Nacelle for an aircraft bypass turbojet engine
AssigneeAircelle
InventorsPatrick GONIDEC, Laurent Albert Blin
Life of this patent
Estimating the term…
Abstract
A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls. In particular, the internal return area allows the circulation of part of the injected auxiliary flow and the drawn-in auxiliary flow
Claims10
A nacelle for an aircraft bypass turbojet engine having a longitudinal axis and a rear section including an annular vein forming a space for circulation of a main air flow delimited by at least one wall of a fixed internal structure and at least one wall of an external structure, said nacelle comprising at least one device for modulating the cross section of said space, positioned in at least one of the wall of the external structure and the fixed internal structure, said device comprising:
- injection means for injecting an ancillary flow of a gas, configured for varying at least one of the orientation and the speed of said ancillary flow;
- suction means for sucking up at least one portion of this injected ancillary flow;
- and
- an internal area for return of the ancillary flow in one or several walls, said area being configured so as to allow circulation of a portion of the injected ancillary flow and of the sucked-up ancillary flow, and for putting into contact a portion of the injected gas ancillary flow and of the main air flow.
Dependencies are inferred from the claim text.