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Fixed vane assembly for turbine engine with reduced weight, and a turbine engine including at least one such fixed vane assembly

A technology of turbine engine and fixed fins, which is applied in the direction of engine components, engine manufacturing, engine function, etc., can solve the problem of heavy component weight, etc., and achieve the effect of simple placement and keeping in place, and easy removal

Active Publication Date: 2011-07-20
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

[0009] This type of fastening is satisfactory, but the weight of the assembly is considerable, the axial stop of the pin is achieved by means of an additional ring flange

Method used

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  • Fixed vane assembly for turbine engine with reduced weight, and a turbine engine including at least one such fixed vane assembly
  • Fixed vane assembly for turbine engine with reduced weight, and a turbine engine including at least one such fixed vane assembly
  • Fixed vane assembly for turbine engine with reduced weight, and a turbine engine including at least one such fixed vane assembly

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Embodiment Construction

[0035] The following description will provide a detailed description of a guide vane assembly for a high pressure turbine, but the invention is not limited to a guide vane assembly, but is applicable to any fixed vane assembly for a turbine engine.

[0036] In the description it should be taken into account that the direction from left to right in FIG. 1 corresponds to the direction of flow of the gas flow, the left being upstream and the right downstream.

[0037] For the sake of brevity, in the various embodiments described, the same reference numerals will be used to refer to elements having the same function or substantially the same structure.

[0038] Figure 1A A detailed view of a turbine engine with an axis of revolution X according to the invention is shown. This turbine engine notably comprises a combustion chamber 2 provided with an upstream intake 4 for air from a compressor (not shown), and a discharge 6 for the combustion gases. The turbine engine further compr...

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PUM

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Abstract

The invention relates to a fixed vane assembly for a turbine engine that comprises an inner casing (18) and a high-pressure turbine distributor formed by at least two angular sectors (8.1) provided with blades (12), each of the angular sectors (8.1) being fixed on the casing (18) and including a platform (20) and a fastening tab (22), said fastening tab (22) radially protruding from the platform (20) towards the outside, the casing (18) including a first annular groove (24) for receiving the fastening tabs (22), radial retaining pins (30) of the angular sectors (8.1) being inserted into bores formed in the casing (18) and the fastening tabs (22), the axial retaining pins (30) being axially stopped by a core (28) mounted in a second annular groove (26) of the casing (18).

Description

technical field [0001] The invention relates to a fixed vane assembly for a turbine engine, such as a high pressure or low pressure turbine guide vane assembly, in particular for an aircraft turbojet, and also to a turbine engine comprising at least one such fixed vane assembly. Background technique [0002] Aircraft turbojet engines traditionally include a high pressure compressor, a low pressure compressor, a combustor, a high pressure turbine engine, and a low pressure turbine engine. [0003] The compressor is used to pressurize the air in the atmosphere, the combustor mixes the air compressed by the compressor with fuel and burns the mixture, and the turbine is placed in the jet stream and driven by the high temperature air flow. The turbine is used in particular to drive the compressor. [0004] The compressor includes rotor vanes, with stationary guide vanes directing the flow between the compression stages. [0005] At the output of the combustor there is a fixed h...

Claims

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Application Information

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IPC IPC(8): F01D9/04
CPCY02T50/671F01D9/023F05D2230/64F05D2260/30F05B2260/30F05B2230/604F01D9/04F01D9/042Y02T50/60
Inventor 斯特凡·皮埃尔·吉拉姆·布兰查德法布里斯·马赛尔·诺埃尔·加林劳伦特·皮埃尔·约瑟夫·里库马蒂厄·达科斯基
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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