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Compressor blade reverse implementation method for correcting multi-dimensional processing error

A technology of machining error and realization method, which is applied in the direction of using mechanical devices, mechanical measuring devices, measuring devices, etc., can solve the problem of inability to determine blade benchmarks, shorten the time for reverse design of compressor blades, and inability to reverse multi-dimensional processing errors. It can save the cost of blade measurement and data processing, shorten the design time, and improve the quality of the blade.

Active Publication Date: 2016-11-16
SHANGHAI JIAO TONG UNIV
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  • Description
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AI Technical Summary

Problems solved by technology

[0004] Aiming at the defects of the prior art that the blades cannot be determined when the blades are installed in the whole compressor, and the compressor blades with multi-dimensional processing errors cannot be reversed, a reverse method for correcting multi-dimensional processing errors of the compressor blades is proposed. The implementation method can save a lot of blade measurement and data processing costs, greatly shorten the time of reverse design of compressor blades, and improve the quality of blades

Method used

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  • Compressor blade reverse implementation method for correcting multi-dimensional processing error
  • Compressor blade reverse implementation method for correcting multi-dimensional processing error
  • Compressor blade reverse implementation method for correcting multi-dimensional processing error

Examples

Experimental program
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Embodiment 1

[0041] like figure 1 As shown, this embodiment includes the following steps:

[0042] 1) Select the measurement benchmark:

[0043] 1.1) Determining the x-axis from component condition measurements with the blades located in the compressor component. The rotor blades and stator blades of the compressor are divided into two types: detachable and non-detachable. Non-detachable blades, such as the integral blisk type of the rotor blade, and the integral welded type of the inner and outer rings of the stator blade. Whether it is a detachable blade or a non-detachable blade, the x-axis can be determined using blade assembly state measurements. The front and rear end surfaces of the blade assembly are rotating planes. First, according to the structural characteristics of the assembly, determine the center line of the assembly, that is, the axis of the compressor, and measure the roundness of the spigot as a reference. The spigot is the cylindrical surface that the assembly fits ...

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Abstract

The invention discloses a compressor blade reverse implementation method for correcting multi-dimensional processing errors. The compressor blade reverse implementation method comprises the steps of: 1) selecting a measuring basis; 2) measuring blade body profiles of cross sections at different heights; 3) carrying out primary processing on blade profile parameters; 4) stacking the blade body profiles according to a stacking law; 5) performing smoothing treatment on the blade body profiles of a designed blade to form a designed blade entity; 6) and adjusting a curvature comb along the blade height, performing smoothing treatment on the blade body profiles again, and carrying out a next step if the blade body profiles conform to design requirement, otherwise, returning to the step 2). The compressor blade reverse implementation method saves a lot of blade measurement and data processing costs, greatly shortens the time for compressor blade reverse design, and improves the blade quality.

Description

technical field [0001] The invention relates to a technology in the field of blade compressor design, in particular to a method for realizing the reverse calculation of compressor blades for correcting multi-dimensional processing errors. Background technique [0002] The compressor is one of the key components of aviation and ground gas turbine engines. Its function is to add power and boost, that is, to compress the gas to increase the pressure. Its performance determines the performance of the entire engine to a large extent. and reliability. In the compressor, the blade is the part that realizes the energy conversion in the working of the compressor, and it is also the part with the largest number and the most complicated processing. The processing quality of the blade plays a vital role in the efficiency and aerodynamic stability of the current high-load designed compressor. effect. [0003] Since the compressor blade is a typical thin-walled part with complex bending...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B5/00G01B21/00
CPCG01B5/003G01B21/00
Inventor 滕金芳郑似玉羌晓青
Owner SHANGHAI JIAO TONG UNIV
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