Patent ID: 8932018
Filing Date: 2015-01-13
Classification: B64C,B64D,F01D,F02C,F04D,F05D,Y02T,Y10T

Abstract:
1. A control device for orientation of fan blades of a turboprop, comprising: at least one set of fan blades having adjustable orientation, the set being attached in rotation to a rotating ring mechanically linked to a rotor of a turbine, each blade of the set being coupled, for control of its orientation, to a blade root support mounted pivotably on the rotating ring by a conical gear train including a first gear wheel attached to the blade root support and centered on an axis radial to the rotating ring and a second gear wheel attached to the rotating ring, centered on an axis tangential to the rotating ring, and bearing a counterweight that is eccentric with respect to an axis of rotation of the second gear wheel; and a cylinder centered on the axis of rotation of the rotating ring, attached in rotation to the turbine rotor and a rod of which is connected to each counterweight through connecting arms so as to impart synchronous angular motion to the set of counterweights about the axis of rotation of their respective gear wheel, each connecting arm including a radial link having one end connected to the corresponding counterweight and the other end connected to an arm of a bellcrank in which another arm is connected to the cylinder rod.