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Stator vane with variable setting of a turbomachine

A technology for turbines and stationary blades, applied to mechanical equipment, engine components, non-variable displacement pumps, etc., can solve problems such as disc and/or bushing wear

Active Publication Date: 2007-10-17
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

Friction again causes wear of the discs and / or bushings

Method used

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  • Stator vane with variable setting of a turbomachine
  • Stator vane with variable setting of a turbomachine
  • Stator vane with variable setting of a turbomachine

Examples

Experimental program
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Embodiment Construction

[0016] FIG. 3 shows the portion of the vanes themselves close to the shaft 14 . The disc 13 is viewed in perspective from above. According to one embodiment of the invention, the surface of the disc facing the housing 3 has been machined so as to make a cavity 22A in the second zone 22 which is not affected by the force F applied to the wing 12. The effect of the induced stress. Here, cavity 22A is processed by a method known per se. The bottom of the cavity is flat; if the processing head is spherical, the bottom of the cavity can also be curved. Other shapes than those shown are also possible. Furthermore, in addition to machining, cavities can also be formed by casting, forging or powder metallurgy. Preferably, the cavity continues an arc of circle, for example 60-120 degrees, advantageously corresponding to the arc facing the zone of intense friction. The role of the cavity is to reduce the weight of the blade without degrading its mechanical properties. Therefore, t...

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PUM

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Abstract

The vane has a plate (13) perpendicular to direction formed by a blade (12) and a pivot (14). A surface of the plate opposed to the blade includes two zones (20, 22), where one zone (20) is subjected to high friction with a wall of a bore housing due to the stress transversely applied on the blade. A cavity (22A) in the zone (22) is fabricated in the surface turned towards the housing, where the cavity is not subjected to compression stress resulting from application of force on the blade. The cavity extends on an arc i.e. circle, from sixty to one hundred and twenty degrees around the pivot.

Description

technical field [0001] The invention relates to the field of turbomachines, such as the axial flow compressors of gas turbines, and in particular to the variable-pitch stationary blades of the machines. Background technique [0002] A variable pitch vane in a pivoting system, such as a gas turbine compressor, includes parts that move relative to each other. Figures 1 and 2 schematically show a variable pitch vane 1 mounted in a casing 3 of the machine. The stationary blade comprises a wing 12 , a disc 13 and a rod forming a shaft 14 at one end. The shaft 14 is mounted in bores or radial bores made in the wall of the housing 3 via a plurality of bearings. The blade is supported by this end only. The other end supports an annular floating element 16 , wherein it is mounted for pivotal rotation via a second shaft 17 . The ring provides a seal for the portion of the rotor 18 adjacent to it. The shaft 14 rotates in a corresponding bore of the housing by means of bearings, su...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F04D29/54
CPCF05D2270/304F01D17/162F04D29/563
Inventor 伊冯·克洛阿雷克
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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