Patent ID: 9382845
Filing Date: 2016-07-05
CPC Classification: F02C,F02K,Y02T

Claim Text:
1. An inner structure for a nacelle for a turbine engine of an aircraft, concentric along a longitudinal axis passing through the center of said structure and comprising a plurality of active and passive mobile elements, each active mobile element is formed with one or several mobile portions and each active mobile element is configured so as to drive adjacent passive mobile elements so that the inner structure has a first rated position in which the active mobile elements are in aerodynamic continuity with the passive mobile elements, a second position in which the active mobile elements jut out from the passive mobile elements towards the outside of the inner structure relative to the center of the inner structure after the active mobile elements have driven the passive mobile elements and a third position in which the active mobile elements jut out from the passive mobile elements towards the inside of the inner structure relative to the center of the inner structure, after the active mobile elements have driven the passive mobile elements.