Exhaust nozzle of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11326552-B2
Application number	US-201916719079-A
Country	US
Kind code	B2
Filing date	Dec 18, 2019
Priority date	Dec 18, 2019
Publication date	May 10, 2022
Grant date	May 10, 2022

Abstract

An exhaust nozzle of a gas turbine engine includes: a nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. One of the struts is connected to the wall by a coupling arrangement that includes two first brackets and a third bracket, the brackets being spaced in an axial direction and being connected either directly to the wall or to a sliding element that is arranged in a displaceable manner in the wall. The brackets each have a first, highest stiffness in a first direction and smaller stiffnesses in a second and third direction. The brackets are oriented such that with the two first brackets, the first direction is aligned with a circumferential direction of the nozzle and that with the third bracket, the first direction is aligned with the axial direction of the nozzle.

First claim

The invention claimed is:

1. An exhaust nozzle of a gas turbine engine, wherein the exhaust nozzle comprises:
a nozzle wall,
a flow channel which is limited radially outwards by the nozzle wall,
a centerbody arranged in the flow channel, and
at least two struts connecting the centerbody to the nozzle wall,
wherein at least one of the at least two struts is connected to the nozzle wall by a coupling arrangement that comprises brackets, including at least two first brackets and at least one third bracket, the brackets being spaced in an axial direction, each of the brackets having a first end, a second end, and a bendable surface in between the first and second ends, wherein the first end is connected to the at least one of the at least two struts and the second end is connected either directly to the nozzle wall or to a sliding element that is arranged in a displaceable manner in the nozzle wall,
wherein the brackets each have a first, highest stiffness in a first direction and smaller stiffnesses in a second direction and a third direction, wherein the first, second and third directions are perpendicular to each other,
wherein the brackets are oriented such that with the at least two first brackets, the first direction in which the stiffness is highest is aligned with a circumferential direction of the nozzle and that with the at least one third bracket, the first direction in which the stiffness is highest is aligned with the axial direction of the nozzle.

2. The nozzle of claim 1 , wherein the bendable surface of the at least two first brackets extends in a radial direction and the circumferential direction.

3. The nozzle of claim 1 , wherein the bendable surface of the at least one third bracket extends in a radial direction and the axial direction.

4. The nozzle of claim 1 , wherein the at least one third bracket is located between two of the at least two first brackets in the axial direction.

5. The nozzle of claim 1 , wherein the first and second ends of two of the at least two first brackets point towards each other in the axial direction.

6. The nozzle of claim 1 , wherein the brackets have a different radial length to compensate for a different radial distance between the at least one of the at least two struts and the nozzle wall at different axial locations.

7. The nozzle of claim 1 , wherein the first and second ends of the brackets are formed by surfaces that are angled or bent with respect to the bendable surface.

8. The nozzle of claim 1 , wherein at least one of the brackets is C-shaped.

9. The nozzle of claim 1 , wherein at least one of the brackets is Z-shaped.

10. The nozzle of claim 1 , wherein at least one of the brackets is U-shaped.

11. The nozzle of claim 1 , wherein the brackets are connected at the nozzle wall side to a sliding element, wherein the sliding element is arranged in a receiving slot that extends in the axial direction in the nozzle wall.

12. The nozzle of claim 11 , wherein the at least one third bracket comprises at one chosen from the first and second ends, an extension surface connected to a flat surface of the sliding element.

13. The nozzle of claim 1 , wherein the brackets consist of a metal or a metal alloy.

14. The nozzle of claim 1 , wherein the brackets consist of a nickel-chromium-molybdenum alloy.

15. The nozzle of claim 1 , wherein the brackets have a width in a range between 60 mm and 100 mm.

16. The nozzle of claim 1 , wherein the brackets have a thickness in a range between 1 mm and 4 mm.

17. The nozzle of claim 1 , wherein there are provided exactly three brackets at each coupling arrangement between one of the struts and the nozzle wall.

18. The nozzle of claim 1 , wherein the nozzle comprises exactly two struts.

19. The nozzle of claim 1 , wherein the nozzle has a convergent-divergent cross-section.

20. The nozzle of claim 1 , wherein the nozzle is configured as the nozzle of a supersonic gas turbine engine.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag

Classifications

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F02K1/80

  Couplings or connections · CPC title

• F02K1/08 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title