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Turbomachine nozzle cowl having jet noise reduction patterns

A fairing and turbine technology, applied in mechanical equipment, engine manufacturing, machine/engine, etc., can solve the problem of increased noise level at the high frequency end

Active Publication Date: 2009-04-01
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

However, besides the acoustic improvement achieved by such jet noise reduction structures at the low frequency end, they also cause an increase in the noise level at the high frequency end

Method used

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  • Turbomachine nozzle cowl having jet noise reduction patterns
  • Turbomachine nozzle cowl having jet noise reduction patterns
  • Turbomachine nozzle cowl having jet noise reduction patterns

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0025] FIG. 1 is a perspective view of an individual gas flow nozzle 10 of a turbomachine. The nozzle 10 has an axially symmetrical shape about its longitudinal axis X-X and is generally composed of a primary cowling 14, a secondary cowling 16 and a central body 18 centered on the nozzle longitudinal axis X-X.

[0026] The main fairing 14 is cylindrical or frustoconical in shape, extending around the longitudinal axis X-X of the nozzle. The central body 18 is located inside the main fairing 14 , concentrically with it, while its ends are actually tapered.

[0027] The secondary fairing 16 is likewise cylindrical or frustoconical in shape, surrounds the main fairing 14, is concentric with it, and extends around the longitudinal axis X-X of the nozzle.

[0028] It should be noted that the longitudinal axis X-X of the nozzle coincides with the longitudinal axis of the primary 14 and secondary 16 cowlings.

[0029] The above-mentioned independent air flow nozzle is fixed to belo...

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PUM

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Abstract

The invention relates to a cowl 14 for a turbomachine nozzle, the cowl including a plurality of repetitive patterns 26 disposed to extend a trailing edge 14a of said cowl and spaced circumferentially apart from one another. Each pattern is in the form of a quadrilateral having a base 28 that is formed by a portion of the trailing edge of the cowl and two vertices 30a,30b that are spaced downstream from the base and that are connected thereto via two sides 32a,32b, each side having the shape of a parabola. Each pattern is asymmetrical relative to a midplane P of the pattern containing a longitudinal axis X-X of said cowl, and it comprises a first portion 34a inclined radially towards the inside of the cowl, and a second portion 34b inclined radially towards the outside of the cowl.

Description

technical field [0001] The present invention relates to the general field of nozzles mounted on turbomachines. The present invention particularly relates to an independent air flow nozzle, in which at least one of the fairings is provided with a jet flow noise reducing structure for reducing the jet flow noise generated at the outlet end of the nozzle. Background technique [0002] In general, the independent air flow nozzle of the turbine includes a main fairing, a secondary fairing arranged concentrically around the main fairing, thereby forming a first annular channel for the flow of the external air flow (or cold air flow), and a concentric arrangement The central body in the main fairing, thereby forming a second annular passage through which the inner air flow (or hot air flow) flows. [0003] One known technique to reduce jet noise at the exit of such nozzles is to promote mixing of the hot and cold gas streams from the turbine. At the heart of the problem is contro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/02
CPCF02K3/06F02K1/386F02K1/48F05D2250/16
Inventor 塞比斯蒂恩·让-保罗·埃伯利皮埃尔·菲利普·玛丽·洛埃亚克斯坦弗尼·杰魁斯·弗朗西斯·托马斯亚历山大·阿尔弗雷德·加斯顿·维耶曼卡迈勒·泽加
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A