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Aero-engine turbine blade hot isostatic pressing near-net forming method

A technology for aero-engines and turbine blades, which is applied to turbines, mechanical equipment, etc., can solve the problems of high manufacturing costs and low yields, and achieve the effects of reducing production costs, high yields, and ensuring the density of blades

Pending Publication Date: 2021-11-19
SINO EURO MATERIALS TECH OF XIAN CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a near-net hot isostatic pressing method for aero-engine turbine blades, which solves the problems of low yield and high manufacturing cost in the preparation of aero-engine low-pressure turbine blades in the prior art

Method used

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  • Aero-engine turbine blade hot isostatic pressing near-net forming method
  • Aero-engine turbine blade hot isostatic pressing near-net forming method
  • Aero-engine turbine blade hot isostatic pressing near-net forming method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0051] According to an air engine turbine blade, the heat and other static pressing method, which is implemented in accordance with the following steps:

[0052] Step 1, the package is designed, and the package is branched by the body convex 1 and the main body recess 2, and the middle portion of the main body convex 1 forms a protrusion that matches the blade portion of the turbine blade, and the central portion of the main body concave 2 is formed with a turbine. The cavity of the blade is matched, and both ends of the main body convex 1 and the two ends of the body recess are formed with a semi-cavity that matches both ends of the turbine blade; the main body convex 1 and the main body recess 2 The lower cover 6 and the upper cover 3 are provided, and there is a feed tube 4 in the upper cover 3;

[0053] Step 2, the Ti4822 alloy powder is filled in the package obtained in step 1, and the Ti4822 alloy powder is sufficiently resolved until the cavity and the half cavity are fille...

Embodiment 2

[0060] According to an air engine turbine blade, the heat and other static pressing method, which is implemented in accordance with the following steps:

[0061] Step 1, the package is designed, and the package is branched by the body convex 1 and the main body recess 2, and the middle portion of the main body convex 1 forms a protrusion that matches the blade portion of the turbine blade, and the central portion of the main body concave 2 is formed with a turbine. The cavity of the blade is matched, and both ends of the main body convex 1 and the two ends of the body recess are formed with a semi-cavity that matches both ends of the turbine blade; the main body convex 1 and the main body recess 2 The lower cover 6 and the upper cover 3 are provided, and there is a feed tube 4 in the upper cover 3;

[0062] Step 2, the Ti4822 alloy powder is filled in the package obtained in step 1, and the Ti4822 alloy powder is sufficiently resolved until the cavity and the half cavity are fille...

Embodiment 3

[0069] According to an air engine turbine blade, the heat and other static pressing method, which is implemented in accordance with the following steps:

[0070] Step 1, the package is designed, and the package is branched by the body convex 1 and the main body recess 2, and the middle portion of the main body convex 1 forms a protrusion that matches the blade portion of the turbine blade, and the central portion of the main body concave 2 is formed with a turbine. The cavity of the blade is matched, and both ends of the main body convex 1 and the two ends of the body recess are formed with a semi-cavity that matches both ends of the turbine blade; the main body convex 1 and the main body recess 2 The lower cover 6 and the upper cover 3 are provided, and there is a feed tube 4 in the upper cover 3;

[0071] Step 2, the Ti4822 alloy powder is filled in the package obtained in step 1, and the Ti4822 alloy powder is sufficiently resolved until the cavity and the half cavity are fille...

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Abstract

The invention discloses an aero-engine turbine blade hot isostatic pressing near-net forming method. The aero-engine turbine blade hot isostatic pressing near-net forming method is characterized by comprising the following steps that 1, a sheath is designed; 2, the sheath obtained in the step 1 is filled with metal powder, and the metal powder is fully compacted until a concave cavity and a half cavity are filled with the metal powder; 3 the sheath obtained in the step 2 is heated and vacuumized, and then a body convex part and a body concave part are welded and sealed; 4, the sheath obtained in the step 3 is put into a hot isostatic pressing furnace to be subjected to hot isostatic pressing densification treatment; 5, the sheath obtained in the step 4 is subjected to acid corrosion removal, and a blade blank is obtained; 6, vacuum heat treatment is carried out on a blade blank obtained in the step 5; and 7, tenon and blade crown machining is conducted on the two ends of the blade blank obtained in the step 6, and an aero-engine turbine blade is obtained.

Description

Technical field [0001] The present invention belongs to the technical field of aviation generator blade, and is specifically involved in an air engine turbine blade heat and the like. Background technique [0002] Aviation engine low pressure turbine blades are an important component of an aerospace engine turbine. The manufacturing method of low pressure turbine blades is mainly: precision casting type, equal temperature mode forging, and additive manufacturing. Among them: (1) The main problem of precision casting process is that the blade is easy to generate loose, inclusion and other metallurgical defects, and the dimensional accuracy control of the blade is also more difficult, so the TIAL alloy turbine blade prepared by precision cast processes is passed. In particular, the initial stage of development is lower. Further, the microstructure of the cast blade is relatively large (for example, the casting tissue of Ti4822 alloy), according to the different parts of the blade, ...

Claims

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Application Information

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IPC IPC(8): B22F3/15B22F5/04B22F3/24
CPCB22F3/15B22F5/04B22F3/24B22F2003/153B22F2003/248
Inventor 张国栋唐洪奎杨超罗成卓君梁书锦赖运金王庆相
Owner SINO EURO MATERIALS TECH OF XIAN CO LTD