Axial flow compressor S2 inverse problem design method based on dimensionless load control parameters

An axial flow compressor, dimensionless parameter technology, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve the problem of space load matching design axial flow compressor S2 inverse problem, shorten the design cycle, improve the The effect of aerodynamic design accuracy and aerodynamic performance improvement

Active Publication Date: 2021-04-23
中国船舶重工集团公司第七0三研究所
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[0004] The purpose of the present invention is to provide a design method for axial flow compressor S2 inverse problem based on dimensionless load control parameters to solve the space load matching design problem in the aerodynamic design of axial flow compressor

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  • Axial flow compressor S2 inverse problem design method based on dimensionless load control parameters
  • Axial flow compressor S2 inverse problem design method based on dimensionless load control parameters
  • Axial flow compressor S2 inverse problem design method based on dimensionless load control parameters

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Embodiment Construction

[0028] The present invention is described in more detail below in conjunction with accompanying drawing example:

[0029] combine figure 1 , a kind of axial flow compressor S2 inverse problem design method based on dimensionless load control parameters of the present invention is realized through the following steps:

[0030] Step 1: Design the spanwise twisting law. Two dimensionless parameters, load coefficient ψ and reaction degree Ω, are used as load control parameters. The load coefficient ψ and the reaction degree Ω pass through the circumferential speed U of the rotor blade and the absolute tangential speed C of the inlet and outlet of the rotor blade 1u and C 2u Calculation:

[0031] Load factor: A dimensionless parameter characterizing the load capacity of an axial compressor stage;

[0032] reactionary degree: It is a dimensionless parameter that characterizes the load distribution between moving and stationary blades in an axial flow compressor stage.

[0...

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Abstract

The invention aims to provide an axial flow compressor S2 inverse problem design method based on dimensionless load control parameters. An S2 aerodynamic design scheme of an axial flow compressor is obtained through spanwise distortion rule design, spanwise loss design and typical S2 flow surface streamline curvature method solving. Customized design of prewhirling of all stages of moving blade inlets of the axial flow compressor is conducted through two key dimensionless parameters including the load coefficient and the reaction degree, active control over the space load of the compressor in the S2 design stage is achieved, and the S2 inverse problem through-flow design of the axial flow compressor reaches the parameterization and refinement degree; the pneumatic design precision of the axial flow compressor is effectively improved, the pneumatic performance is improved, and the method is very suitable for engineering design application. Meanwhile, the invention is not limited to a gas turbine axial flow compressor, but also suitable for the pneumatic design process of various industrial axial flow compressors and aero-engine axial flow compressors / fans.

Description

technical field [0001] The invention relates to a gas turbine design method, in particular to a compressor design method. Background technique [0002] As one of the three core components of the gas turbine, the performance of the compressor directly affects the economic index of the gas turbine. The development of gas turbines in the future puts forward extremely high requirements on compressor components: on the one hand, the level of stage load is increased, and on the other hand, it is to ensure long-term efficient and stable operation in a wide range of working conditions. Therefore, it has become one of the main research directions in the field of modern turbomachinery design to design a compressor with excellent performance indicators and high reliability, while reducing design costs and shortening the design cycle. [0003] The S1 and S2 flow surface calculation programs have been widely used in the advanced aerodynamic design of compressors, and have become the cor...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/28G06F113/08G06F119/14
CPCG06F30/17G06F30/28G06F2113/08G06F2119/14
Inventor 王琦潘宏伟王旭张舟李冬万新超邓庆锋
Owner 中国船舶重工集团公司第七0三研究所
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