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Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes

A technology for injection systems, swirlers, used in lighting and heating equipment, climate sustainability, combustion methods, etc., which can solve the problems of difficult injection system manufacturing, incompletely satisfactory flow, small injection system size, etc.

Pending Publication Date: 2021-09-07
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Manufacture of the injection system is difficult due to its small size
In addition, the flow inside the Venturi is not entirely satisfactory, especially since a film of the air and fuel mixture can deposit on the inner walls of the Venturi

Method used

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  • Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes
  • Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes
  • Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes

Examples

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Embodiment Construction

[0034] Identical, similar or equivalent parts of the various figures are given the same reference numerals to facilitate passage from one figure to another.

[0035] figure 1 A combustion chamber 2 of an aircraft turbine is shown in a schematic manner. The combustion chamber 2 is annular around the longitudinal axis Y-Y of the turbine.

[0036] The combustion chamber has an inner wall 26 , an outer wall 25 , a fairing 24 , an inner housing wall 23 and an outer housing wall 22 , connected by a chamber bottom 28 .

[0037] The combustion chamber also includes the injector 3 , the injection system 4 and the diffuser 10 and the upstream holding assembly 21 of the injection system 4 .

[0038] The outer casing wall 22 delimits the combustion chamber 2 radially outwardly with respect to the longitudinal axis Y-Y of the turbine. The inner casing wall 23 is positioned radially towards the inside with respect to the outer wall 22 with respect to the longitudinal axis Y-Y of the turb...

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PUM

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Abstract

The invention relates to an injection system (4) for a turbomachine combustion chamber. The injection system comprises a swirler (7) and a mixing bowl (8). The mixing bowl (8) comprises a converging frustoconical portion (82) and a diverging frustoconical portion (84). The diverging frustoconical portion (84) is connected to the converging frustoconical portion (82), forming a continuous aerodynamic profile with the converging frustoconical portion (82). The diverging frustoconical portion (84) is passed through by vortex holes (81) which each comprise a circumferential component around a longitudinal axis (X-X) of the injection system and an axial component along the longitudinal axis (X-X) of the injection system.

Description

technical field [0001] The invention relates to the general technical field of aircraft turbines, such as turbojets and turboprops. The invention relates to an injection system for a turbomachine combustor. Background technique [0002] Turbine annular combustors typically include multiple injection systems inserted into openings at the bottom of the combustor. Fuel injectors are housed in each of the injection systems. [0003] Snecma patent application FR 2 903 169 relates to an injection system comprising an internal swirler, a venturi and a mixing bowl. The mixing bowl includes swirl holes. These mixing bowl vortex holes are arranged radially outside and around the Venturi. These mixing bowl vortex holes are arranged in the upstream part of the mixing bowl, which is cylindrical and has a circular cross-section. [0004] The injection system of application FR 2 903 169 is limited in size while enabling a relatively satisfactory injection of fuel into the combustion c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/12F23R3/14F23R3/28
CPCF23R3/283F23R3/286F23R3/12F23R3/14F23R2900/03044Y02T50/60
Inventor 塞巴斯蒂安·阿兰·克里斯多夫·布格斯罗曼·尼古拉斯·吕内尔哈里斯·姆塞范迪克
Owner SAFRAN AIRCRAFT ENGINES SAS