发明名称 |
GAS TURBINE ENGINE COMPRESSOR STATOR SEAL |
摘要 |
<p>A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.</p> |
申请公布号 |
EP2847450(A4) |
申请公布日期 |
2015.05.06 |
申请号 |
EP20130797841 |
申请日期 |
2013.05.06 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
WARD, ERIC J. |
分类号 |
F01D5/06;F01D11/00;F01D11/02;F04D29/10 |
主分类号 |
F01D5/06 |
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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