发明名称 |
METHOD AND APPARATUS FOR REDUCING ROTAR ASSEMBLY CIRCUMFERENTIAL RIM STRESS |
摘要 |
A rotor assembly (10) for a gas turbine engine (12) operates with reduced circumferential rim stress. The rotor assembly includes a rotor (14) including a plurality of rotor blades (26) extending radially outward from an annular rim (20). A root fillet (80) extends circumferentially around each blade between the blades and rim. The rim includes an outer surface (28) including a plurality of concave indentations (90) extending between adjacent rotor blades and forming a compound radius. Each indentation extends from a leading edge (40) of the rotor blade s towards a trailing edge (42) of the rotor blades. |
申请公布号 |
CA2358673(A1) |
申请公布日期 |
2002.04.20 |
申请号 |
CA20012358673 |
申请日期 |
2001.10.11 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
DECKER, JOHN JARED;MIELKE, MARK JOSEPH |
分类号 |
F01D5/02;F01D5/06;F01D5/14;F01D5/34;F04D29/32;(IPC1-7):F01D5/02;B23P15/00 |
主分类号 |
F01D5/02 |
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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