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Turbomachine ring

A technology for turbine engines and supports, applied in the direction of engine functions, engine components, machines/engines, etc., can solve the problems of insufficient resin temperature tolerance, difficult coverage, size dispersion, etc.

Active Publication Date: 2020-09-01
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it is thus difficult to cover the entire stream
In fact, the covering leads to excessive size dispersion; moreover, the temperature tolerance of the resin is not sufficient in the context of application to turbine engines

Method used

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  • Turbomachine ring
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Examples

Experimental program
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Embodiment Construction

[0054] In order to make the present invention more concrete, an example of a turbine engine ring is described in detail below with reference to the accompanying drawings. Remember that the invention is not limited to these examples.

[0055] figure 1 The uniflow turbojet 1 according to the invention is shown in section along a vertical plane passing through its main axis A. It includes a low-pressure compressor 3 , a high-pressure compressor 4 , a combustion chamber 5 , a high-pressure turbine 6 and a low-pressure turbine 7 from upstream to downstream according to the circulation of the air flow.

[0056] figure 2 A part of the stator of the high pressure compressor 4 is shown. In this figure, two compressor rings 30 according to the first embodiment are visible. Each compressor ring 30 comprises a generally cylindrical upstream ring support 31m and a downstream ring support 31v and forms an integral part of the casing of the compressor 4: they each form a stream wall fac...

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PUM

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Abstract

A turbomachine ring and a turbomachine comprise such a ring and a method for repairing such the ring, the turbomachine ring comprising an essentially cylindrical support (31v) comprising a front surface (36) in which a notch (35) is made, one or more sectors (32) forming a crown configured to create an air stream section, each sector (32) comprising a hook portion (34) projecting in the directionof the support (31v) and engaging in the notch (35) of the support (31v), and an anti-wear device (40) having a U-shaped portion (41), provided in the notch (35) of the support (31v) and pressed at least against the radially external surface (35d) of the notch (35), and a tab portion (42) continuously extending the U-shaped portion (41), pressed against and affixed to the front surface (36) of thesupport (31v).

Description

technical field [0001] The invention relates to a turbine engine ring and a turbine engine comprising a ring of this type and a method for repairing a ring of this type. In particular, the invention relates to a compressor or turbine ring of an aircraft engine with single or double flow. Background technique [0002] In many turbine engine compressors, and in some turbines, these stationary blades are mounted on sectors which form a ring containing the flow: these sectors are then aided by engaging in recesses in the stator support The hook part is installed on the casing of the stator. [0003] However, during operation of the turbine engine, in particular due to the vibrations to which the sectors of the ring are subjected, the hooks of the sectors rub against and wear the notches of the support: erosion of the inner surfaces of the notches is thus sometimes observed. Naturally, this type of erosion alters the dimensional chains between the parts of the ring, in particul...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D25/24
CPCF01D25/246F05D2230/80F05D2260/38F01D9/04F01D11/08F05D2220/323
Inventor 昆廷·皮埃尔·休伯特·邦贝罗马丁·朱比安朱利安·米歇尔·奥古斯特·罗伯特
Owner SAFRAN AIRCRAFT ENGINES SAS
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