Exhaust cone

Patent metadata

Field	Value
Publication number	US-9062610-B2
Application number	US-201314108799-A
Country	US
Kind code	B2
Filing date	Dec 17, 2013
Priority date	Jan 31, 2013
Publication date	Jun 23, 2015
Grant date	Jun 23, 2015

Abstract

A gas turbine engine exhaust cone ( 40 ) comprising one or more acoustic absorption chambers ( 48 ), each chamber ( 48 ) comprising two side walls ( 50 ) and an acoustic attenuation wall ( 62 ). The side walls ( 50 ) define the circumferential extent of the chamber ( 48 ). The acoustic attenuation wall ( 62 ) has one or more acoustic attenuators ( 64 ) and is positioned circumferentially intermediate the side walls ( 50 ). The side walls ( 50 ) extend axially along the exhaust cone ( 40 ) at least one of them with a circumferential progression. The acoustic attenuation wall ( 62 ) extends axially along the exhaust cone ( 40 ) with or without a circumferential progression.

First claim

The invention claimed is:

1. A gas turbine engine exhaust cone comprising one or more acoustic absorption chambers, each chamber comprising two side walls and an acoustic attenuation wall, the side walls defining the circumferential extent of the chamber and the acoustic attenuation wall having one or more acoustic attenuators and being positioned circumferentially intermediate the side walls, where the side walls extend axially along the exhaust cone at least one of them with a circumferential progression and the acoustic attenuation wall extends axially along the exhaust cone with or without a circumferential progression, where the side walls are imperforate, and where the acoustic attenuation wall is substantially parallel to the side walls.

2. A gas turbine engine exhaust cone according to claim 1 where the chamber further comprises inner and outer walls defining the radial extent of the chamber.

3. A gas turbine engine exhaust cone according to claim 1 where the chamber further comprises one or more end walls closing the chamber at its distal end.

4. A gas turbine engine exhaust cone according to claim 3 where the side walls and acoustic attenuation wall of the chamber are arranged so that assuming reflection at side walls, at least one wave propagation path is provided passing through the acoustic attenuation wall at least three times and where the path length along the wave propagation path between each passage through the acoustic attenuation wall is substantially equal to or a multiple of the shortest path length between acoustic attenuation wall passages.

5. A gas turbine engine exhaust cone according to claim 4 where the side walls and acoustic attenuation wall of the chamber are arranged so that there are two or more such wave propagation paths.

6. A gas turbine engine exhaust cone according to claim 5 where at least some of the different wave propagation paths target absorption of different acoustic wavelengths, each wave propagation path passing through the acoustic attenuation wall at least three times and having path lengths along the wave propagation path between each passage through the acoustic attenuation wall equal to half the wavelength of acoustic waves targeted for absorption or a multiple thereof.

7. A gas turbine engine exhaust cone according to claim 4 where the acoustic attenuators intersecting wave propagation paths are tailored to absorption of acoustic waves of the wavelength corresponding to that targeted along that wave propagation path.

8. A gas turbine engine exhaust cone according to claim 4 where at least one of the wave propagation paths incorporates at least one reflection at one, more or all of the end walls of the chamber.

9. A gas turbine engine exhaust cone according to claim 8 where the end walls are arranged to cause reflection of a wave back along its wave propagation path incident towards the end walls.

10. A gas turbine engine exhaust cone according to claim 1 where the side walls and acoustic attenuation wall of the chamber are parallel.

11. A gas turbine engine exhaust cone according to claim 1 where the side walls of the chamber are non-parallel.

12. A gas turbine engine exhaust cone according to claim 3 where at least one chamber has a single end wall comprising a concave spherical wall and concave parabolic walls extending between the concave spherical wall and the side, inner and outer walls, where the centre of the sphere defining the spherical wall and the focus of the parabolic walls coincide at a single point.

13. A gas turbine engine exhaust cone according to claim 1 where one or more inner cavities are provided radially inwards of the chambers with at least one inner acoustic inlet region arranged to allow the passage of acoustic waves into one or more of the inner cavities being provided in the inner wall of at least one chamber.

14. An acoustic absorption chamber in accordance with claim 1 .

15. A gas turbine engine provided with an exhaust cone according to claim 1 .

Assignees

• Rolls Royce Plc

Inventors

• Morvant Romuald

Classifications

• F02K1/44

  Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction (F02K1/40 takes precedence) · CPC title

• F02K1/827

  Sound absorbing structures or liners · CPC title

• F02C7/24 Primary

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F02K1/34 Primary

  for attenuating noise · CPC title