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Turbine blade assembly

A technology of blades and components, applied in the direction of supporting elements of blades, engine elements, machines/engines, etc., which can solve the problems of increased cost of turbomachinery

Inactive Publication Date: 2012-03-21
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Consequently, the number of components and thus the cost of the turbomachinery increases

Method used

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  • Turbine blade assembly
  • Turbine blade assembly
  • Turbine blade assembly

Examples

Experimental program
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Embodiment Construction

[0015] figure 1 Illustrated in is one embodiment of a rotor assembly 10 for use in, for example, a turbine of a turbomachine. The rotor assembly 10 includes a plurality of blade assemblies 12 secured to the rotor 14 at the periphery of the rotor 14 via, for example, a plurality of tenon attachment means 16 .

[0016] see figure 2 As shown in the exploded view, the blade assembly 12 includes an airfoil section 18 and an attachment section 20 . Airfoil segment 18 includes an airfoil 22 and, in some embodiments, a platform 24 that defines an annular flow path for rotor 14 . Airfoil segments 18 may be formed from a variety of materials that are well suited to the high temperature environments in which many rotors 14 operate. For example, airfoil segment 18 may be formed from a ceramic matrix composite (CMC) or a single crystal alloy. Attachment section 20 is formed separately from airfoil section 18 and may be formed from a different material than that used in airfoil section...

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PUM

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Abstract

The invention provides a turbine blade assembly. Concretely, a blade assembly (12) for a rotor (14) includes an attachment section (20) operably connectable to a rotor (14), and an airfoil section (18). At least one retainer extends in a substantially tangential direction at least partially through the airfoil section (18) and the attachment section (20) to secure the airfoil section (18) to the attachment section. A method of assembling a rotor (14) assembly (10) includes inserting at least one retainer in a substantially tangential direction at least partially through an attachment section (20) of a blade assembly (12) and an airfoil section of the blade assembly, thereby securing the airfoil section (18) to the attachment section (20). The blade assembly is then secured to a rotor (14).

Description

technical field [0001] This invention was conceived under US Government contract DE-FC26-05NT42643-DOE. The federal government may have certain rights in this invention. [0002] The subject matter disclosed herein relates to turbomachinery. More specifically, the present disclosure relates to turbine blade assemblies for turbomachines. Background technique [0003] A turbine assembly includes a number of blades secured to a rotor. In some turbines, it is required that the blade include an airfoil portion as well as a platform portion into which the airfoil portion is inserted, usually to allow the airfoil portion and platform portion to be formed from different materials. The combined airfoil / platform blade assembly is secured to the rotor via eg a conventional dovetail attachment. [0004] Blade assemblies where the airfoil portion and the platform portion are of different materials (which have different mechanical and thermal properties) introduce thermal matching iss...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/14F01D5/30F01D5/28
CPCF05D2230/61F01D5/147F01D5/225F05D2230/64Y10T29/49321
Inventor A·J·加西亚-克雷斯波R·A·布里廷厄姆
Owner GENERAL ELECTRIC CO