Propelling nozzle for a turbofan engine on a supersonic aircraft

Patent metadata

Field	Value
Publication number	US-11448162-B2
Application number	US-201816954053-A
Country	US
Kind code	B2
Filing date	Dec 5, 2018
Priority date	Dec 19, 2017
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle including: a propelling nozzle wall, a duct, which is radially outwardly bounded by the propelling nozzle wall, and a central body arranged in the duct. According to the invention, the central body is connected to the propelling nozzle wall via at least one brace.

First claim

The invention claimed is:

1. A thrust nozzle for a turbofan engine of a supersonic aircraft, wherein the thrust nozzle comprises:
a thrust nozzle wall,
a flow channel which is delimited radially to an outside by the thrust nozzle wall,
a central body arranged in the flow channel,
two struts connecting the central body to the thrust nozzle wall,
a thrust reverser integrated into the thrust nozzle, the thrust reverser including two pivotable thrust reverser doors which are rotatably mounted in two side structures of the thrust nozzle wall, the two side structures being formed on opposite sides of the thrust nozzle wall,
the two struts being connected respectively to the two side structures of the thrust nozzle wall, and
wherein the thrust reverser doors are, in a pivoted position, arranged such that radially inner ends thereof are arranged at least partially downstream of leading edges of the two struts and at the same time lie against the two struts.

2. The thrust nozzle as claimed in claim 1 , wherein the two struts each have a profile with one of the leading edges and a trailing edge.

3. The thrust nozzle as claimed in claim 1 , wherein the central body is connected via exactly two struts of the at least two struts to the thrust nozzle wall, wherein the exactly two struts are arranged in a same plane.

4. The thrust nozzle as claimed in claim 1 , wherein the thrust nozzle includes an upstream coupling region configured for being connected to housing components of the core engine, wherein the two struts, the thrust nozzle wall and the upstream coupling region are arranged such that forces acting on the central body are conducted via the two struts and the thrust nozzle wall into the upstream coupling region.

5. The thrust nozzle as claimed in claim 1 , wherein the two side structures are structurally reinforced to be structurally stronger than other regions of the thrust nozzle wall.

6. The thrust nozzle as claimed in claim 5 , wherein the two side structures comprise ribbed stiffening elements which structurally reinforce the two side structures, and the two side structures are connected to one another at a top and a bottom by semicircular structural elements.

7. The thrust nozzle as claimed in claim 6 , wherein the central body is fixed with respect to the thrust nozzle wall in an axial direction.

8. The thrust nozzle as claimed in claim 6 , wherein the central body is axially displaceable with respect to the thrust nozzle wall.

9. The thrust nozzle as claimed in claim 8 , wherein the central body is axially displaceable relative to the two struts.

10. The thrust nozzle as claimed in claim 8 , wherein the two struts are axially displaceable relative to the thrust nozzle wall.

11. The thrust nozzle as claimed in claim 6 , wherein the thrust nozzle wall is configured to be non-adjustable with regard to a nozzle throat area thereof and a nozzle exit area thereof.

12. The thrust nozzle as claimed in claim 6 , wherein an upstream end of the central body is arranged downstream of the leading edges of the two struts, wherein the two struts adjoin one another at the radially inner ends.

13. The thrust nozzle as claimed in claim 12 , wherein the leading edges of the two struts collectively form an arcuate curve which extends furthest upstream at radially outer ends of the two struts adjoining the thrust nozzle wall and extends furthest downstream at a centerline of the thrust nozzle.

14. The thrust nozzle as claimed in claim 6 , wherein an upstream end of the central body is arranged at the leading edge of at least one of the two struts or upstream of the leading edge of at least one of the two struts.

15. The thrust nozzle as claimed in claim 6 , wherein the central body is of conical shape at an upstream end thereof and/or at a downstream end thereof and forms at least one maximum of a cross-sectional area thereof between the upstream end and the downstream end.

16. The thrust nozzle as claimed in claim 6 , wherein the central body is rotationally symmetrical.

17. The thrust nozzle as claimed in claim 6 , wherein at least the leading edges of the two struts are positioned axially upstream of a nozzle throat of the thrust nozzle.

18. The thrust nozzle as claimed in claim 6 , wherein the thrust nozzle is formed as a convergent-divergent thrust nozzle or as a convergent-cylindrical thrust nozzle.

19. The thrust nozzle as claimed in claim 6 , wherein the central body is connected to the thrust nozzle, and mounted therein, exclusively via the two struts, and no further structural components are present which absorb forces acting on the central body.

20. A thrust nozzle for a turbofan engine of a supersonic aircraft, wherein the thrust nozzle comprises:
a thrust nozzle wall,
a flow channel which is delimited radially to an outside by the thrust nozzle wall,
a central body arranged in the flow channel,
at least two struts connecting the central body to the thrust nozzle wall,
a thrust reverser integrated into the thrust nozzle, the thrust reverser including two pivotable thrust reverser doors which are rotatably mounted in two side structures of the thrust nozzle wall, the two side structures being formed on opposite sides of the thrust nozzle wall,
the at least two struts being connected respectively to the two side structures of the thrust nozzle wall,
wherein the central body is axially displaceable with respect to the thrust nozzle wall, and
wherein the at least two struts are axially displaceable relative to the thrust nozzle wall.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag
• Schillinger Thomas

Classifications

• F02K1/60

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• F02K1/04 Primary

  Mounting of an exhaust cone in the jet pipe · CPC title

• F02K1/56 Primary

  Reversing jet main flow · CPC title

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title

• F02K1/78

  Other construction of jet pipes · CPC title