Core air flow to equalize temperature differential

Patent metadata

Field	Value
Publication number	US-11085398-B2
Application number	US-201916351031-A
Country	US
Kind code	B2
Filing date	Mar 12, 2019
Priority date	Mar 12, 2019
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.

First claim

What is claimed is:

1. A gas turbine exhaust nozzle assembly, comprising:
an engine flange;
an exhaust nozzle that extends circumferentially about an axial centerline, comprising
an exhaust nozzle flange that is removably and replaceably secured to the engine flange;
a radially inner surface that comprises an axially forward inner surface;
a noise attenuating structure comprising a perforated layer, a base layer, and a core layer, all of which are radially stacked in a superimposed relationship so that the core layer is disposed between the perforated layer and the base layer;
an axially rear inner surface that is axially rearward of the noise attenuating structure, where the axially forward inner surface, the perforated layer and the axially rear inner surface are radially aligned to form the radially inner surface;
at least one through hole inlet formed in at least one of the axially forward inner surface and the base layer;
at least one through hole outlet formed in the axially rear inner surface; and
a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the at least one through hole inlet and exits the nozzle cavity axially downstream of the at least one through hole inlet via the at least one through hole outlet.

2. The gas turbine exhaust nozzle assembly of claim 1 , wherein the perforated layer is configured to permit noise to pass there-through, the core layer includes a substructure that is operable to receive an amount of the noise that passes through the perforated layer that is operable to reflect the amount of the noise off the base layer such that sound waves of reflected noise are out of phase with and destructively interfere with sound waves of noise outside the substructure.

3. The gas turbine exhaust nozzle assembly of claim 2 , wherein the substructure comprises a honey-comb shaped matrix.

4. The gas turbine exhaust nozzle assembly of claim 2 , wherein the substructure includes at least one of an N-shaped core, a rod shaped core or a deep cavity structure.

5. The gas turbine exhaust nozzle assembly of claim 1 , where the base layer and the perforated layer are manufactured from ceramic matrix composites.

6. The gas turbine exhaust nozzle assembly of claim 1 , where the base layer is imperforate and the engine core air enters the nozzle cavity through the axially forward inner surface.

7. The gas turbine exhaust nozzle assembly of claim 1 further comprising an exhaust centerbody radially within the axially forward inner surface and coaxial with the axial centerline.

8. The gas turbine exhaust nozzle assembly of claim 1 , where the core air originates from a low pressure turbine outlet.

9. The gas turbine exhaust nozzle assembly of claim 8 , further comprising a seal axially upstream of the at least one through hole inlet to prevent back flow of the core air from the nozzle cavity.

10. A gas turbine exhaust nozzle assembly, comprising:
an engine flange;
an exhaust nozzle that extends circumferentially about an axial centerline, comprising an exhaust nozzle flange that is removably and replaceably secured to the engine flange;
a radially inner surface that comprises an imperforate axially forward inner surface;
a noise attenuating structure comprising a first perforated layer, a second perforated layer, and a core layer, all of which are radially stacked in a superimposed relationship so that the core layer is disposed between the first and the second perforated layers;
an axially rear inner surface that is axially rearward of the noise attenuating structure, where the axially forward inner surface, the first perforated layer and the axially rear inner surface are radially aligned to form the radially inner surface;
a through hole outlet formed in the axially rear inner surface; and
a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity by passing through the first and the second perforated layers and exits the nozzle cavity via the through hole outlet located axially aft of the first and the second perforated layers.

11. The gas turbine exhaust nozzle assembly of claim 10 , wherein the through hole outlet is one of a plurality of through hole outlets arranged annularly on the axially rear inner surface about the axial centerline.

12. The gas turbine exhaust nozzle assembly of claim 10 , wherein the through hole outlet is an annular slit axially downstream of the noise attenuating structure and in the axially rear inner surface about the axial centerline, where the annular slit allows core air within the nozzle cavity to exit the nozzle cavity and mix with core air that did not enter the nozzle cavity.

13. The gas turbine exhaust nozzle assembly of claim 10 , wherein a thrust reverser is axially forward of the exhaust nozzle.

14. The gas turbine exhaust nozzle assembly of claim 10 , where the core air originates from a low pressure turbine outlet.

15. The gas turbine exhaust nozzle assembly of claim 14 further comprising a bracket that connects the radially outer surface with a radially exterior surface of the second perforated layer, where a seal is located between the second perforated layer and the radially outer surface.

Assignees

• Rohr Inc

Inventors

• Aten Michael
• Saunders Adam
• Bowman Gary E

Classifications

• F02K1/52

  Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing · CPC title

• F02K1/76

  Control or regulation of thrust reversers · CPC title

• F02K1/827 Primary

  Sound absorbing structures or liners · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F02K1/64

  Reversing fan flow · CPC title