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Axial flow compressor size calculation method considering blade mounting angle

A technology for installing axial flow compressors and blades, applied in complex mathematical operations, design optimization/simulation, geometric CAD, etc., can solve problems such as insufficient precision, large calculation errors, and inaccurate dimensions, so as to facilitate optimization iterations and shorten design The effect of the iteration cycle

Pending Publication Date: 2022-04-12
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

Although the existing calculation methods for size estimation of axial flow compressors take into account many influencing factors such as hub ratio and aspect ratio, there are still problems such as insufficient accuracy and large calculation errors in the calculation process. Accurate, which brings a lot of inconvenience to component designers when performing detailed design

Method used

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  • Axial flow compressor size calculation method considering blade mounting angle
  • Axial flow compressor size calculation method considering blade mounting angle
  • Axial flow compressor size calculation method considering blade mounting angle

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Embodiment 1

[0069] Embodiment 1: A method for calculating the size of an axial flow compressor with equal inner diameters considering the installation angle of the blades, comprising the following steps:

[0070] 101. According to the section parameters of the inlet stage of the axial flow compressor with equal inner diameters, the section parameters of the inlet stage rotor blades and the outlet stage of the axial flow compressor include: the Mach number of the inlet stage rotor blades is Ma in , the Mach number of the rotor blade at the exit stage is Ma out ; The rotor blade flow rate at the inlet stage is W in , the rotor blade flow rate at the outlet stage is W out ; The total temperature of the rotor blades at the inlet stage is T in , the total temperature of the rotor blades at the outlet stage is T out ; The total pressure of the rotor blades at the inlet stage is P in , the total pressure of the rotor blades at the outlet stage is P out ; The oil-gas ratio of the inlet stage...

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Abstract

The invention relates to a method for calculating the size of an equal-inner-diameter axial flow compressor by considering a blade mounting angle, which comprises the following steps of: forming a speed triangle according to inlet-stage section parameters of the equal-inner-diameter axial flow compressor, a blade tip tangential velocity UTin of an inlet-stage rotor blade obtained by calculation, and an airflow axial velocity Uzin of the inlet-stage rotor blade; according to the trigonometric function relation of the speed triangle, the installation angle ain of the inlet-stage rotor blade is obtained through calculation, and then the axial length Lgin of the inlet-stage rotor blade is obtained; and meanwhile, according to the characteristics of the equal-inner-diameter axial flow compressor, the axial length Lout of the outlet-stage rotor blade is obtained, and therefore the estimated total length size of the equal-inner-diameter axial flow compressor is obtained. According to the method, when the overall scheme of the aero-engine is designed, the influence factors of the blade mounting angle can be considered, and the size of the axial flow compressor can be quickly and accurately estimated.

Description

technical field [0001] The invention belongs to the field of aero turbine engines, in particular to a method for calculating the size of an axial flow compressor considering blade installation angles. Background technique [0002] The axial flow compressor is a key component of the aero turbine engine, and the size estimation of the axial flow compressor is an important link in the overall design technology of the aeroengine. Although the existing calculation methods for size estimation of axial flow compressors take into account many influencing factors such as hub ratio and aspect ratio, there are still problems such as insufficient accuracy and large calculation errors in the calculation process. Accurate, it brings a lot of inconvenience to component designers when they carry out detailed design. Contents of the invention [0003] The purpose of the present invention is to avoid the deficiencies of the prior art and provide an axial flow compressor that uses the blade...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/20G06F17/11
CPCY02T90/00
Inventor 陈玉春陈敏泽李孙洋
Owner NORTHWESTERN POLYTECHNICAL UNIV
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