发明名称 |
FAN PLATFORM WITH LEADING EDGE TAB |
摘要 |
A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed. |
申请公布号 |
EP3047109(A4) |
申请公布日期 |
2016.10.05 |
申请号 |
EP20140852016 |
申请日期 |
2014.08.06 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
ALARCON, ANDREW G. |
分类号 |
F01D5/30;F01D5/02;F02K3/06 |
主分类号 |
F01D5/30 |
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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