A supersonic blade design method suitable for high inlet relative Mach number
A design method and Mach number technology, applied to components, design optimization/simulation, and mechanical equipment of pumping devices for elastic fluids, can solve the problem that supersonic cascades cannot achieve aerodynamic performance and cannot accurately control supersonic Cascade start-up conditions and other issues, to achieve the effect of accurate control
Active Publication Date: 2021-04-30
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology
The previous supersonic cascade design method cannot combine the starting condition of the supersonic cascade with the unique angle of attack condition, and cannot accurately control the starting condition of the supersonic cascade, so that the supersonic cascade cannot achieve the predetermined aerodynamic performance
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[0044] In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the examples. The following examples are explanations of the present invention and the present invention is not limited to the following examples.
[0045] Taking the specific application of the present invention to the design of the supersonic cascade airfoil as an example, the supersonic cascade airfoil is designed and completed according to the design requirements.
[0046] SS1, the design incoming flow condition of the known supersonic blade shape: the design incoming flow Mach number is Ma ∞ =1.8, the design incoming air flow angle is β ∞ = 65°.
[0047] SS2. The design geometric parameters of the known supersonic airfoil: grid pitch s=70mm, installation angle β s =67°, chord length c / s=2.5, that is, chord length c=175mm.
[0048] SS3. According to the selection criterion of the thr...
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The invention relates to a supersonic blade cascade blade design method suitable for high inlet relative Mach number, which can be used for supersonic blade type design with inlet Mach number not lower than 1.7. The method combines the unique angle of attack of the supersonic blade cascade By controlling the key parameters of the ultrasonic cascade modeling, the pressure surface and the suction surface can be directly constructed, and the shock angle of the extended wave in the leading edge of the cascade can be accurately controlled, so as to realize the convective flow field. The control of the oblique shock wave system structure, and the designed ultrasonic cascade can accurately control the starting conditions of the cascade.
Description
technical field [0001] The invention relates to a modeling method of a supersonic cascade, in particular to a supersonic blade design method suitable for a high inlet relative Mach number, which can be used for the design of a supersonic blade whose inlet Mach number is not less than 1.7, through This method can directly construct the pressure surface and suction surface, and can accurately control the shock angle of the inward extension wave at the leading edge of the cascade. At the same time, the designed supersonic cascade can accurately control the start-up conditions of the cascade. Background technique [0002] The modeling method of the supersonic cascade is widely used in high-load trans / supersonic compressors. In order to increase the stage load of the compressor, the relative Mach number of the inlet of the compressor is getting higher and higher. When the relative Mach number of the inlet exceeds 1.7, the generation of the shock wave structure in the cascade will...
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IPC IPC(8): G06F30/17G06F30/20F04D29/26
CPCF04D29/26G06F30/17G06F30/20
Inventor 赵庆军孙小磊张锴赵巍崔伟伟
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI