发明名称 |
Estructura de soporte para un motor de turbina de gas, motor de turbina de gas, avión y método de construcción correspondientes |
摘要 |
The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26). According to the present invention, the first material type is different from the second material type. |
申请公布号 |
ES2605102(T3) |
申请公布日期 |
2017.03.13 |
申请号 |
ES20110877972T |
申请日期 |
2011.12.23 |
申请人 |
Volvo Aero Corporation |
发明人 |
ARONSSON, Egon;WIDSTRÖM, Per;MAGNUSSON, Elinor;THORÈUS, Johan;LUNDH, Christian |
分类号 |
B23P15/04;B23K1/00;B23P15/00;F01D5/14;F01D9/04 |
主分类号 |
B23P15/04 |
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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