Alpha + beta type two-phase titanium alloy for aero-engine fan blade and preparation method of alpha + beta type two-phase titanium alloy

A technology for aero-engines and fan blades, applied in the field of titanium alloys, can solve problems such as poor superplasticity and difficult diffusion connection control, and achieve the effects of improving tissue uniformity, reducing weight and increasing efficiency, and reducing weight

Active Publication Date: 2021-06-04
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
View PDF7 Cites 6 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The embodiment of the present invention provides an α+β-type two-phase titanium alloy for aeroengine fan blades and a preparation method thereof. Through chemical composition design and microstructure regulation, its plasticity is equivalent to that of Ti-6Al-4V all

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
  • Alpha + beta type two-phase titanium alloy for aero-engine fan blade and preparation method of alpha + beta type two-phase titanium alloy
  • Alpha + beta type two-phase titanium alloy for aero-engine fan blade and preparation method of alpha + beta type two-phase titanium alloy
  • Alpha + beta type two-phase titanium alloy for aero-engine fan blade and preparation method of alpha + beta type two-phase titanium alloy

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0037] Example 1

[0038] A air engine fan blades with α + β-type two-phase titanium alloy, including the following chemical composition according to mass ratios: 0.2% to 5.6%, vanadium 7.5% ~ 8.8%, oxygen 0.18% ~ 0.24%, iron ≤ 0.5% , Niobium ≤1%, silicon 0.4% ~ 0.8%, carbon ≤ 0.05%, nitrogen ≤ 0.05%, hydrogen ≤ 0.015%, the rest is titanium and impurity elements.

[0039] Preparation method of α + β-type two-phase titanium alloy with an aviation engine fan blades, including the following steps:

[0040] S1, by quality ratio acquisition: 0.2% ~ 5.6%, vanadium 7.5% ~ 8.8%, oxygen 0.18% ~ 0.24%, iron ≤ 0.5%, niobium ≤1%, silicon 0.4% ~ 0.8%, carbon ≤ 0.05%, nitrogen ≤ 0.05%, hydrogen ≤ 0.015%, the rest is titanium and impurity elements;

[0041] S2, the raw material of each chemical component is made into a titanium alloy ingot by three vacuum self-consuming smelting, and then the β transition temperature of the titanium alloy ingot is measured, the titanium alloy ingot is heated to ...

Example Embodiment

[0056] Example 2

[0057] The difference between the present embodiment and the first embodiment is that in step S3, the titanium alloy ingot is heated to the β phase change point of 30 ° C to 50 ° C, and under the conditions of the preset deformation, The titanium alloy ingot is performed in the second stage of the second stage, so that the edges of the titanium alloy ingot and the center of the heart are uniform. This embodiment regarding the improvement of step S3 is an alternative scheme of step S3 in Example 1. Please refer to figure 2 The test results show that the tensile strength, yield strength, elongation, section shrinkage and elastic modulus are 1137 MPa, 1063 MPa, 12.3%, 46.9% and 116GPa, and their plasticity and stiffness are comparable to the Ti-6Al-4V alloy. The tensile strength is greater than 1100 MPa. Adaptability of blade forming process shows that its superplasticity and diffusion connection properties also meet the needs of superplastic forming / proliferatio...

Example Embodiment

[0058] Example 3

[0059] The difference from the first embodiment is that the titanium alloy ingot is heated to 50 ° C to 80 ° C below the β phase change point, and the six-fire secondary phase is taken upset in α + β. To obtain a complete crushing of a small uniform blank tissue to obtain a titanium alloy material. This embodiment regarding the improvement of step S5 is an alternative to step S5 in Example 1. Please refer to image 3 The test results show that its tensile strength, yield strength, elongation, section shrinkage and elastic modulus are 1121 MPa, 1033 MPa, 13.6%, 44.7% and 112GPa, and its plasticity and stiffness are comparable to the Ti-6Al-4V alloy. The tensile strength is greater than 1100 MPa. Adaptability of blade forming process shows that its superplasticity and diffusion connection properties also meet the needs of superplastic forming / proliferation.

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

PropertyMeasurementUnit
Tensile strengthaaaaaaaaaa
Elastic modulusaaaaaaaaaa
Tensile strengthaaaaaaaaaa
Login to view more

Abstract

The invention relates to an alpha + beta type two-phase titanium alloy for an aero-engine fan blade and a preparation method of the alpha + beta type two-phase titanium alloy for the aero-engine fan blade. The preparation method of the alpha + beta type two-phase titanium alloy for the aero-engine fan blade comprises the following steps that S1, the following chemical components are obtained: 4.2%-5.6% of aluminum, 7.5%-8.8% of vanadium, 0.18%-0.24% of oxygen, less than or equal to 0.5% of iron, less than or equal to 1% of niobium, 0.4%-0.8% of silicon, less than or equal to 0.05% of carbon, less than or equal to 0.05% of nitrogen, less than or equal to 0.015% of hydrogen and the balance of titanium and impurity elements; S2, the titanium alloy cast ingot is subjected to first-stage upsetting and drawing; S3, under the conditions of the preset temperature and the preset deformation amount, after reversing is conducted, second-stage upsetting and drawing are conducted on the titanium alloy cast ingot; S4, the titanium alloy cast ingot is heated to the temperature above the phase transformation point, and then the titanium alloy cast ingot is subjected to third-stage upsetting and drawing; S5, the titanium alloy cast ingot is heated to the temperature below the phase transformation point, then fourth-stage upsetting and drawing are conducted on the titanium alloy cast ingot, and a titanium alloy material is obtained; and S6, the titanium alloy material is subjected to heat treatment. The preparation method is applied to the technical field of titanium alloys.

Description

technical field [0001] The invention relates to the technical field of titanium alloys, in particular to an α+β type two-phase titanium alloy for aeroengine fan blades and a preparation method thereof. Background technique [0002] Titanium alloy has become one of the main structural materials of advanced aircraft and engines because of its excellent comprehensive performance matching such as high specific strength, modulus, toughness, high damage tolerance, corrosion resistance and weldability. [0003] Improving the thrust-to-weight ratio and efficiency is the continuous goal of aero-engines, and fan blades are one of the key rotating parts of advanced aero-engines. Since the 1960s and 1970s, aero-engine companies in the United Kingdom, the United States and other Western countries began to develop and use titanium alloy materials and special forming processes to manufacture wide-chord hollow fan blades. After a lot of design, processing and experimental research, it has g...

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): C22C14/00C22C1/02C22F1/18
CPCC22C14/00C22C1/02C22F1/183
Inventor 刘运玺李志强陈玮韩晓宁杜立华周琳
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

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

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap