发明名称 |
TURBO-MACHINERY ROTORS WITH ROUNDED TIP EDGE |
摘要 |
A rotor for a gas turbine engine includes a plurality of radially extending blades, each having a remote blade tip defining an outer tip surface, and a leading edge defined between opposed pressure and suction side airfoil surfaces. A shroud circumferentially surrounds the rotor, and a radial distance between an inner surface of the shroud and the outer tip surface of the blades defines a radial tip clearance gap therebetween. The tip of each of the blades has a pressure side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface, and a suction side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface. The suction side edge has a larger radius of curvature than the pressure side edge, thereby reducing the amount of tip leakage flow through the radial tip clearance gap. |
申请公布号 |
CA2846376(A1) |
申请公布日期 |
2014.09.14 |
申请号 |
CA20142846376 |
申请日期 |
2014.03.13 |
申请人 |
PRATT & WHITNEY CANADA CORP. |
发明人 |
DUONG, HIEN;NICHOLS, JASON;KANDASAMY, VIJAY |
分类号 |
F01D11/08;F01D5/14;F01D11/10 |
主分类号 |
F01D11/08 |
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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