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A Design Method for Inverse Problem of Axial Compressor S2 Based on Dimensionless Load Control Parameters

A technology of axial flow compressor and load control, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve problems such as space load matching design axial flow compressor S2 inverse problem, shorten the design cycle, improve aerodynamic Improvement of design accuracy and aerodynamic performance

Active Publication Date: 2022-04-08
中国船舶重工集团公司第七0三研究所
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Problems solved by technology

[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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  • A Design Method for Inverse Problem of Axial Compressor S2 Based on Dimensionless Load Control Parameters
  • A Design Method for Inverse Problem of Axial Compressor S2 Based on Dimensionless Load Control Parameters
  • A Design Method for Inverse Problem of Axial Compressor S2 Based on Dimensionless Load Control Parameters

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[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 purpose of the present invention is to provide a design method of axial flow compressor S2 inverse problem based on dimensionless load control parameters, through the spanwise distortion law design, spanwise loss design and typical S2 flow surface streamline curvature method to obtain the axial flow The S2 aerodynamic design scheme of the compressor. The present invention uses the two key dimensionless parameters of load coefficient and reaction degree to carry out the customized design of the inlet pre-rotation of the rotor blades at all levels of the axial flow compressor, and realizes the active control of the space load of the compressor in the S2 design stage, so that the axial flow compressor The flow design of the S2 inverse problem has reached the degree of parameterization and refinement, which effectively improves the aerodynamic design accuracy of the axial flow compressor and improves the aerodynamic performance, which is very suitable for engineering design applications. At the same time, the method is not limited to gas turbine axial compressors, but is also applicable to the aerodynamic design process of various industrial axial compressors and aeroengine axial 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 Patents(China)
IPC IPC(8): G06F30/17G06F30/28G06F113/08G06F119/14
CPCG06F30/17G06F30/28G06F2113/08G06F2119/14
Inventor 王琦潘宏伟王旭张舟毛冬岩万新超邓庆锋
Owner 中国船舶重工集团公司第七0三研究所
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