发明名称 |
COMBUSTION CHAMBER FOR A TURBINE ENGINE |
摘要 |
A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall. |
申请公布号 |
US2012240584(A1) |
申请公布日期 |
2012.09.27 |
申请号 |
US201013514060 |
申请日期 |
2010.12.02 |
申请人 |
BERDOU CAROLINE JACQUELINE DENISE;CAMERIANO LAURENT BERNARD;SNECMA |
发明人 |
BERDOU CAROLINE JACQUELINE DENISE;CAMERIANO LAURENT BERNARD |
分类号 |
F02C1/00 |
主分类号 |
F02C1/00 |
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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