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Turbine blade including coating system and method of forming turbine blade

一种涡轮叶片、涂层系统的技术,应用在叶片的支承元件、涂层、金属材料涂层工艺等方向,能够解决昂贵、少热保护、降低空气动力学效率等问题

Active Publication Date: 2019-03-05
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, patterned ridges on the surface of the shroud reduce aerodynamic efficiency and tend to be more expensive and have less thermal protection

Method used

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  • Turbine blade including coating system and method of forming turbine blade
  • Turbine blade including coating system and method of forming turbine blade
  • Turbine blade including coating system and method of forming turbine blade

Examples

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Embodiment Construction

[0056] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield still a further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0057] The technical terms used herein are only used to describe specific embodiments, and are not intended to limit the present invention. As used herein, the singular forms "a" and "the" are intended to include the plural forms as well, unless ...

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PUM

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Abstract

Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for formingthe cooled blade tip and applying the coating system onto the cooled turbine blade tip.

Description

technical field [0001] The subject matter disclosed herein relates to turbine blade tip wear, and more particularly, to cooling turbine blades including coating systems and methods for eliminating turbine blade tip wear in conjunction with CMC or metal shrouds in gas turbine engines. Background technique [0002] The turbine section of a gas turbine engine includes a rotor shaft and one or more turbine stages, each turbine stage having a turbine disk (or rotor) mounted or otherwise carried by a bearing and a perimeter mounted to and extending radially from the disk of turbine blades. Turbine assemblies typically generate rotating shaft power by expanding hot compressed gases produced by the combustion of fuel. Gas turbine blades or vanes generally have an airfoil shape designed to convert the thermal and kinetic energy of flow path gases into mechanical rotation of the rotor. [0003] In a turbine engine, a shroud is a ring of material that surrounds the rotating blades. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18F01D5/28F01D11/08C23C24/10
CPCC23C24/103F01D5/18F01D5/28F01D5/288F01D11/08F01D5/186F01D5/187F05D2240/11F05D2300/6033F01D11/122F05D2300/2112F05D2240/307F05D2300/17F05D2300/2261F05D2300/2262F05D2300/2263F05D2300/2284F05D2300/2283F05D2300/2282F01D5/20Y02T50/60F05D2220/32F05D2260/2214
Inventor 石进杰D.P.德里C.E.沃尔夫A.J.加西亚-克雷斯波Y.朱
Owner GENERAL ELECTRIC CO