Transpirationally cooled exhaust center body for an aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-11560847-B2
Application number	US-202117224514-A
Country	US
Kind code	B2
Filing date	Apr 7, 2021
Priority date	Apr 7, 2020
Publication date	Jan 24, 2023
Grant date	Jan 24, 2023

Abstract

An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.

First claim

What is claimed is:

1. An assembly for an aircraft propulsion system, comprising:
an outer nacelle structure;
an inner nacelle structure at least partially covered by the outer nacelle structure;
an exhaust center body comprising an exterior skin, the exterior skin forming an inner peripheral portion of a core flow path within the aircraft propulsion system;
a nozzle extending circumferentially around and radially spaced outward from the exhaust center body, the nozzle forming an outer peripheral portion of the core flow path; and
a duct system fluidly coupled with a plurality of exterior skin perforations in the exterior skin, the duct system configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the plurality of exterior skin perforations, and the bypass flow path at least partially formed by and radially between the outer nacelle structure and the inner nacelle structure.

2. The assembly of claim 1 , wherein the plurality of exterior skin perforations are configured to direct the bypass air received from duct system out of the exhaust center body to cool the exhaust center body.

3. The assembly of claim 1 , wherein the duct system comprises a scoop that projects radially into the bypass flow path.

4. The assembly of claim 1 , wherein the duct system extends radially across the core flow path.

5. The assembly of claim 1 , wherein the exhaust center body is configured with a single layer skin that consists of the exterior skin.

6. The assembly of claim 1 , wherein
the exhaust center body further includes a porous layer of sound attenuating material; and
the duct system is configured to direct the bypass air received from the bypass flow path through the porous layer of sound attenuating material to the plurality of exterior skin perforations.

7. The assembly of claim 1 , wherein
the exhaust center body comprises a structural panel;
the structural panel includes the exterior skin, an interior skin and a core that is between and connected to the exterior skin and the interior skin;
a plurality of cavities within the core fluidly couple a plurality of interior skin perforations in the interior skin with the plurality of exterior skin perforations; and
the duct system is fluidly coupled with the plurality of exterior skin perforations through the plurality of interior skin perforations and the plurality of cavities.

8. The assembly of claim 7 , wherein a quantity of the plurality of exterior skin perforations in the exterior skin is equal to a quantity of the plurality of interior skin perforations in the interior skin.

9. The assembly of claim 7 , wherein a quantity of the plurality of exterior skin perforations in the exterior skin is different than a quantity of the plurality of interior skin perforations in the interior skin.

10. The assembly of claim 7 , wherein
a first of the plurality of the exterior skin perforations has a first size;
a second of the plurality of the interior skin perforations has a second size; and
the first size is equal to the second size.

11. The assembly of claim 7 , wherein
a first of the plurality of the exterior skin perforations has a first size;
a second of the plurality of the interior skin perforations has a second size; and
the first size is different than the second size.

12. The assembly of claim 7 , wherein the structural panel is configured such that one of the interior skin perforations feeds the bypass air to an array of the plurality of cavities.

13. The assembly of claim 7 , wherein
the core includes a sidewall between and partially forming a first of the plurality of cavities and a second of the plurality of cavities; and
the sidewall is configured with an aperture that fluidly couples the first of the plurality of cavities with the second of the plurality of cavities.

14. The assembly of claim 1 , wherein the exhaust center body comprises a noise attenuating structural panel that includes the exterior skin.

15. An assembly for an aircraft propulsion system, comprising:
a compressor section, a combustor section, a turbine section and a core flow path extending sequentially through the compressor section, the combustor section and the turbine section;
an exhaust center body including an exterior skin and a porous layer of sound attenuating material located inward of and overlapped by the exterior skin, the exterior skin forming an inner peripheral portion of the core flow path; and
a duct system configured to direct cooling air through the porous layer of sound attenuating material to a plurality of exterior skin perforations in the exterior skin for cooling the exhaust center body.

16. The assembly of claim 15 , wherein the duct system is configured to receive the cooling air from a bypass flow path within the aircraft propulsion system.

17. An assembly for an aircraft propulsion system, comprising:
an exhaust center body comprising a structural panel;
the structural panel including an exterior skin, an interior skin and a core arranged between and connected to the exterior skin and the interior skin; and
the exterior skin configured as an exterior flow skin of the exhaust center body, and the exterior flow skin configured to form an inner peripheral portion of a core flow path which extends through a compressor section, a combustor section and a turbine section of the aircraft propulsion system;
wherein one or more cavities within the core fluidly couple one or more interior skin perforations in the interior skin with one or more exterior skin perforations in the exterior skin.

18. The assembly of claim 15 , wherein the porous layer of sound attenuating material comprises ceramic felt.

Assignees

• Rohr Inc

Inventors

• Kelford Bryce T
• Saunders Adam
• Alloway Richard S
• Haslim Richard
• Frazier Travis M

Classifications

• F02C6/20

  Adaptations of gas-turbine plants for driving vehicles · CPC title

• F02C7/141 Primary

  of working fluid · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B64D33/08 Primary

  of power plant cooling systems · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title