A compressor stability boundary judgment method considering the influence of intake total pressure distortion

A technology that stabilizes boundaries and compressors, applied in the field of aviation systems, can solve problems such as poor performance, and achieve the effect of reducing development cycle, development cost and risk

Active Publication Date: 2019-05-28
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Koch's method is suitable for the judgment of the stability boundary of the compressor under uniform intake conditions, but not for the distortion of the total intake pres...

Method used

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  • A compressor stability boundary judgment method considering the influence of intake total pressure distortion
  • A compressor stability boundary judgment method considering the influence of intake total pressure distortion
  • A compressor stability boundary judgment method considering the influence of intake total pressure distortion

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Embodiment

[0086] The specific process is as follows:

[0087] (1) According to the geometric data of each row of blades of the compressor design results, the maximum steady-state aerodynamic load H of each compressor under different design parameters under uniform air intake conditions max , Among which, the design parameters include aspect ratio, consistency, leaf shape; and according to figure 2 The calculation method shown obtains the dimensionless diffusion length of each stage of the compressor rotor blade

[0088] (2) Change the compressor And H max Construct an array, use the least square method to obtain a fitting curve for this value, and use this fitting curve to obtain the maximum steady-state aerodynamic load H of each stage of the compressor ef (θ); change the compressor And H max Construct an array, use the least square method to obtain a fitting curve for this value, and use this fitting curve, such as figure 1 As shown, obtain the maximum steady-state aerodynamic load H o...

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Abstract

The invention discloses a compressor stability boundary judgment method considering the influence of intake total pressure distortion, which comprises the following steps of obtaining the maximum stable state aerodynamic load Hmax of each stage of a compressor and the dimensionless diffusion length of each stage of rotor blade, and obtaining the maximum stable state aerodynamic load Hef (theta) ofeach stage of the compressor; solving the effective stable state pneumatic load of the critical distortion angle of the gas compressor under the gas inlet distortion condition; if the load is smallerthan Hmax, determining that the gas compressor is still in a stable working state, if the load is larger than Hmax, determining that the gas compressor enters an unstable state, wherein the working point of the last stable working state is considered as a stable boundary point under the current rotating speed; and repeating the steps to finally obtain the stable boundary points at different rotating speeds, and connecting the stable boundary points to obtain the stable boundary of the gas compressor. The method can quickly and accurately predict the stable boundary of the gas compressor underthe condition of inlet gas total pressure distortion, can be used in the initial stage of gas compressor design, can reduce the development cycle of the gas compressor, and reduces the development cost and risk.

Description

Technical field [0001] The invention relates to a method for analyzing the internal aerodynamic flow state of an aero engine compressor, and belongs to the technical field of aviation systems. Background technique [0002] The compressor is the core component of an aero engine. During use, it is in a stable working state under normal conditions. However, under special circumstances such as aircraft maneuvering, takeoff at a high angle of attack, or missile launch, the compressor operating point will cross the stability boundary , The occurrence of aerodynamic instability such as rotating stall and surge, resulting in a significant drop in the thrust of the aero engine, and at the same time, it will cause great damage to the structure of the engine. Therefore, in the design process of the compressor, it is necessary to analyze the aerodynamic stability of the compressor. The first is to accurately know the position of the compressor stability boundary under uniform intake conditio...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 屠宝锋胡骏郭晋徐蓉付文军王昊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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