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Electric spark machining method for small-size spaceflight impact type turbine blade fatigue sample

A technology of impingement turbines and fatigue samples, which is applied in the direction of electric processing equipment, metal processing equipment, manufacturing tools, etc., to achieve the effect of simple experimental verification procedures, extensive manufacturing channels, and convenient control of processing costs

Active Publication Date: 2021-03-09
BEIJING AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, on the basis of the existing manufacturing and processing methods, it is difficult to provide a convenient and cheap way for the design, processing and verification of small-sized aerospace impact turbine blade fatigue samples under laboratory conditions.

Method used

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  • Electric spark machining method for small-size spaceflight impact type turbine blade fatigue sample
  • Electric spark machining method for small-size spaceflight impact type turbine blade fatigue sample
  • Electric spark machining method for small-size spaceflight impact type turbine blade fatigue sample

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0054] Such as figure 1 Shown, the electrical discharge machining method of the small size aerospace impact type turbine blade fatigue sample of the present invention, the step comprises:

[0055] Step 1: Analyze the basic structure of the blade, understand the size and shape characteristics of each part of the blade, and the actual appearance of some blades is as follows figure 2 shown. Using the finite element method to calculate the mechanical response characteristics of the blade model, the mesh division is as follows Figure 7 As shown in (a), on this basis, the part of the leading edge of the blade close to the blade root is selected as the fatigue life assessment site.

[0056] Step 2, use CATIA three-dimensional drawing software to draw the blade fatigue sample model, and use AutoCAD two-dimensional drawing software to complete the drawing design of the blade fatigue sample, such as image 3 shown.

[0057] When drawing the fatigue sample model, design the experim...

Embodiment approach

[0072] Its specific implementation is as follows:

[0073]The first step: Use a CNC lathe to process the metal bar into a workpiece directly used for EDM machining. The workpiece consists of three sections, the middle section is a cylindrical section, and there is a clamping section at each end. The cylindrical section and the clamping section There is a transition link between the sections, and the slope angle of the transition link is 45°, such as Figure 5 as shown in (a);

[0074] The second step: use the electric discharge machine tool to install the workpiece processed in the first step on the Figure 5 In the station shown in (b), it is used in the way of oil immersion processing Figure 4 The processing electrode for the transition section on the pressure side shown in (a-1) completes the machining of the transition section on the pressure side. For the specific forming process, see Figure 5 Medium (b-1);

[0075] Step 3: Keep the station in the second step, use t...

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Abstract

The invention discloses an electric spark machining method for a small-size spaceflight impact type turbine blade fatigue sample. The electric spark machining method comprises the steps of blade modelcharacteristic analysis, fatigue sample drawing design, machining electrode design, an electric spark machining mode and blade sample surface observation and deep treatment. After the sample is machined, blade deformation behavior calculation and analysis are carried out by combining finite element software to obtain a stress-strain state of an examination part, so that a fatigue verification experiment is guided, and the method is used for researching characteristics related to reusability of a spaceflight impact type turbine blade. The blade sample is directly formed, and the design requirement and the machining quality of the sample are fundamentally guaranteed. Machining tools are wide in manufacturing channel, and the machining cost and the sample machining number are convenient to control. Finite element calculation and analysis and fatigue sample surface microstructure observation guarantee the credibility of a fatigue experiment result. The difficulty of designing and machining the small-size spaceflight impact type turbine blade fatigue sample is overcome to a great extent.

Description

technical field [0001] The invention belongs to the research field of reusability of gas turbine hot end components, and relates to an electric discharge machining method for a small-scale aerospace impact turbine blade fatigue sample, which can be used for small-scale impact turbine blade fatigue or aerodynamic related theories and experimental research. Background technique [0002] With the development of commercial aerospace and aerospace science and technology, research on reusable space vehicles has attracted more and more attention. As a key component of a liquid rocket engine, the experimental study of the fatigue life of the turbine blade is crucial to determine the reusability of the engine. Compared with the aerospace impingement turbine blades, the turbine blades in the aerospace field are larger in size, and casting or welding methods are generally used to design and process fatigue samples. The welding process will cause damage to the structure of small-sized...

Claims

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Application Information

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IPC IPC(8): B23H9/10B23H11/00
CPCB23H9/10B23H11/00
Inventor 刘士杰梁国柱康红雷李子亮庞红丽刘继超叶莺樱
Owner BEIJING AEROSPACE PROPULSION INST
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