Patent ID: 9279385
Filing Date: 2016-03-08
CPC Classification: F02K,F05D,Y02T

Claim Text:
1. A nacelle for an aircraft bypass turbojet engine, comprising: a downstream section comprising an inner fixed structure surrounding part of the aircraft bypass turbojet engine, and an outer structure at least partially surrounding the inner fixed structure so as to define an annular flow path along which an air flow circulates, the outer structure comprising at least one movable flap positioned at a downstream end of the outer structure and positioned facing the annular flow path, wherein said at least one movable flap pivots along a pivot axis of an elastic return device which directly connects said at least one movable flap to a stationary part of the outer structure at an upstream end of said at least one movable flap, and wherein each of said at least one movable flap under an effect of the elastic return device is configured to inwardly or outwardly rotate in a radial direction so as to move into a position that increases or reduces a height (h) of a cross-section of the annular flow path in relation to an idle position, in response to pressures exerted on said at least one movable flap by the air flow and by an outer air flow circulating outside of the nacelle.