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Synthetic high-temp assembly and manufacturing method therefor

A component and column technology, which is applied in the field of turbine assembly components, can solve the problem of aggravated oxidation resistance turbine design

Inactive Publication Date: 2008-07-16
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Problems related to material melting point and oxidation resistance are exacerbated by prior art turbine designs that require higher operating temperatures in order to increase turbine efficiency

Method used

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  • Synthetic high-temp assembly and manufacturing method therefor
  • Synthetic high-temp assembly and manufacturing method therefor
  • Synthetic high-temp assembly and manufacturing method therefor

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Embodiment Construction

[0042] In the following description, it is understood that terms such as "top", "bottom", "outwardly", "inwardly" and the like are words of convenience and not intended to be limiting.

[0043] Noble metals such as Rh, Pd and Pt and their alloys have a high melting temperature, excellent oxidation resistance, high temperature strength and good adhesion properties for thermal barrier coatings (hereinafter also referred to as TBC). It is impractical to manufacture entire turbine components such as airfoils since they are very dense and costly. The present invention overcomes these and other problems by providing a turbine component of composite construction. The composite structure includes at least one column providing mechanical support, a spacer structure connected to the column, and an outer shell comprising at least one noble metal or alloy thereof. The housing is in contact with the spacing structure and conformally surrounds the post.

[0044] Reference is made to the d...

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Abstract

An article (200) for use in a hot gas path of a gas turbine assembly, a metallic skin (212) for such an article (200), and a method for making such an article (200) are presented with, for example, the article (200) comprising a spar (208), the spar (208) providing'mechanical support for the article (200) and comprising a cooling fluid delivery system (218), a top end, and a bottom end; a standoff structure (208) attached to the spar (208), the standoff structure (208) comprising a plurality of spacing elements (214) in a spaced-apart relation to each other, the spacing elements (214) having first ends adjacent to the spar (208) and second ends opposite to the first ends; a skin (212) conformally surrounding the spar (208) and the standoff structure (208), the skin (212) comprising a top end and a bottom end, wherein the standoff structure (208) separates the spar (208) and the skin (212), wherein the plurality of spacing elements (214) is disposed with an inner surface of the skin (212) adjacent to the second ends of the spacing elements (214) to form a plurality of plena (216) between the spar (208) and the skin (212), the plena (216) in fluid communication with the cooling fluid delivery system (218), the skin (212) comprising at least one metal selected from the group consisting of Rh, Pd, and Pt; and a base (204) connecting the bottom end of the spar (208) and the bottom end of the skin (212).

Description

technical field [0001] The invention relates to a turbine assembly such as an airfoil. In particular, the invention relates to a turbine assembly having a composite structure. More particularly, the present invention relates to components, such as airfoils, for turbine components having an oxidation resistant composite structure. Background technique [0002] Turbine components such as aviation turbines, land turbines, marine turbines, and the like often include components formed of materials also known as superalloys. Superalloys exhibit desirable chemical and physical properties at the high temperatures, stresses, and pressures often encountered during turbine operation. Nickel (Ni), iron (Fe) and cobalt (Co) based superalloys are particularly desirable in this application. For example, turbine components such as airfoils in modern jet engines can reach temperatures as high as 1150°C, which is about 85% of the melting temperature of most Ni-based superalloys. [0003] ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18B23P15/04F01D5/14F01D5/28F02C7/00
CPCF01D5/14F05C2201/0427F05D2300/143Y02T50/672F01D5/18F01D5/28Y02T50/676Y02T50/67Y02T50/60
Inventor J·-C·赵L·姜M·R·杰克逊R·达罗利尔R·E·沙夫里克
Owner GENERAL ELECTRIC CO