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Device for axial retention of vanes mounted on a turbomachine rotor disc

A technology of axial retention and rotor disk, applied in the direction of blade support elements, mechanical equipment, engine elements, etc., can solve the problems of increasing the total weight of the turbine, inaccessible to bolt parts, etc., and achieve the effect of easy manufacturing and easy installation

Active Publication Date: 2008-12-31
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION (S N E C M A)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Unfortunately some low pressure turbine constructions do not allow access to bolted parts without prior removal of some stages of the turbine
Also, specific flanges added to fasten the counterweight increase the overall weight of the turbine

Method used

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  • Device for axial retention of vanes mounted on a turbomachine rotor disc
  • Device for axial retention of vanes mounted on a turbomachine rotor disc

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0018] Figures 1 and 1A are partial longitudinal sectional views of a low-pressure turbine of an aviation turbine equipped with a device constituting an embodiment of the invention.

[0019] Naturally, the invention is applicable to any turbomachine installation (aerial or terrestrial) with a rotor disk on which blades are mounted by axial displacement.

[0020] The low pressure turbine is centered on the longitudinal axis X-X of the turbine. The final stage of the turbine comprises a nozzle consisting of a plurality of stator blades 2 and a rotor wheel placed behind the nozzle and consisting of a plurality of rotor blades 4 axially mounted on a rotor disk 6 . The next last pole of the turbine also has nozzles (not shown) and a rotor wheel formed by a plurality of rotor blades 4' mounted on a rotor disk 6'.

[0021] The disks 6 and 6' of the second and last stages of the turbine are fastened to each other by bolted connections 8 and they are fixed by annular trunnions 10...

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PUM

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Abstract

The invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk, the device comprises a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also comprises a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots, said retaining ring being housed in the groove of the disk, being held outwardlyin the notches of the blade roots, and being constituted by a plurality of angular segments placed end to end.

Description

technical field [0001] The invention relates to an axial retention device for blades mounted on a turbine rotor disk, such as a low pressure turbine last stage rotor. Background technique [0002] As is known, the low-pressure turbine of a turbomachine comprises multiple stages of rotor blades alternating with stator blades. For each stage of the turbine, the stator blades are fastened to two concentric shrouds and the rotor blades are fastened by their roots to the rotor disk. All rotor disks of the turbine are fastened to each other by bolted connections and are secured to the low pressure shaft of the turbine by trunnions. [0003] Such low-pressure turbine final stage disks are known to have a plurality of axial slots on their periphery, each slot housing the root of a turbine rotor blade. The air flow through the turbine exerts an axial force on the rotor blades, so it is necessary to use retaining means to prevent any axial displacement of the blades. One such devic...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/30
CPCF01D5/3015
Inventor 克劳德·格哈德·瑞恩·德捷恩瓦勒里·安尼·格劳斯格尔·劳罗让-卢克·索皮祖
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION (S N E C M A)
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