Error compensation method for integral turbine blade machining based on mathematical model reconstruction

A technology for turbine blades and machining errors, which is applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as machining accuracy out of tolerance, and achieve the effects of controlling machining errors, high efficiency, and good consistency

Inactive Publication Date: 2012-11-07
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the processing accuracy of the existing aero-engine integral turbine blades is out of tolerance due to the difficulty in controlling the amount of elastic recovery. The blades processed by this method have the advantages of high precision, good consistency after processing multiple blades, and high efficiency, and are suitable for machining error compensation of integral turbine blade parts.

Method used

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  • Error compensation method for integral turbine blade machining based on mathematical model reconstruction
  • Error compensation method for integral turbine blade machining based on mathematical model reconstruction
  • Error compensation method for integral turbine blade machining based on mathematical model reconstruction

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Experimental program
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Effect test

Embodiment 2

[0072] Such as Figure 5 Shown.

[0073] The difference between this embodiment and the first embodiment is that the experimental method is used to reconstruct the processed digital model of the blade. The reconstruction process is as follows:

[0074] Step 201: Trial cutting one blade on the turbine according to the predetermined process parameters, and verify the rationality of the numerical control program and clamping method. After curing the processing parameters, try cutting 3 blades again.

[0075] Step 202: Use a coordinate measuring machine to measure the error at each cross-section control point, and save it as a text file, and record one control point coordinate per line.

[0076] Step 203: Determine whether the blade error is out of tolerance. If it is not out of tolerance, go directly to step 206. If it is out of tolerance, go to step 204.

[0077] Step 204: According to the coordinate position of the original control point and the corresponding error point, the mirrorin...

Embodiment 3

[0086] Such as Image 6 Shown.

[0087] This embodiment is a combination of the first and second embodiments. It reconstructs the processing digital model through theoretical calculations and actual measurements, verifies whether the theoretical calculations are correct through experimental data, and then uses theoretical calculations to determine whether the deviation of the experimental data is Satisfy the calculation requirements, that is, the overall turbine blade machining error compensation is performed through the hybrid method. It is a combination of calculation method and test method. For specific steps, please refer to steps 101-105 and 201-206.

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Abstract

The invention relates to an error compensation method for integral turbine blade machining based on mathematical model reconstruction, belonging to the technical field of error compensation of part machining in mechanical engineering. In the method, the theoretic mathematical model of blades is reconstructed before the blade machining, and the error of the blade machined through the reconstructedmathematical model is largely reduced so as to greatly improve the precision of the blade machining. The error compensation process is completed before the machining and the machining process keeps unchanged and has high feasibility. In addition, multiple blades on an integral turbine are good in machining conformity without needing manual repairing, thus the method has high efficiency.

Description

Technical field [0001] The invention relates to a method for compensating machining errors of turbine blades, in particular to a machining digital model (that is, mathematical model, the same below) after elastic recovery is obtained through error compensation calculation or measurement, and then machining errors according to the machining digital model The compensation method is specifically a method for compensating the machining error of the overall turbine blade based on digital-analog reconstruction. Background technique [0002] A large number of various integral structural parts are used in new aero-engines, such as integral turbines. Compared with discrete built-in assemblies, integral turbine structural parts have no discrete component connection. The number of parts is greatly reduced, the quality is significantly reduced, and the reliability is significantly improved. The thrust-to-weight ratio, life and safety of the engine are greatly improved. However, the overall ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 郝小忠何磊耿习琴鲍益东王珉
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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