发明名称 |
GAS TURBINE ENGINE COMPRISING A COMPOSITE COMPONENT AND A METAL COMPONENT WHICH ARE CONNECTED BY A FLEXIBLE FIXING DEVICE |
摘要 |
<p>A gas turbine engine for powering an aircraft, said engine extending axially from upstream to downstream and comprising a composite component (3), a metal component (2) and a flexible device (4) for fixing said components (2, 3) together, said fixing device (4) comprising: - a flexible connecting element (5) comprising a first fixing part (51) connected to the metal component (2) by an axial connection (B1) and a second fixing part (53) connected to the composite component (3) by an axial connection (B2), the said connecting element (5) comprising a free end (55) that extends axially; and - a rigid locking element (6) comprising a fixing part (61) connected to the metal component (2) by an axial connection (B1) and a free end (63) extending axially, the free end (63) of the locking element (6) being radially aligned with the free end (55) of the connecting element (5) so as to limit the deformation suffered by the connecting element (5) during engine operation.</p> |
申请公布号 |
WO2014001682(A1) |
申请公布日期 |
2014.01.03 |
申请号 |
WO2013FR51378 |
申请日期 |
2013.06.12 |
申请人 |
SNECMA |
发明人 |
BEAUJARD, ANTOINE, JEAN-PHILIPPE;BART, JACQUES, RENE |
分类号 |
F01D25/24;F02K1/04;F02K1/80 |
主分类号 |
F01D25/24 |
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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