Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines

Patent metadata

Field	Value
Publication number	US-10094334-B2
Application number	US-201414172060-A
Country	US
Kind code	B2
Filing date	Feb 4, 2014
Priority date	Jun 5, 2007
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle. A mixer duct shell is supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell. A first portion of fan exhaust may be routed through the mixer duct shell between its inner surface and an outer surface of a core engine shroud. A second portion of fan exhaust may be routed over an outer surface of the mixer duct shell. At least one of the inner surface and an outer surface of the mixer duct shell may have an acoustic lining including a honeycomb core structure.

First claim

What is claimed is:

1. A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle, the turbofan engine assembly providing a fan exhaust and being mounted on an airborne mobile platform, the method comprising:
providing a mixer duct shell supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell;
routing a first portion of the fan exhaust through the mixer duct shell between an inner surface of the mixer duct shell and an outer surface of a core engine shroud, wherein the core engine shroud is covering a core engine, the first portion of the fan exhaust being directed towards a nozzle of the mixer duct shell;
routing a portion of exhaust gases of the core engine from a lobed mixer to adjacent the inner surface of the mixer duct shell to mix the portion of the exhaust gases of the core engine with the first portion of the fan exhaust to form a mixed exhaust, the mixed exhaust exiting the nozzle of the mixer duct shell;
routing a second portion of the fan exhaust over an outer surface of the mixer duct shell;
routing an engine case ventilation flow adjacent the core engine and an inward surface of the core engine shroud and subsequently inside the lobed mixer; and
covering at least one of the inner surface of the mixer duct shell and the outer surface of the mixer duct shell with an acoustic lining including a honeycomb core structure.

2. The method of claim 1 , further comprising incorporating an additional lining material, wherein the acoustic lining covers one of the inner surface of the mixer duct shell and the outer surface of the mixer duct shell, and the additional lining material covers the other of the inner surface of the mixer duct shell and the outer surface of the mixer duct shell.

3. The method of claim 2 , wherein at least one of the acoustic lining and the additional lining material comprises a layer of at least one of perforated titanium, perforated titanium alloy and perforated ceramic matrix composite.

4. The method of claim 2 , wherein the acoustic lining comprises a perforated facesheet and the additional lining material comprises a bulk absorber facesheet, and wherein each of the perforated facesheet and the bulk absorber facesheet is formed from one of:
a metallic material;
a ceramic material; and
a composite material having a foam-like or porous construction.

5. The method of claim 2 , wherein both the acoustic lining and the additional lining material each comprise a perforated sheet of at least one of titanium, titanium alloy and ceramic matrix composite material.

6. The method of claim 2 , wherein the acoustic lining comprises bulk absorber facesheets secured to the honeycomb core structure to sandwich the honeycomb core structure therebetween.

7. The method of claim 1 , wherein the honeycomb core structure includes a plurality of holes extending completely therethrough.

8. A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle, the turbofan engine assembly providing a fan exhaust and being mounted on an airborne mobile platform, the method comprising:
providing a mixer duct shell supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell;
routing a first portion of the fan exhaust through the mixer duct shell between an inner surface of the mixer duct shell and an outer surface of a core engine shroud, wherein the core engine shroud is covering a core engine, the first portion of the fan exhaust being directed towards a nozzle of the mixer duct shell;
routing a portion of exhaust gases of the core engine from a lobed mixer to adjacent the inner surface of the mixer duct shell to mix the portion of the exhaust gases of the core engine with the first portion of the fan exhaust to form a mixed exhaust, the mixed exhaust exiting the nozzle of the mixer duct shell;
routing a second portion of the fan exhaust over an outer surface of the mixer duct shell;
routing an engine case ventilation flow adjacent the core engine and an inward surface of the core engine shroud and subsequently inside the lobed mixer; and
covering at least one of the inner surface of the mixer duct shell and the outer surface of the mixer duct shell with an acoustic lining, the acoustic lining including a plurality of distinct layers of material.

9. The method of claim 8 , wherein the plurality of distinct layers of material includes a honeycomb core structure sandwiched between two layers of material.

10. The method of claim 9 , wherein each of the two layers of material is a bulk absorber facesheet.

11. The method of claim 9 , wherein the honeycomb core structure includes a plurality of holes extending completely therethrough.

12. The method of claim 9 , wherein the covering of the at least one of the inner surface of the mixer duct shell and the outer surface of the mixer duct shell with the acoustic lining comprises covering the inner surface of the mixer duct shell with the acoustic lining, and further comprising covering the outer surface of the mixer duct shell with a second acoustic lining.

13. The method of claim 8 , wherein the acoustic lining comprises a layer of at least one of perforated titanium, perforated titanium alloy and perforated ceramic matrix composite.

14. The method of claim 8 , wherein the covering of the at least one of the inner surface of the mixer duct shell and the outer surface of the mixer duct shell with the acoustic lining comprises covering the inner surface of the mixer duct shell with the acoustic lining, and further comprising covering the outer surface of the mixer duct shell with an additional acoustic lining, each of the acoustic lining and the additional acoustic lining having a honeycomb core structure.

15. The method of claim 14 , wherein the acoustic lining comprises a perforated facesheet and the additional acoustic lining comprises a bulk absorber facesheet, and wherein each of the perforated facesheet and the bulk absorber facesheet is formed from a metallic material.

16. The method of claim 14 , wherein the acoustic lining comprises a perforated facesheet and the additional acoustic lining comprises a bulk absorber facesheet, and wherein each of the perforated facesheet and the bulk absorber facesheet is formed from a ceramic material.

17. The method of claim 14 , wherein the acoustic lining comprises a perforated facesheet and the additional acoustic lining comprises a bulk absorber facesheet, and wherein each of the perforated facesheet and the bulk absorber facesheet is formed from a composite material having a foam-like or porous construction.

18. A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle, the turbofan engine assembly providing a fan exhaust and being mounted on an airborne mobile platform, the method comprising:
providing a mixer duct shell supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell;
routing a first portion of the fan exhaust through the mixer duct shell between an inner surface of the mixer duct shell and an outer surface of a core engine shroud, wherein the core engine shroud is covering a core engine, the first portion of the fan exhaust being directed towards a nozzle of the mixer duct shell;
routing a portion of exhaust gases of the core engine from a lobed mixer to adjacent the inner surface of the mixer duct shell to mix t

Assignees

• Boeing Co

Inventors

• Moore Matthew D
• Marques Edward C

Classifications

• F02K3/02 Primary

  in which part of the working fluid by-passes the turbine and combustion chamber · CPC title

• F02K1/766

  with blocking systems or locking devices; Arrangement of locking devices for thrust reversers · CPC title

• F02K1/386 Primary

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F02K1/827

  Sound absorbing structures or liners · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic