Discharge system of a separated twin-flow turbojet for an aircraft, corresponding turbojet and associated design method
View Patent ↗A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.
1. A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, said discharge system comprising:
a main nozzle delimited by an annular cowl extending along a longitudinal axis, said cowl comprising a slot of annular shape which defines an upstream portion of the cowl and a downstream portion of the cowl, said slot configured to elect air and being traversed by the suspension mast of the turbojet,
wherein the downstream portion of the cowl of the main nozzle comprises:
a first part extending downstream from the upstream portion of the cowl to a first trailing edge, the first part extending circumferentially on respective sides of the suspension mast along a first angular sector and a second angular sector, the first part terminating the slot at respective circumferential ends of the first and second angular sectors, and
a second part extending circumferentially along a third angular sector between the first and second angular sectors and which is formed from an internal contour of the slot, said second part extending downstream from the slot to a second trailing edge,
wherein the first part is defined by a first generatrix line revolved about a length of the longitudinal axis along the first and second angular sectors, and the second part is defined by a second generatrix line revolved about the length of the longitudinal axis along the third angular sector, wherein the second generatrix line is offset radially inward from the first generatrix line,
wherein a trailing edge of the main nozzle is defined by the first trailing edge and the second trailing edge, and the trailing edge of the main nozzle is non-axisymmetric, and
wherein the first and second parts of the downstream portion are connected laterally to one another with a first connecting wall and a second connecting wall.
2. The discharge system as claimed in claim 1 , wherein the first generatrix line is a straight line of the upstream portion of the cowl.
3. The discharge system as claimed in claim 1 , wherein the first generatrix line is a concave curved line.
4. The discharge system as claimed in claim 1 , wherein the first and second connecting walls are respectively defined by a curved line in a transverse plane orthogonal to the longitudinal axis.
5. The discharge system as claimed in claim 4 , wherein the curved line has a point of inflexion.
6. The discharge system as claimed in claim 1 , wherein the first and second connecting walls are respectively defined by a straight line in a transverse plane orthogonal to the longitudinal axis.
7. A separated twin-flow turbojet, which comprises the discharge system as described in claim 1 .
8. A method of providing a discharge system of a separated twin-flow turbojet for an aircraft, said turbojet being supported by a suspension mast, the discharge system comprising a main nozzle delimited by an annular cowl extending along a longitudinal axis, said cowl comprising a slot of annular shape which defines an upstream portion of the cowl and a downstream portion of the cowl, said slot configured to elect air and being traversed by the suspension mast of the turbojet,
the method comprising:
providing a downstream portion of the cowl of the main nozzle comprising:
a first part extending downstream from the upstream portion of the cowl to a first trailing edge, the first part extending circumferentially on respective sides of the suspension mast along a first angular sector and a second angular sector, the first part terminating the slot at respective circumferential ends of the first and second angular sectors;
a second part extending circumferentially along a third angular sector between the first and second angular sectors and which is formed from an internal contour of the slot, said second part extending downstream from the slot to a second trailing edge, said first trailing edge and said second trailing edge defining a trailing edge of the main nozzle which is non-axisymmetric,
wherein the first part is defined by a first generatrix line revolved about a length of the longitudinal axis along the first and second angular sectors and the second part is defined by a second generatrix line revolved about the length of the longitudinal axis along the third angular sector, wherein the second generatrix line is offset radially inward from the first generatrix line, and
connecting a first lateral end of the first part to a first lateral end of the second part with a first connecting wall, and connecting a second lateral end of the first part and a second lateral end of the second part with a second connecting wall.
9. The method as claimed in claim 8 , wherein the first generatrix line is a straight line.
10. The method as claimed in claim 8 , wherein the first generatrix line is a concave curved line.