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Combustion chamber double chamber bottom

A technology of combustion chamber and fuel oil, which is applied in the field of combustion chamber and can solve the problems of polluting fuel consumption and increasing the weight of combustion chamber

Active Publication Date: 2022-08-05
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] Gaps can occur which create problems with contamination, fuel consumption and re-ignition of the combustion chamber when a fire is extinguished
Adding a fail-safe system is also an unsuitable solution, which increases the weight of the combustion chamber

Method used

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  • Combustion chamber double chamber bottom
  • Combustion chamber double chamber bottom
  • Combustion chamber double chamber bottom

Examples

Experimental program
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Embodiment Construction

[0051] figure 1 The combustion chamber 10 of an aircraft gas turbine 1 according to the prior art is shown. With respect to the turbine (as indicated by arrow 11), upstream (AM) with respect to the general direction of airflow in the turbine 1, the turbine 1 has a compressor, not shown, in which the air is injected through the diffuser duct to the not shown. is compressed within the combustion chamber casing (phantom line 5) and then injected into the combustion chamber 10 mounted in this casing. Compressed air is fed into combustion chamber 10 and mixed with fuel before coming out of injector 12 . The gases from the combustion are directed to a high pressure turbine, not shown, located downstream (AV) of the combustion chamber 10 outlet. The annular combustion chamber 10 includes a radially inner annular wall 14 and a radially outer annular wall 16 whose upstream ends are connected by a substantially radially extending bottom wall 18 . The bottom wall 18 has a plurality of...

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Abstract

The invention relates to a combustion chamber of a gas turbine engine, the combustion chamber comprising a chamber bottom having an upstream wall (230) and a downstream wall (218) which are inner annular walls and the outer annular wall, and each of them includes an opening (221) for mounting a fuel injection device (220) through which the fuel injection device injects fuel. The downstream wall has multiple sectors (218a, 218b).

Description

technical field [0001] The present invention relates to the combustion chamber of a gas turbine, such as an aircraft turbojet or turboprop. Background technique [0002] In the field, combustion chambers are known to have: [0003] - two walls, the (radial) inner wall and the (radial) outer wall, and [0004] - a chamber bottom (BCC, combustion chamber bottom) comprising upstream and downstream walls extending between said inner and outer walls, each comprising a mounting opening for a fuel injection device (ie, configured to allow mounting), thereby Fuel is injected through the openings. [0005] FR 2 998 038 discloses such a combustion chamber. [0006] The space or enclosure between the upstream and downstream chamber bottom walls is supplied with air via a plurality of perforations to ensure impingement cooling of the downstream wall which is in direct contact with the flame radiation. Air is then injected through the slots or holes towards the inner and outer walls ...

Claims

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Application Information

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IPC IPC(8): F23R3/00F23R3/50
CPCF23M2900/05002F23R3/002F23R3/50F23R2900/00005F02C7/232F05D2220/32F05D2240/35F23R3/283
Inventor 雅克斯·马塞尔·亚瑟·布内尔丹·朗吉夫·乔里
Owner SAFRAN AIRCRAFT ENGINES SAS
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