A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.
Variable pitch fan of a gas turbine engine
08.10.2024
Patent
Elektronische Ressource
Englisch
Variable-pitch fan with low pitch of a turbine engine
Europäisches Patentamt | 2019
|Aircraft turbine engine comprising variable pitch propeller blades
Europäisches Patentamt | 2024
|VARIABLE PITCH MOUNTING FOR AIRCRAFT GAS TURBINE ENGINE
Europäisches Patentamt | 2016
|VARIABLE PITCH MOUNTING FOR AIRCRAFT GAS TURBINE ENGINE
Europäisches Patentamt | 2016
|TURBINE ENGINE HAVING A VARIABLE PITCH AIRFOIL ASSEMBLY
Europäisches Patentamt | 2025
|