Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

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, improving machining accuracy, and high efficiency

Inactive Publication Date: 2011-10-19
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
View PDF2 Cites 26 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • 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

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 2

[0072] like Figure 5 shown.

[0073] The difference between this embodiment and Embodiment 1 is that the numerical model of blade processing is reconstructed by using the experimental method, and the reconstruction process is as follows:

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

[0075] Step 202: Use a three-coordinate measuring machine to measure the errors at the control points of each section, and save them in a text file, with each line recording the coordinates of one control point.

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

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

Embodiment 3

[0086] like Figure 6 shown.

[0087] This embodiment is a combination of Embodiments 1 and 2. It reconstructs the processing digital model through theoretical calculation and actual measurement, verifies whether the theoretical calculation is correct through experimental data, and then determines whether the deviation value of the experimental data is correct through theoretical calculation. To meet the calculation requirements, that is, to compensate the machining error of the overall turbine blade through the hybrid method. It is a combination of calculation method and test method. For specific steps, refer to steps 101-105 and steps 201-206.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

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 reconstructed mathematical 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 an error compensation calculation or measurement to obtain a machining digital model (that is, a mathematical model, the same below) after elastic recovery, and then process the error according to the processing digital model. The compensation method is specifically a method for compensating machining errors of integral turbine blades 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 embedded assemblies, integral turbine structural parts have no discrete component connection, greatly reduce the number of parts, significantly reduce quality, and significantly improve reliability. The thrust-to-weight ratio, service life and safety of the engine are greatly improved. However, the overall turbine works ...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
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
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com