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Annular combustion chambers for turbine engines

一种环形燃烧室、涡轮发动机的技术，应用在燃烧室、连续燃烧室、燃烧方法等方向，能够解决火焰周边蔓延困难、降低燃烧室性能等问题

Active Publication Date: 2016-01-20
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

As a result, the flakes of fuel injected from the adjacent injection system no longer cross the perimeter of the main dilution hole upwards, making it difficult for the flame to spread around the perimeter between the injectors, reducing the performance of the combustion chamber

Method used

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  • Annular combustion chambers for turbine engines
  • Annular combustion chambers for turbine engines
  • Annular combustion chambers for turbine engines

Examples

Experimental program
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Embodiment Construction

[0043] see first figure 1 , figure 1 An annular combustion chamber 10 of a turbine engine, such as a turboprop or turbojet, is shown at the outlet of a centrifugal diffuser 12 mounted at the outlet of a high pressure compressor (not shown). The combustion chamber 10 is followed by a high-pressure turbine 14 , of which only the intake nozzle 16 is shown.

[0044]The combustion chamber 10 has coaxial inner and outer frusto-conical walls 18 and 20 forming surfaces of revolution nested one within the other and having a downwardly conical section. Such a combustion chamber is called converging. The inner and outer annular walls 18 and 20 are connected at their upstream ends to an annular chamber end wall 22 and they are secured downstream by inner and outer annular flanges 24 and 26 . The outer annular flange 26 bears radially outward against a housing 28 and axially against a radial flange 30 for fastening the nozzle 16 of the high-pressure turbine to the housing 28 . The inne...

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Abstract

An annular combustion chamber including inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough. Each injection system includes at least one swirler for producing a rotating stream of air downstream from a fuel injector, and a frustoconical bowl downstream from the swirler and formed with an annular row of air injection orifices, the outer wall having an annular row of primary dilution orifices. The orifices of the bowls are distributed and dimensioned such that sheets of air / fuel mixture present a local enlargement circumferentially intersecting an adjacent sheet of fuel upstream from the primary dilution orifices.

Description

technical field [0001] The invention relates to an annular combustion chamber of a turbine engine, such as a turbojet or turboprop. Background technique [0002] In a known manner, the annular combustor of the turbine engine receives the upstream flow from the high-pressure compressor and delivers a hot flow downstream to drive the rotors of the high-pressure and low-pressure turbines. [0003] The annular combustion chamber comprises two coaxial walls forming surfaces of revolution extending one inside the other and connected together at their upstream ends by the annular chamber end wall. The chamber end wall has openings for mounting the fuel injection system between the inner and outer coaxial walls. [0004] Each injection system includes means for supporting the head of the fuel injector and at least one swirler located coaxially at a location downstream of the fuel injector head, wherein the swirler delivers a swirling air flow downstream from the location of fuel in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/50F23R3/12F23R3/06
CPCF23R3/06F23R3/12F23R3/286F23R3/50F23R3/002
Inventor 丹尼斯·吉恩·莫里斯·桑德里斯克里斯托弗·皮尤瑟格斯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION (S N E C M A)
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