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Blades equipped with cooling systems, associated deflector assemblies, and associated turbines

A cooling system, turbine technology, applied in the direction of supporting elements of blades, engine cooling, turbine/propulsion cooling, etc., can solve the problems of air loss, inability to use cooling blades or turbines, cold air leakage, etc.

Active Publication Date: 2020-08-11
SAFRAN HELICOPTER ENGINES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] However, this insert configuration results in a significant leakage of cold air at the interface between the insert and the inner meridian
The air that escapes due to this leak is lost (especially in the jet stream of the outflow of gas) and cannot be used to cool the blades or other parts of the turbine

Method used

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  • Blades equipped with cooling systems, associated deflector assemblies, and associated turbines
  • Blades equipped with cooling systems, associated deflector assemblies, and associated turbines
  • Blades equipped with cooling systems, associated deflector assemblies, and associated turbines

Examples

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Embodiment Construction

[0036] The following embodiments are examples. Although the description refers to one or more embodiments, this does not necessarily mean that every reference refers to the same embodiment, or that a feature is only applicable to a single embodiment. Single features of different embodiments may also be combined to provide other embodiments. In the drawings, scale and proportion have not been strictly observed, which are for the purpose of illustration and clarity.

[0037] Figure 1 to Figure 3 ( figure 1 as perspective and figure 2 with image 3 As a cross-sectional view) schematically shows a blade 10 of a baffle assembly of a turbomachine. A blade 10 as arranged in a turbomachine comprises a portion called the outer meridian 12 on the side of the turbine's combustion chamber (not shown) and a section called the inner meridian 14 on the side of the turbine's central hub 16 part of the turbine around which the rotating parts of the turbine rotate. Additionally, the ga...

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Abstract

The invention relates to a blade of a turbomachine deflector assembly, the blade being equipped with a cooling system comprising an insert (22) arranged in an inner cavity (24) of said blade, and a discharge means, The insert is connected to the inlet (26) for the cooling air of the blade and is designed to cool the surface of the inner cavity (24) of the blade; Some of the cooling air is exhausted and is designed to send some of this cooling air to the central hub of the turbine. The discharge device comprises a discharge head (30) which is arranged in the inner cavity (24) of the blade and passes through the opening (34) of the insert and which is configured to transfer the cooling air in the insert (22) Some of the air is expelled.

Description

technical field [0001] The invention relates to a blade of a baffle assembly of a turbomachine. In particular, the present invention relates to a blade of a baffle assembly equipped with a cooling system for the blade as well as for other components of a turbomachine. Background technique [0002] Typically, a turbine includes, from upstream to downstream, one or more compressor stages (such as a low pressure compressor and a high pressure compressor), a combustor, and one or more turbine stages (such as a high pressure turbine and a low pressure turbine). Upstream and downstream are defined relative to the normal gas flow direction (from upstream to downstream) in the outflowing jet. [0003] The turbine converts the thermal and kinetic energy of the airflow from the combustion chamber into the mechanical energy required to drive the compressor and / or the rotor (eg in the case of a helicopter). [0004] A turbine generally comprises one or more stages of blades, each comp...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18F01D9/06
CPCF01D5/188F01D9/065F05D2260/201Y02T50/60F01D5/18F01D9/02F01D25/246F02C7/18F05D2240/12F05D2240/81
Inventor 巴普蒂斯特·哈路英简-路克·布雷宁达米恩·拉伯尼
Owner SAFRAN HELICOPTER ENGINES
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