TURBOFAN EXHAUST SYSTEM

Abstract

The present invention relates to a turbofan exhaust system comprising at least one exhaust nozzle (13; 17) with a trailing edge having an upper edge (13s; 17s), a lower edge (13i; 17i), an inner lateral edge (13int; 17int) and an outer lateral edge (13ext; 17ext), the upper edge (13s; 17s) being upstream with respect to the lower edge (13i; 17i). According to the invention, the exhaust system is characterized in that the outer lateral edge (13ext; 17ext) of the exhaust nozzle is also upstream of the inner lateral edge (13int; 17int).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will now be described in more detail with reference to the drawings, in which

FIG. 1 is a side view showing the rear part of a jet engine nacelle according to the prior art;

FIG. 2 is a side view, from the outer side, showing the rear part of a jet engine nacelle according to the invention;

FIG. 3 is a plan view showing the nacelle of FIG. 2 mounted below an aircraft wing;

FIG. 4 shows an embodiment of the invention applied to a nozzle for mixed primary and secondary streams. The engine is shown in a rear three-quarter perspective with part of the casing cut away.

Claims

1. A turbofan exhaust system comprising at least one exhaust nozzle with a trailing edge having an upper edge, a lower edge, an inner lateral edge and an outer lateral edge, the upper edge being upstream with respect to the lower edge, wherein the outer lateral edge of the exhaust nozzle is also upstream of the inner lateral edge.

2. The system as claimed in the preceding claim, wherein the trailing edge forms a plane of angle A1 with the vertical of between 5 and 15°.

3. The system as claimed in either of the preceding claims, wherein the trailing edge forms a plane of angle A2 with the horizontal direction of between 5 and 15°.

4. The system as claimed in either of claims 2 and 3, wherein the angles A1 and A2 are equal.

5. An exhaust system for a jet engine having a separately exhausted primary stream and secondary stream and comprising a nozzle for the primary stream and a nozzle for the secondary stream, wherein at least one of the two nozzles is configured as claimed in one of claims 1 to 4.

6. An exhaust system for a jet engine having a mixed primary stream and secondary stream, wherein the exhaust nozzle for the mixed stream is configured as claimed in one of claims 1 to 4.

7. A turbofan comprising an exhaust system as claimed in one of claims 1 to 6.