Invention Grant
- Patent Title: Low hub-to-tip ratio fan for a turbofan gas turbine engine
- Patent Title (中): 用于涡轮风扇燃气涡轮发动机的低毂对尖端风扇
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Application No.: US13687540Application Date: 2012-11-28
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Publication No.: US09303589B2Publication Date: 2016-04-05
- Inventor: Kari Heikurinen , Peter Townsend
- Applicant: PRATT & WHITNEY CANADA CORP.
- Applicant Address: CA Longueuil
- Assignee: PRATT & WHITNEY CANADA CORP.
- Current Assignee: PRATT & WHITNEY CANADA CORP.
- Current Assignee Address: CA Longueuil
- Agency: Norton Rose Fulbright Canada LLP
- Main IPC: F02K3/06
- IPC: F02K3/06 ; F04D29/02 ; F04D29/32 ; F01D5/30 ; F01D5/34 ; B23K20/12 ; F01D5/14
Abstract:
A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge. A hub radius (RHUB) is the radius of the leading edge at the hub relative to a centerline of the fan. A tip radius (RTIP) 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 (RHUB/RTIP) 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.
Public/Granted literature
- US20140356159A1 LOW HUB-TO-TIP RATIO FAN FOR A TURBOFAN GAS TURBINE ENGINE Public/Granted day:2014-12-04
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