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Compressor blades, compressors and aeroengines

A technology of compressors and blades, applied in the direction of machines/engines, liquid fuel engines, mechanical equipment, etc., can solve the problem that the blade shape is difficult to obtain a good flow condition, and achieve the effect of air separation

Active Publication Date: 2017-06-16
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology

[0004] For modern high-performance aviation axial flow compressors and fans, due to the further increase of incoming flow velocity and load, it is difficult to obtain good flow conditions and reduce losses by using conventionally designed airfoils.

Method used

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  • Compressor blades, compressors and aeroengines
  • Compressor blades, compressors and aeroengines
  • Compressor blades, compressors and aeroengines

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Embodiment Construction

[0026] Those skilled in the art can know according to the law of conservation of mass commonly used in the field of aerodynamics: G=ρVA, wherein, G is the mass flow rate, ρ is the gas density, and V is the airflow velocity. Figure 9 Shown), A the air flow area between two adjacent blades. dA / A is the area change gradient. According to the above formula, when the density ρ is constant, -dA / A=dV / V. In a compressor, kinetic energy is converted to pressure energy. That is, a change in velocity is converted into a change in pressure. There are the following ways, namely Accordingly, it is not difficult to understand that when the airflow flows between two adjacent blades (refer to e.g. Figure 9 The basic blade flow shown), the reverse pressure gradient is basically positively correlated with the area change gradient. In cascade channel flow, when the area change gradient is large, the reverse pressure gradient is large, and airflow separation is easy to occur. The reason wh...

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Abstract

The invention relates to a compressor blade, a corresponding compressor and an aero-engine, and aims to solve the air flow separation problem of the existing compressor blade. According to the present invention, by designing the compressor blade to have a local thickness reduction, that is, the thickness curve has at least three inflection points, the technical effect of reducing the airflow separation of the blade is successfully achieved.

Description

technical field [0001] The invention relates to a compressor blade, a compressor with the blade and a corresponding aeroengine. Background technique [0002] Modern civil aero-engines are developing toward the goals of low fuel consumption, low cost, and low emissions, which requires the compressor to have the characteristics of high pressure ratio and high efficiency. Those skilled in the art should be able to understand that the term "compressor efficiency" refers to the proportional coefficient of how much the reduced kinetic energy is converted into adiabatic compression work when the airflow velocity in the diffuser cascade decreases. In order to achieve high pressure ratio and high efficiency, it is necessary to have good aerodynamic design performance and structural form in the design of the compressor. The flow parameters on the meridian surface can be obtained after the one-dimensional and S2 flow design of the compressor. Whether it is to realize the flow charact...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/38
Inventor 许峰雷丕霓陈美宁李游王青
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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