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Low hub-to-tip ratio fan for a turbofan gas turbine engine

机译：用于涡轮风扇燃气涡轮发动机的低轮毂对叶尖比的风扇

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摘要

A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (R_HUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (R_TIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (R_HUB/R_TIP) is 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 0.25.

机译：公开了一种用于涡轮风扇燃气涡轮发动机的风扇，其具有低的轮毂对顶部的比率。风扇包括转子毂和多个径向延伸的风扇叶片。每个风扇叶片均定义了轮毂半径（R _{HUB ），该半径是指轮毂前缘相对于风扇中心线的半径，而尖端半径（R _{TIP ），它是风扇叶片尖端的前缘相对于风扇中心线的半径。轮毂半径与尖端半径之比（R _{HUB / R _{TIP ）小于0.29。在特定的实施方案中，该比率在0.25至0.29之间。在另一特定实施例中，该比率小于0.25。}}}}

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公开/公告号US9709070B2

专利类型
公开/公告日2017-07-18

原文格式PDF
申请/专利权人 PRATT & WHITNEY CANADA CORP.;
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申请/专利号US201615052178
发明设计人 KARL HEIKURINEN;PETER TOWNSEND;
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申请日2016-02-24
分类号F04D29/38;F04D29/32;F04D29/34;F04D29/64;F04D29/02;F01D5/30;F01D5/34;F02K3/06;B23K20/12;F01D5/14;B23K101;
国家 US
入库时间 2022-08-21 13:45:57

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