A Method for Reducing Turbine Blade Looseness of Gas Turbine

A technology of turbine blades and gas turbines, which is applied to casting molding equipment, casting mold components, manufacturing tools, etc., can solve problems such as complex blade structures, and achieve the effects of improving cooling methods, reducing micro-porosity, and eliminating porosity

Active Publication Date: 2020-10-09
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] This type of blade has a complex structure, consisting of a large tenon frame structure, blade body and lower edge plate

Method used

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  • A Method for Reducing Turbine Blade Looseness of Gas Turbine
  • A Method for Reducing Turbine Blade Looseness of Gas Turbine
  • A Method for Reducing Turbine Blade Looseness of Gas Turbine

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Effect test

Embodiment 1

[0030] In this embodiment, the ЧС70-ВИ alloy is taken as an example. The method for reducing the looseness of the turbine blades of the gas turbine according to the present invention includes the following steps:

[0031] 1) Prepare the gas turbine blade wax mold, wherein the height of the riser of the gas turbine blade wax mold is 1 / 5 to 1 / 6 of the total length of the gas turbine blade, and then use the automatic line full silica sol through the gas turbine blade wax mold Prepare turbine blade formwork;

[0032] 2) Wrap three layers of ceramic wool around the turbine blade formwork, wherein the thickness of each layer of ceramic wool is 6mm, the first layer of ceramic wool is located between the lower end of the ceramic sprue cup and the riser, and the second layer of ceramic wool is located between the ceramic pouring cup and the riser. Between the lower end of the beaker and 1 / 3 of the leaf body, the third layer of ceramic cotton is located between the lower end of the cera...

Embodiment 2

[0036] In this embodiment, the ЧС70-ВИ alloy is taken as an example. The method for reducing the looseness of the turbine blades of the gas turbine according to the present invention includes the following steps:

[0037] 1) Prepare the gas turbine blade wax mold, wherein the height of the riser of the gas turbine blade wax mold is 1 / 5 to 1 / 6 of the total length of the gas turbine blade, and then use the automatic line full silica sol through the gas turbine blade wax mold Prepare turbine blade formwork;

[0038] 2) Wrap three layers of ceramic wool around the turbine blade formwork, wherein the thickness of each layer of ceramic wool is 6mm, the first layer of ceramic wool is located between the lower end of the ceramic sprue cup and the riser, and the second layer of ceramic wool is located between the ceramic pouring cup and the riser. Between the lower end of the beaker and 1 / 3 of the leaf body, the third layer of ceramic cotton is located between the lower end of the cera...

Embodiment 3

[0042] In this embodiment, the ЧС70-ВИ alloy is taken as an example. The method for reducing the looseness of the turbine blades of the gas turbine according to the present invention includes the following steps:

[0043] 1) Prepare the gas turbine blade wax mold, wherein the height of the riser of the gas turbine blade wax mold is 1 / 5 to 1 / 6 of the total length of the gas turbine blade, and then use the automatic line full silica sol through the gas turbine blade wax mold Prepare turbine blade formwork;

[0044] 2) Wrap three layers of ceramic wool around the turbine blade formwork, wherein the thickness of each layer of ceramic wool is 6mm, the first layer of ceramic wool is located between the lower end of the ceramic sprue cup and the riser, and the second layer of ceramic wool is located between the ceramic pouring cup and the riser. Between the lower end of the beaker and 1 / 3 of the leaf body, the third layer of ceramic cotton is located between the lower end of the cera...

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Abstract

The invention discloses a method for reducing loosening of a gas turbine blade. The method for reducing loosening of the gas turbine blade comprises the following steps that (1) a gas turbine blade wax pattern is prepared, wherein the riser height of the gas turbine blade wax pattern is 1 / 5-1 / 6 of the total length of a gas turbine blade, and then a turbine blade die shell is prepared through the gas turbine blade wax pattern; (2) the turbine blade die shell is wrapped with three layers of ceramic wool in a surrounded mode, the first layer of ceramic wool is located between the lower end of a ceramic sprue cup and a riser, the second layer of ceramic wool is located between the lower end of the ceramic sprue cup and 1 / 3 of a blade body, and the third layer of ceramic wool is located betweenthe lower end of the ceramic sprue cup and 2 / 3 of the blade body; (3) the turbine blade die shell after being treated through the step 2 is roasted; and (4) molten steel is prepared, then the moltensteel is filtered through a filter screen and poured into the turbine blade die shell, the turbine blade die shell is then removed, cutting is carried out, and the gas turbine blade is obtained. The method for reducing loosening of the gas turbine blade can avoid loosening at the joint R between the blade body and an edge plate.

Description

technical field [0001] The invention belongs to the technical field of precision casting, and relates to a method for reducing the looseness of turbine blades of a gas turbine. Background technique [0002] Large-sized turbine blades are the key core components of heavy-duty gas turbines, and are mainly made of nickel-based superalloy precision casting without allowance. The power blade is a high-temperature, high-speed, and high-load rotating part. The working environment is harsh, the thermal load and power load are large, and the working conditions are very harsh. Cast nickel-based superalloys have extremely complex components, a wide range of solidification temperatures, and well-developed solidification dendrites, which hinder the feeding of dendrites and have a high tendency to form porosity. [0003] This type of blade has a complex structure, consisting of a large tenon frame structure, blade body and lower edge plate. The leaf body is large in size, thin in wall t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B22C9/04B22C9/08B22C9/22B22D27/04
CPCB22C9/04B22C9/088B22C9/22B22D27/045
Inventor 牛建平尹冬梅王琳雍坤轩常涛岐刘晓飞闵蓉陈波
Owner AECC AVIATION POWER CO LTD
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