发明名称 |
Fan blade for a turbofan gas turbine engine |
摘要 |
A fan (12) for a turbofan gas turbine engine comprises a rotor hub (36) and a plurality of radially extending fan blades (20) integral with the hub (36) to form an integrally bladed rotor. Each fan blade (20) defines a leading edge (34). A hub radius (R HUB ) is the radius of the leading edge (34) at the hub (36) relative to a centerline of the fan. A tip radius (R TIP ) is the radius of the leading edge (34) at a tip (40) of the fan blade (20) relative to the centerline of the fan. The ratio of the hub radius to the tip radius (R HUB /R TIP ) is at least less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than or equal to 0.25. |
申请公布号 |
EP2738392(A3) |
申请公布日期 |
2014.12.24 |
申请号 |
EP20130194497 |
申请日期 |
2013.11.26 |
申请人 |
PRATT & WHITNEY CANADA CORP. |
发明人 |
HEIKURINEN, KARL;TOWNSEND, PETER |
分类号 |
F04D29/02;B23K20/12;F01D5/30;F01D5/34;F04D29/32 |
主分类号 |
F04D29/02 |
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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