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self clamping fasteners for cmc turbine blades

A technology of turbine blades and clamping parts, which is applied in the field of turbine engines and turbine blades, can solve problems such as difficult assembly of discs, and achieve the effect of eliminating friction

Active Publication Date: 2017-04-12
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0008] However, these configurations have the disadvantage that they are difficult to fit into the tray, since these configurations require several operations, requiring installation aids

Method used

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  • self clamping fasteners for cmc turbine blades
  • self clamping fasteners for cmc turbine blades

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Experimental program
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Embodiment Construction

[0023] refer to figure 1 , the upper part of the turbine disk 1 can be seen, which is divided into two disk halves, the reference number of the upstream disk half according to the flow direction of the gas in the flow path of the turbine engine is 1a, and the downstream half of the disc is referenced 1b. For the sake of clarity, only the upper contour of the downstream disc half 1b is shown. Axially extending between the upper parts of the two disc halves are some spars 2 in the form of connectors, which connect the radial faces of the two disc halves to each other and which are to be fitted to The retaining force of the turbine blades of the turbine disk 1 is transmitted to the two disk halves. The number of spars 2 is equal to the number of blades 3 fitted to the turbine disk, each blade occupying a position between two consecutive spars 2 . The radial cross-section of these spars is H-shaped, but its shape is not the most important; the most important feature is that its...

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PUM

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Abstract

The invention relates to a turbine blade having a vane (31) extending above a platform (32) and a root (33) extending below said platform, the root of the blade being a radially extending arm (34), made of composite material and having at least one cylindrical surface (34), the direction of the generatrix of said cylinder is oriented in the direction of said platform, so as to allow the clamping member (5) under the action of centrifugal force slides on said cylindrical surface towards said platform, characterized in that said arm has at its lower end a protrusion (35) forming a radial bearing point, in order to be used for holding said blade on the turbine disk The element on the body (1) engages, and said root (33) is completely on the side of said protrusion with respect to said face.

Description

technical field [0001] The present invention relates to the field of turbine engines, and more particularly to the field of turbine blades for these turbine engines. Background technique [0002] A turbine engine for an aircraft generally includes a fan, one or more compressor stages (such as a low-pressure compressor and a high-pressure compressor), a combustor, one or more turbine stages (such as a high-pressure and low-pressure turbine) and gas discharge pipe. A turbine may correspond to each compressor, the turbines and compressors being connected by a shaft, thereby forming eg a high pressure (HP) body and a low pressure (LP) body. [0003] Turbine blades are components that are subjected to very high temperatures as well as high levels of mechanical stress (due to the centrifugal forces exerted on the turbine blades). In particular, the performance of modern engines requires that the high pressure turbine blades be exposed to as high a temperature as possible. For t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/30F01D5/26
CPCF01D5/26F01D5/3084F01D5/3007Y02T50/60F01D5/284
Inventor 弗朗索瓦·加莱
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A