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Spray coating process for protecting gas film hole of gas turbine blade

A technology of gas turbine blades and gas film holes, which is applied in coatings, spray devices, and devices for coating liquid on surfaces, etc., can solve the problems of high equipment cost, gas film hole shrinkage, complicated processes, etc., and achieve anti-corrosion performance. Good, prevent blocking and shrinkage phenomenon

Pending Publication Date: 2021-08-24
远科秦皇岛节能环保科技开发有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The gas turbine blades on aero-engines and gas turbines are the jewels in the crown, and they have been a long-term bottleneck project for my country's engine technology in the West. The WP-13 and WS-10 series engines belong to the second-generation technology, and the gas turbine blades mostly use heat Thermal technology methods such as spraying and electrochemical methods are not only complicated in process and high in equipment cost, but also have serious problems such as gas film hole shrinkage in the first-stage gas turbine blades. big problem

Method used

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  • Spray coating process for protecting gas film hole of gas turbine blade
  • Spray coating process for protecting gas film hole of gas turbine blade

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] A spraying process for protecting gas turbine blade gas film holes, comprising the following steps:

[0034] (1) Insert the tenon of the gas turbine blade 1 into the plaster protection mold 3 to protect the original size and shape of the tenon during sandblasting and spraying.

[0035] (2) The gypsum protection mold 3 is nested into the metal protection mold 2 made of alloy steel. The metal protection mold 2 is used to resist external force and prevent deformation of the entire device during the sandblasting process.

[0036] (3) Select the dry air compressor 4, and its air outlet passes through the metal protective mold 2 to be connected to the gas turbine blade, adjust the pressure of the dry air compressor 4 to be 0.1Mpa, and the dry compressed air enters the turbine blade 1, Then it is sprayed at the air film hole, and the continuous injection of gas can prevent the sand particles in the sandblasting and the paint in the spraying from blocking the air film hole.

...

Embodiment 2

[0042] A spraying process for protecting gas turbine blade gas film holes, comprising the following steps:

[0043] (1) Insert the tenon of the gas turbine blade 1 into the plaster protection mold 3 to protect the original size and shape of the tenon during sandblasting and spraying.

[0044] (2) The gypsum protection mold 3 is nested into the metal protection mold 2 made of alloy steel. The metal protection mold 2 is used to resist external force and prevent deformation of the entire device during the sandblasting process.

[0045] (3) Select the dry air compressor 4, and its air outlet passes through the metal protective mold 2 to be connected to the gas turbine blade, adjust the pressure of the dry air compressor 4 to be 0.1Mpa, and the dry compressed air enters the turbine blade 1, Then it is sprayed at the air film hole, and the continuous injection of gas can prevent the sand particles in the sandblasting and the paint in the spraying from blocking the air film hole.

...

Embodiment 3

[0051] A spraying process for protecting gas turbine blade gas film holes, comprising the following steps:

[0052] (1) Insert the tenon of the gas turbine blade 1 into the plaster protection mold 3 to protect the original size and shape of the tenon during sandblasting and spraying.

[0053] (2) The gypsum protection mold 3 is nested into the metal protection mold 2 made of alloy steel. The metal protection mold 2 is used to resist external force and prevent deformation of the entire device during the sandblasting process.

[0054] (3) Select the dry air compressor 4, and its air outlet passes through the metal protective mold 2 to be connected to the gas turbine blade, adjust the pressure of the dry air compressor 4 to be 0.1Mpa, and the dry compressed air enters the turbine blade 1, Then it is sprayed at the air film hole, and the continuous injection of gas can prevent the sand particles in the sandblasting and the paint in the spraying from blocking the air film hole.

...

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Abstract

The invention provides a spray coating process for protecting a gas film hole of a gas turbine blade. The spray coating process comprises the following steps of protecting a tenon of the gas turbine blade; introducing air into the hollow gas turbine blade by an air compressor, and continuously spraying out gas from the gas film hole formed in the gas turbine blade; performing sand blasting treatment on the gas turbine blade; continuously introducing air to the gas turbine blade subjected to sand blasting, and then performing heating treatment on the treated gas turbine blade; and continuously introducing air into the hollow gas turbine blade by the air compressor, continuously spraying the gas out from the gas film hole formed in the gas turbine blade for spray coating; and after the spray coating is completed, performing drying and sintering treatment in sequence. According to the method, compressed air is sprayed out from the gas film hole of the gas turbine blade, and then sand blasting and spray coating are performed, so that the gas film hole is protected, and the occurrence of phenomena of blockage and shrinkage of the gas film hole is prevented.

Description

technical field [0001] The invention relates to the technical field of spraying technology, in particular to a spraying technology for protecting gas turbine blade gas film holes. Background technique [0002] The turbine is the part with the largest thermal load and mechanical load. The working environment of the turbine blade is particularly harsh. In the engine cycle, it bears the impact of high-temperature and high-pressure gas after combustion. Its manufacturing technology is also listed as the key technology of modern aero-engines. Engine performance depends largely on the temperature of the turbine inlet, which is limited by the material of the turbine blades. Continuous cooling of these components can allow their working environment temperature to exceed the melting point of the material, so that they can still work safely and reliably. Air film cooling technology refers to opening air film holes on the gas turbine blades and extracting them from the compressor. The...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B05D1/02B05D7/24B24C1/06B05D1/32B05B12/18B05B12/20
CPCB05D1/02B05D7/24B24C1/06B05D1/32B05B12/18B05B12/20
Inventor 闫俊良黄开明刘勇军闫慧斌刘德奇王广勇孙瑞嘉谢昌坦宋星奇杨幼欣张利
Owner 远科秦皇岛节能环保科技开发有限公司
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