Invention Grant
- Patent Title: Aircraft gas turbine engine variable fan blade mechanism
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Application No.: US15646460Application Date: 2017-07-11
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Publication No.: US10801339B2Publication Date: 2020-10-13
- Inventor: Aldo Daniel Lopez Guzman , Alberto del Angel Duran , Daniela Martinez Arteaga , Carla Garcia Lopez de Llergo , Ileana Prisabel Corona Acosta
- Applicant: General Electric Company
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Agency: Hanley, Flight & Zimmerman, LLC
- Main IPC: F01D7/00
- IPC: F01D7/00 ; F01D7/02 ; F04D29/36 ; B64C11/30

Abstract:
A variable pitch fan assembly includes variable pitch fan blades circumscribed about engine centerline axis coupled to a drive shaft centered about the engine centerline axis. Each blade pivotable about pitch axis perpendicular to centerline axis and having blade turning lever connected thereto. One or more linear actuators non-rotatably mounted parallel to engine centerline axis and operably linked to fan blades for pivoting fan blades and connected to spider ring through thrust bearings for transmission of axial displacement of non-rotatable actuator rods of actuators while the fan blades are rotating. Spider arms extending away from spider ring towards blade roots and each spider arm connected to one of the turning levers. Turning levers may be connected and caromed to spider arms by pin and slot joint. Each spider arm may include joint pin disposed through joint slot of turning lever. Joint slot may be angled or curved.
Public/Granted literature
- US20190017396A1 AIRCRAFT GAS TURBINE ENGINE VARIABLE FAN BLADE MECHANISM Public/Granted day:2019-01-17
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