引信侧进气涡轮发电机气动优化研究
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摘要
引信侧进气涡轮发电机作为引信电源的一种，其所具有的良好稳定的性能特点能够满足现代电子时间引信对电源的要求，成为引信电源发展的重要方向之一，对于我军现役和在研弹药引信都具有重要的应用价值。为适应引信电源的发展和现代战争的要求，本文以引信侧进气涡轮发电机研制工作为背景，围绕其气动优化所涉及到的各项理论及技术展开了系统的研究。
本文首先以绝对坐标系和旋转坐标系下积分形式三维可压缩雷诺平均Navier-Stokes方程为控制方程，建立了基于非结构网格条件下的三维隐式有限体积数值求解格式，给出了三维可压缩粘性流场的计算方法、定解条件和源项处理技术；研究了阵面推进法生成三维非结构网格的方法。此外，采用所建立的流场数值求解方法对二维NACA0012翼型跨音速流场和三维ONERA M6机翼跨音速绕流流场进行了详细的数值计算和分析，计算结果与实验结果吻合良好。
深入研究了引信涡轮发电机气动优化的策略和方法。提出了基于自学习响应面模型的气动优化方法，并对该方法所涉及到的关键技术即试验设计技术、响应面模型的寻优以及响应面模型的构造进行了详细研究，选择了一组典型解析函数对本文所提出的基于自学习响应面模型的气动优化算法进行了验证，验证结果表明，该方法具有良好的精度和适应性，能够满足引信侧进气涡轮发电机气动优化的要求。
在本文对流场数值求解方法及气动优化方法研究的基础之上，对引信涡轮发电机进气道的气动优化问题进行了详细研究。分别对两种进气道的气动优化流程、参数化定义方法、气动优化的目标函数等进行了分析和研究。然后在一定背景下，完成了两种进气道的气动优化设计，并对优化设计结果进行了分析。
详细研究了引信侧进气涡轮发电机整体三维气动优化所涉及到的相关技术问题。分析了引信侧进气涡轮发电机整体三维气动优化的方法及流程；论述了高速永磁发电机的结构、电磁特性和输出参数求解，分析了电机涡轮的运动特征；提出了结合电机涡轮运动特性分析及电磁特性分析的整体三维流场数值计算方法，与给定涡轮旋转角速度条件下三维流场的数值计算相比，该方法解决了三维流场数值计算时初始边界条件确定困难的问题，提高了流场数值计算的精度。本文最后完成了某引信侧进气涡轮发电机整体三维气动优化设计。
通过本文的研究可在一定程度上填补国内外引信侧进气涡轮发电机气动优化研究的空白，为进一步开展引信侧进气涡轮发电机的型号研究奠定了坚实的基础。
The turbine alternator with side intake ducts for the fuze, one of the important types ofthe fuze power, whose fine stable function characteristic can satisfy power demand ofmodern electricity fuze, has currently become the most important development direction offuze power and has important application value to our serving and studying ammunitionfuze. To cater for the development of fuze power and the demand of modern warfare, inthe present dissertation, the theory and the technology of aerodynamic optimization designof the turbine alternator with side intake ducts for-the fuze was studied in detail.
The dissertation builds the finite volume method for solving the compressibleReynolds average Navier-Stokes equations in absolute coordinates and in relative rotatingcoordinates on unstructured meshes; conducts a detailed analysis of Advancing FrontMethod (AFM) which is used to generate 3D unstructured grids; describes the types ofboundary conditions of numeric calculation of 3D flow field of the turbine alternator withside intake ducts for the fuze; and provides an explanation of how to set boundaryconditions. In addition, the 2D airfoil NACA 0012 and 3D ONERA M6 wing arecalculated to verify the above numeric method. The results show calculations match theexperimental results well.
In the dissertation, the author conducts a detailed analysis of the method ofaerodynamic optimization design; and puts forward a new method of aerodynamicoptimization design based on the Self-study Response Surface Methodology (SRSM). Thetheory and technology of SRSM, namely design of experiment (DOE), construction ofSRSM and finding optimum of SRSM are lucubrated. Then some representative functionsare chosen to verify the accuracy and adaptability of SRSM. The results show the SRSMhas fine accuracy and adaptability and is able to satisfy the request of aerodynamicoptimization design of the turbine alternator with side intake ducts for the fuze.
The dissertation also makes research with aerodynamic optimization design of theintake ducts based on the research of the numeric solving method and aerodynamicoptimization method; Conducts a detailed analysis of the parameterized method andoptimization objective function of the straight and side intake ducts; and carries out theaerodynamic optimization design of two types of the intake ducts.
The dissertation gives an in-depth study of the technology which 3D aerodynamicoptimization design involves. In this section of the dissertation, the method and the flow chart of the whole 3D aerodynamic optimization design are analyzed. Then the structure,electromagnetic characteristic, equivalent magnetogram, and equivalent calculation of thehigh-speed permanent magnet aero-synchronous alternators are studied. An iterativemethod of numerical calculation of 3-D flow-field of the turbine alternator with side intakeducts for the fuze is put forward, based on the interaction between flow-field and turbinerotational speed. This method solved the problem caused by the uncertainty of theboundary conditions, and improved the accuracy of numerical simulation ofthree-dimensional flow field of the turbine alternator with side intake ducts for the fuze.The dissertation also carries out the whole 3D aerodynamic optimization design of thealternator with side intake ducts for a certain fuze.
