发明名称 |
Turbomachine e.g. aircraft turbojet, combustion chamber, has internal and external flanges with orifices of triangular shape, where successive triangular orifices are arranged in staggered and head-to-tail configuration |
摘要 |
<p>The chamber has a chamber endwall (17) equipped with fuel injectors (32) and axisymmetric walls connecting the chamber endwall to internal and external flanges (18, 20) for fastening to internal and external casings (24). The flanges have annular portions that are pierced by orifices (30) for the flow of air to cool the downstream components, where the orifices of the flanges are of triangular shape. The successive triangular orifices e.g. isosceles triangles and equilateral triangles are arranged in a staggered and head-to-tail configuration. An independent claim is also included for a turbomachine such as an aircraft turbojet or turboprop comprising a combustion chamber.</p> |
申请公布号 |
FR2890156(A1) |
申请公布日期 |
2007.03.02 |
申请号 |
FR20050008891 |
申请日期 |
2005.08.31 |
申请人 |
SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION SNECMA SOCIETE ANONYME |
发明人 |
KREDER OLIVIER;PARENT DELPHINE;SEVI GUILLAUME |
分类号 |
F23R3/50;F02C7/12;F02C7/18 |
主分类号 |
F23R3/50 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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