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 f

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

Example Embodiment

[0053] Embodiment:

[0054] Such as figure 1 As shown, the small size space impact turbine blade fatigue sample of the present invention, the steps include:

[0055] Step 1, the basic structure of the blade is analyzed, understand the size, shape characteristics of the deposited parts of the blade, and some vane actual appearance figure 2 Indicated. The mechanical response characteristics of the blade model are calculated using finite element methods, and the mesh is divided. Figure 7 In the middle (a), the leading edge of the blade is selected as the fatigue life assessment site on this basis.

[0056] Step 2, using the Catia three-dimensional drawing software to draw the blade fatigue sample model, use the AutoCAD two-dimensional drawing software to complete the drawings of the blade fatigue sample, such as image 3 Indicated.

[0057] When drawing the fatigue sample model, the design of the fatigue sample is analyzed according to the characteristics of the blade, ensuring th...

Example Embodiment

[0072] The specific embodiment is as follows:

[0073]The first step: Using a CNC lathe to process the metal bar into a workpiece for the machining of the electric spark machine, the workpiece is composed of three sections, and the middle is a cylindrical section, and each end has a clamping section, a cylindrical section and clamping. The segment is a transitional link, the rampous angle of the transition section is 45 °, such as Figure 5 Displayed in (a);

[0074] Step 2: Using the electric spark machine, install the workpiece of the first step processing Figure 5 On the station shown in (b), it is used in a manner in which it is used. Figure 4 The pressure surface-side transition section of the medium (A-1) completes the processing of the pressure plane transition section, the specific molding process is seen Figure 5 Central (B-1);

[0075] Step 3: Maintain the second step, use the electric spark machine, use the way of immersion processing Figure 4 The pressure surface s...

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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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