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Locally-free-telescopic single crystal blade-used complex-structured ceramic core preparation technology

A technology for ceramic cores and single crystal blades, which is applied in the field of superalloys to achieve the effects of reducing production costs, good economic benefits and engineering application prospects, and ensuring overall integrity

Active Publication Date: 2015-05-27
SHENYANG POLYTECHNIC UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Single-crystal alloy blades can be used at higher temperatures because they remove the influence of grain boundaries, usually 30°C higher than oriented alloy blades, and nearly 100°C higher than polycrystalline blades, but this still cannot fully meet the requirements of the modern aviation industry

Method used

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  • Locally-free-telescopic single crystal blade-used complex-structured ceramic core preparation technology
  • Locally-free-telescopic single crystal blade-used complex-structured ceramic core preparation technology

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0039] At first select quartz glass tube as 2# ceramic core, its diameter is 1 millimeter, 2 # ceramic core 2 sides are coated with wax film thickness to be 10 microns, and core end face is coated with wax mold thickness and is 0.5 millimeter;

[0040] 1# and 3# ceramic cores are made of silica material. 1# ceramic core 1 and 3# ceramic core 3 need to reserve a seat hole 6 of the same size as ceramic core 2, the diameter of the seat hole is 10 microns larger than the diameter of 2# ceramic core 2, and the length of the seat hole is 1 mm; 1# ceramic core 1 and 3# ceramic core 3 have independent positioning core head 5, 2# ceramic core 2 is combined with 1# ceramic core 1 and 3# ceramic core 3 on 1# core The length of the outcrop L is 1 mm; the 2# ceramic core 2 is dip-coated with a thin layer of wax film as a whole, and then the 2# ceramic core 2 and the 1# ceramic core 1 and 3# after the dip-coated wax film are treated The ceramic core 3 is combined and put into the wax mold ...

Embodiment 2

[0043] First select the quartz glass tube as the 2# ceramic core, its diameter is 0.6 mm, the thickness of the wax film on the side of the ceramic core 2 is 5 microns, and the thickness of the wax mold on the end face of the core is 0.5 mm;

[0044] 1# and 3# ceramic cores are made of silica material. 1# ceramic core 1 and 3# ceramic core 3 need to reserve a seat hole of the same size as ceramic core 2, the diameter of the seat hole is 10 microns larger than the diameter of core 2, and the length of the seat hole is 1 mm; 1# Ceramic core 1 and 3# ceramic core 3 have independent positioning core heads, and the outcrop size on 1# core after 2# ceramic core 2 is combined with 1# ceramic core 1 and 3# ceramic core 3 is 1 mm; then put the processed 2# ceramic core 2 and 1# ceramic core 1 and 3# ceramic core 3 into the wax mold to press the blade wax mold.

[0045]The injection temperature of the blade wax mold is 65°C, the pressure is 0.3MPa, the injection time is 20 seconds, and ...

Embodiment 3

[0047] First select the quartz glass tube as the 2# ceramic core, its diameter is 2 millimeters, 2 # ceramic core 2 sides are coated with wax film thickness is 30 microns, and core end face is coated with wax mold thickness and is 1.5 millimeters;

[0048] 1# and 3# ceramic cores are made of alumina material. 1# ceramic core 1 and 3# ceramic core 3 need to reserve a seat hole of the same size as ceramic core 2, the diameter of the seat hole is 10 microns larger than the diameter of 2# ceramic core 2, and the length of the seat hole is 3 mm ; 1# ceramic core 1 and 3# ceramic core 3 have independent positioning core heads, 2# ceramic core 2 is combined with 1# ceramic core 1 and 3# ceramic core 3 on the 1# ceramic core The outcrop size is 1 mm; then put the processed 2# ceramic core 2 and 1# ceramic core 1 and 3# ceramic core 3 into the wax mold to press the blade wax mold.

[0049] The injection temperature of the blade wax mold is 55°C, the pressure is 0.3MPa, the injection t...

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Abstract

The invention relates to a locally-free-telescopic single crystal blade-used complex-structured ceramic core preparation technology and belongs to the technical field of high-temperature alloy. The preparation technology comprises steps of: (1) firstly preparing a main ceramic core 1# ceramic core, a 3# ceramic core, and a high-performance local ceramic core 2# ceramic core, wherein the 1# ceramic core and the 3# ceramic core are provided with individual positioning core heads and the 2# ceramic core is in an individual column-shaped structure or an individual tube-shaped structure; (2) totally dip-coating the 2# ceramic core by a thin layer of wax; (3) assembling the treated 2# ceramic core, the 1# ceramic core and the 3# ceramic core and placing the assembled ceramic cores in a wax mould die to carry out wax pressing; and (4) performing a coating shell-making process, a dewaxing process, a sintering process, a single crystal directional solidification process and a decoring process to obtain a finish product of the blade. The preparation technology can effectively avoid a breaking phenomenon of the ceramic core and is suitable for being used industrially.

Description

technical field [0001] The invention belongs to the technical field of superalloys, and in particular relates to a preparation process of a single-crystal hollow turbine blade ceramic core with complex structure. Background technique [0002] The most critical hot-end part of an aero-engine is the turbine blade. In order to improve thermal efficiency, the temperature of the air in front of the turbine blade is getting higher and higher. Single crystal alloy blades remove the influence of grain boundaries and thus can be used at higher temperatures, usually 30°C higher than oriented alloy blades and nearly 100°C higher than polycrystalline blades, but this cannot fully meet the requirements of the modern aviation industry. Therefore, air cooling technology is used in all gas turbine blades today. The air cooling effect is closely related to the air cooling structure of the blade. In order to pursue a higher air cooling effect, the hollow structure of the blade is becoming m...

Claims

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Application Information

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IPC IPC(8): B22C9/10B22C9/04C30B11/00
CPCB22C9/043B22C9/10C30B11/00
Inventor 毛萍莉姜卫国刘正王峰
Owner SHENYANG POLYTECHNIC UNIV
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