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Pneumatic power design method for big and small blade compressor

A technology of aerodynamic design and compressor, applied in the direction of calculation, special data processing application, instrument, etc., can solve the problem of optimizing the geometric parameters of large and small blades of compressors with large and small blades, and achieve the optimization of geometric parameters and optimization of design data. Effect

Inactive Publication Date: 2008-04-09
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] It is difficult to optimize the geometric parameters of the large and small blades of the compressor with large and small blades

Method used

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  • Pneumatic power design method for big and small blade compressor
  • Pneumatic power design method for big and small blade compressor

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Embodiment Construction

[0024] The aerodynamic design method of the large and small blade compressor of the present invention, its preferred specific implementation is as shown in Figure 1, comprising:

[0025] Step 1. Input the parameter information required for the aerodynamic design, including whether the compressor to be aerodynamic designed is a large or small blade compressor.

[0026] The parameter information includes the following parameters: the chord length of the small blade, the position of the leading edge and the trailing edge of the small blade, the relative circumferential position of the small blade in the channel of the large blade, the distribution of the leading edge and the trailing edge of the small blade in the radial direction, the meridian of the small blade The surface coordinates, as well as the number of blades, blade shape, etc., may include one or more of these parameters as required, and may also include other parameters.

[0027] Step 2. Determine whether the compress...

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Abstract

The invention discloses an aerodynamic design method of large-small leaf compressors, which includes that firstly, input the parameter information needed for the aerodynamic design, including the information whether the compressor needing the aerodynamic design is a large-small leaf compressor or not; then, judge whether the compressor needing the aerodynamic design is an identical leaf compressor or a large-small leaf compressor, if being a large-small leaf compressor, define the parameters according to the aerodynamic design method of large-small leaf compressors, including the relative circumferential position of the small leaf between the two adjacent large leaves P1=S1 / S and the consistency P3=(C1+C) / S; thereafter, calculate by using throughflow method and optimize the design data by using convergence theorem. The invention can realize the optimization design on the geometric parameters of large and small leaves.

Description

technical field [0001] The invention relates to a compressor design technology, in particular to an aerodynamic design method of a compressor with large and small blades. Background technique [0002] Compressors are a classification of turbomachinery, and vane compressors are generally used to pressurize gases. A rotating impeller with a row of blades and a row of stationary blades behind it are called the first stage of the compressor. When it is necessary to pressurize the gas to a higher level, a multi-stage compressor is usually used. For one of the stages In terms of gas flow, it can be divided into axial flow, centrifugal and diagonal flow compressors. The air flow mode of axial flow compressor is axial intake and axial exhaust; the flow mode of centrifugal compressor gas is axial intake and radial exhaust; the diagonal flow compressor is axial flow and centrifugal compressor. The compromise of the machine, the axial intake, and the exhaust at a certain angle with t...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 陈懋章严明刘宝杰刘火星王洪伟
Owner BEIHANG UNIV