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Turbine bucket assembly and turbine system

a technology of turbine buckets and buckets, which is applied in the direction of liquid fuel engines, vessel construction, marine propulsion, etc., can solve the problems of limited operating capacity of such engines, and achieve the effects of reducing heat resistance, reducing heat expansion, and reducing heat resistan

Inactive Publication Date: 2015-12-03
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a turbine bucket assembly that includes a single-lobe joint with an integral platform, a segmented airfoil with a root segment and tip segment, and a turbine wheel with a receptacle that matches the single-lobe joint. The tip segment includes a material with higher thermal expansion and lower heat resistance than the root segment material and the tip segment material. This design helps improve the performance of the turbine system.

Problems solved by technology

The roots of at least some known buckets are coupled to the disk with dovetails that are inserted within corresponding dovetail slots formed in the rotor disk to form a bladed disk, or “blisk.” Because such turbine engines operate at relatively high temperatures and may be relatively large, the operating capacity of such an engine may be at least partially limited by the materials used in fabricating the buckets and / or the length of the airfoil portions of the buckets.

Method used

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  • Turbine bucket assembly and turbine system
  • Turbine bucket assembly and turbine system
  • Turbine bucket assembly and turbine system

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Embodiment Construction

[0013]Provided is a turbine bucket assembly and a turbine system. In addition, methods of assembling and / or producing such turbine bucket assemblies and turbine systems are apparent from the disclosure. Embodiments of the present disclosure, for example, in comparison to similar concepts failing to include one or more of the features disclosed herein, permit easier repair of damage (for example, by a tip-rub event, overheating, and / or any other damaging event) by permitting the tip segment to be repaired alone without requiring more expensive and more time-consuming removal and repair / replacement of the complete turbine bucket, reduce overall operating and maintenance costs, reduce duration of out-of-service periods for repairs, permit other suitable advantages, permit larger or smaller sized engines and / or turbine buckets to be used, permit portions of a turbine bucket assembly to be exposed to higher temperatures, permit properties in a specific portion of a turbine bucket assembl...

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Abstract

A turbine bucket assembly and turbine system are disclosed. The assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material having a lower heat resistance and a higher thermal expansion than the root segment material and the tip segment material.

Description

FIELD OF THE INVENTION[0001]The present invention is directed to turbine components and turbine systems. More particularly, the present invention is directed to turbine bucket assemblies and turbine systems having one or more turbine bucket assemblies.BACKGROUND OF THE INVENTION[0002]At least some known gas turbine engines include a combustor, a compressor, and / or turbines that include a rotor disk that includes a plurality of rotor blades, or buckets, that extend radially outward therefrom. The plurality of rotating turbine blades or buckets channel high-temperature fluids, such as combustion gases or steam, through either a gas turbine engine or a steam turbine engine. The roots of at least some known buckets are coupled to the disk with dovetails that are inserted within corresponding dovetail slots formed in the rotor disk to form a bladed disk, or “blisk.” Because such turbine engines operate at relatively high temperatures and may be relatively large, the operating capacity of...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/28F01D5/14
CPCF01D5/141F01D5/28F01D5/16F01D5/225F01D5/3007F05D2230/642F01D5/282F01D5/284F05D2300/6033
Inventor DAVIDSON, DWIGHT ERICPOTTER, BRIAN DENVERBALSONE, STEPHEN JOSEPH
Owner GENERAL ELECTRIC CO
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