Single-alloy double-performance turbine disc of aero-engine and preparation method of single-alloy double-performance turbine disc

An aero-engine, dual-performance technology, used in engine components, machines/engines, turbines, etc., can solve problems such as difficult control and complex preparation processes, and achieve good room temperature tensile properties, superior high temperature properties, high temperature creep resistance Excellent variable performance

Active Publication Date: 2020-12-11
CHANGSHA ADVANCED MATERIALS IND RES INST CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention provides an aero-engine single-alloy dual-performance turbine disk and its preparation method, which is used to overcome the complexity of the preparation process in the prior art, and the control difficulty is relatively high major defects

Method used

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  • Single-alloy double-performance turbine disc of aero-engine and preparation method of single-alloy double-performance turbine disc

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preparation example Construction

[0029] The present invention also proposes a method for preparing a single-alloy dual-performance turbine disk for an aero-engine, comprising:

[0030] S1: Construct a 3D model of a single-alloy dual-performance turbine disk using 3D graphics software;

[0031] S2: Divide the 3D model from the side near the turbine shaft outwards into the core area, the web area and the disk edge area, and mark the area on the 3D model, as shown in figure 1 shown;

[0032] S3: Use layering software to cut and layer the 3D model after region marking along the height direction to obtain N slice models; each slice model contains region marks;

[0033] Preferably, in step S3, the thickness of the sheet model is 50-150 μm, and the degree of melting of each layer is controlled by controlling the thickness of the sheet, so that each layer reaches an optimal melting state.

[0034] S4: Along the height direction of the three-dimensional model, starting from the lowest layer model, the electron beam ...

Embodiment 1

[0067] This embodiment provides an aero-engine single-alloy dual-performance turbine disk, which is composed of TiAl alloy; the single-alloy dual-performance turbine disk includes a disk core, a web and a disk edge from the side near the turbine shaft to the outside, and the disk core is double-state tissue, the disc edge is a full-thickness sheet tissue, and the radial plate is a transition state between a two-state tissue and a full-thickness sheet tissue.

[0068] This embodiment also provides a method for preparing the above-mentioned single-alloy dual-performance turbine disk, including:

[0069] S1: Construct a 3D model of a single-alloy dual-performance turbine disk using the 3D graphics software Magics;

[0070] S2: Divide the three-dimensional model from the side near the turbine shaft outward into the core area, the web area and the flange area, and mark the area on the three-dimensional model, and then save it as a file with the suffix .stl;

[0071] S3: Import the...

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Abstract

The invention discloses a single-alloy double-performance turbine disc of an aero-engine and a preparation method of the single-alloy double-performance turbine disc. The turbine disc is composed of TiAl alloy and sequentially comprises a disc core, a spoke plate and a disc edge from the side close to a turbine shaft to the outside, the disc core is of a double-state structure, the disc edge is ofa full-lamellar structure, and the spoke plate is of a transition state of the double-state structure and the full-lamellar structure; and the preparation method comprises the following steps of firstly, constructing a three-dimensional model of the single-alloy dual-performance turbine disc by adopting three-dimensional cartographic software, and then scanning by adopting an electron beam melting mode according to the three-dimensional model to obtain the single-alloy dual-performance turbine disc. According to the single-alloy double-performance turbine disc provided by the invention, two different structures can be realized by only adopting one alloy so as to meet different requirements of disc core and disc edge service conditions; and according to the preparation method provided by the invention, the integral one-step forming of the double-structure turbine disc can be realized by adopting the electron beam melting mode, the preparation process is simplified, and the production efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of aero-engine manufacturing, in particular to an aero-engine single-alloy dual-performance turbine disc and a preparation method thereof. Background technique [0002] The working conditions of the aeroengine turbine disk are more complex. The working temperature of the disk core is low, it is subjected to the torsion of the turbine shaft, and bears a large centrifugal force load, so the disk core is required to have higher strength. However, the edge of the disk is close to the turbine blade, exposed to high-temperature gas, and has a high working temperature. Therefore, the edge of the disk needs to have excellent creep resistance and durability. The different service conditions of the disk core and the disk flange put forward different requirements for the materials. The disk body of the dual-performance turbine disk has different structures in different parts. The disk core is a fine-grained structure...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/02F01D25/00B22F5/00B22F3/105B33Y10/00B33Y50/02B33Y80/00
CPCF01D5/02F01D25/005F01D25/00B22F5/009B33Y10/00B33Y50/02B33Y80/00Y02P10/25
Inventor 邓阳丕曹玄扬宰雄飞李晓庚周朝辉
Owner CHANGSHA ADVANCED MATERIALS IND RES INST CO LTD
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