. (4) the inviscid inverse problem design method is extended to viscous flow, and the design flow of blade viscous inverse problem is constructed. The design of viscous inverse problem is verified in subsonic flow with double arc blades. The method of predicting the pressure distribution of non-viscous target in the design process of viscous inverse problem is improved to make it suitable for the flow with shock wave, and it is verified in the cascade flow with shock wave. (5) aiming at the blade profile of the second stage rotor blade of a two-stage fan designed by NASALewis Research Center, the inverse problem design technique constructed in this paper is used to improve the design. The flow loss of the improved blade is reduced on the premise that the inlet flow condition is the same and the load of the blade shape is not reduced. The calculation results show that the load of the improved blade shape is increased by 2.2 than that of the initial blade shape, the static pressure rising coefficient is increased by 9.4and the total pressure loss is reduced by 1.47m when the Mach number is 1.02.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2012
【分类号】：TH45
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