The finish of this dissertation has great help for the deeper research of the alternatorwith side intake ducts for the fuze, which is an important type of the fuze power and hasimportant application value to our serving and studying ammunition fuze.
本文首先以绝对坐标系和旋转坐标系下积分形式三维可压缩雷诺平均Navier-Stokes方程为控制方程，建立了基于非结构网格条件下的三维隐式有限体积数值求解格式，给出了三维可压缩粘性流场的计算方法、定解条件和源项处理技术；研究了阵面推进法生成三维非结构网格的方法。此外，采用所建立的流场数值求解方法对二维NACA0012翼型跨音速流场和三维ONERA M6机翼跨音速绕流流场进行了详细的数值计算和分析，计算结果与实验结果吻合良好。
深入研究了引信涡轮发电机气动优化的策略和方法。提出了基于自学习响应面模型的气动优化方法，并对该方法所涉及到的关键技术即试验设计技术、响应面模型的寻优以及响应面模型的构造进行了详细研究，选择了一组典型解析函数对本文所提出的基于自学习响应面模型的气动优化算法进行了验证，验证结果表明，该方法具有良好的精度和适应性，能够满足引信侧进气涡轮发电机气动优化的要求。
在本文对流场数值求解方法及气动优化方法研究的基础之上，对引信涡轮发电机进气道的气动优化问题进行了详细研究。分别对两种进气道的气动优化流程、参数化定义方法、气动优化的目标函数等进行了分析和研究。然后在一定背景下，完成了两种进气道的气动优化设计，并对优化设计结果进行了分析。
详细研究了引信侧进气涡轮发电机整体三维气动优化所涉及到的相关技术问题。分析了引信侧进气涡轮发电机整体三维气动优化的方法及流程；论述了高速永磁发电机的结构、电磁特性和输出参数求解，分析了电机涡轮的运动特征；提出了结合电机涡轮运动特性分析及电磁特性分析的整体三维流场数值计算方法，与给定涡轮旋转角速度条件下三维流场的数值计算相比，该方法解决了三维流场数值计算时初始边界条件确定困难的问题，提高了流场数值计算的精度。本文最后完成了某引信侧进气涡轮发电机整体三维气动优化设计。
通过本文的研究可在一定程度上填补国内外引信侧进气涡轮发电机气动优化研究的空白，为进一步开展引信侧进气涡轮发电机的型号研究奠定了坚实的基础。
The turbine alternator with side intake ducts for the fuze, one of the important types ofthe fuze power, whose fine stable function characteristic can satisfy power demand ofmodern electricity fuze, has currently become the most important development direction offuze power and has important application value to our serving and studying ammunitionfuze. To cater for the development of fuze power and the demand of modern warfare, inthe present dissertation, the theory and the technology of aerodynamic optimization designof the turbine alternator with side intake ducts for-the fuze was studied in detail.
The dissertation builds the finite volume method for solving the compressibleReynolds average Navier-Stokes equations in absolute coordinates and in relative rotatingcoordinates on unstructured meshes; conducts a detailed analysis of Advancing FrontMethod (AFM) which is used to generate 3D unstructured grids; describes the types ofboundary conditions of numeric calculation of 3D flow field of the turbine alternator withside intake ducts for the fuze; and provides an explanation of how to set boundaryconditions. In addition, the 2D airfoil NACA 0012 and 3D ONERA M6 wing arecalculated to verify the above numeric method. The results show calculations match theexperimental results well.
In the dissertation, the author conducts a detailed analysis of the method ofaerodynamic optimization design; and puts forward a new method of aerodynamicoptimization design based on the Self-study Response Surface Methodology (SRSM). Thetheory and technology of SRSM, namely design of experiment (DOE), construction ofSRSM and finding optimum of SRSM are lucubrated. Then some representative functionsare chosen to verify the accuracy and adaptability of SRSM. The results show the SRSMhas fine accuracy and adaptability and is able to satisfy the request of aerodynamicoptimization design of the turbine alternator with side intake ducts for the fuze.
The dissertation also makes research with aerodynamic optimization design of theintake ducts based on the research of the numeric solving method and aerodynamicoptimization method; Conducts a detailed analysis of the parameterized method andoptimization objective function of the straight and side intake ducts; and carries out theaerodynamic optimization design of two types of the intake ducts.
The dissertation gives an in-depth study of the technology which 3D aerodynamicoptimization design involves. In this section of the dissertation, the method and the flow chart of the whole 3D aerodynamic optimization design are analyzed. Then the structure,electromagnetic characteristic, equivalent magnetogram, and equivalent calculation of thehigh-speed permanent magnet aero-synchronous alternators are studied. An iterativemethod of numerical calculation of 3-D flow-field of the turbine alternator with side intakeducts for the fuze is put forward, based on the interaction between flow-field and turbinerotational speed. This method solved the problem caused by the uncertainty of theboundary conditions, and improved the accuracy of numerical simulation ofthree-dimensional flow field of the turbine alternator with side intake ducts for the fuze.The dissertation also carries out the whole 3D aerodynamic optimization design of thealternator with side intake ducts for a certain fuze.
The finish of this dissertation has great help for the deeper research of the alternatorwith side intake ducts for the fuze, which is an important type of the fuze power and hasimportant application value to our serving and studying ammunition fuze.
引文
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