System and method for reducing grain boundaries in shrouded airfoils

a technology of shrouds and airfoils, applied in the field of gas turbine components, can solve the problems of affecting the service life of shrouds, and affecting and reducing the service life of shrouds. the effect of reducing the risk of rust and other failure mechanisms

Active Publication Date: 2011-10-20
GE INFRASTRUCTURE TECH INT LLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0005]Aspects and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned through practice of the invention.

Problems solved by technology

However, angles, curves, indentations, and other changes in the mold shape alter the direction of the grain growth, resulting in the development of multiple directionally solidified grains as the molten metal cools.
As a result, the shroud portion may be more susceptible to an earlier onset of corrosion, creep, fatigue failure, cracking, and other failure mechanisms.

Method used

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Examples

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Embodiment Construction

[0015]Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention.

[0016]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 modifications and variations can be made in the present invention without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still 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.

[0017]FIG. 1 provide...

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Abstract

A turbine bucket includes an airfoil and a shroud. The shroud includes first and second bearing surfaces, and the first and second bearing surfaces each comprise a single grain structure. A method for forming a turbine bucket includes orienting a mold vertically, wherein the mold includes a first portion that defines a shank, a second portion connected to the first portion that defines an airfoil, and a third portion connected to the second portion that defines a shroud, wherein the third portion includes first and second sides, and wherein the first portion is higher than the second portion and the second portion is higher than the third portion. The method further includes flowing a molten metal into the mold and selectively growing large single grains in at least one of the first or second sides.

Description

FIELD OF THE INVENTION[0001]The present invention generally involves gas turbine components made from super alloy castings. In particular, the present invention describes and enables a turbine blade shroud with a localized single grain structure and a method for manufacturing such a turbine blade shroud.BACKGROUND OF THE INVENTION[0002]Turbines generally include multiple stages of rotating blades, also known as turbine buckets, circumferentially located around a rotor. Each turbine bucket generally includes a root portion that connects to the rotor, an airfoil portion that extends radially from the root portion, and a shroud portion that connects to the airfoil portion at the outer radial end of the turbine bucket. A working fluid flowing through the turbine causes the turbine buckets and rotor to rotate to produce work. A bearing surface on each side of the shroud portion allows adjacent turbine buckets to interlock at the outer radial extremity. This radial interlocking of turbine...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/14B22C9/00B22D27/04
CPCB22D27/045C30B11/002F05D2300/607F01D5/225F01D5/28C30B29/52
Inventor KING, WARREN TANKOTTILINGAM, SRIKANTH CHANDRUDUPECK, ARTHUR SAMUEL
Owner GE INFRASTRUCTURE TECH INT LLC
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