Thermally conforming acoustic liner cartridge for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10669936-B2
Application number	US-201414774035-A
Country	US
Kind code	B2
Filing date	Mar 12, 2014
Priority date	Mar 13, 2013
Publication date	Jun 2, 2020
Grant date	Jun 2, 2020

Abstract

A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.

First claim

What is claimed is:

1. A fan case of a gas turbine engine comprising:
a cartridge comprising an inlet acoustic liner section integrated with an axially adjacent thermally conforming liner section;
an impact liner axially aft of said cartridge; and
a seal positioned axially between said cartridge and said impact liner to damp movement of said cartridge,
wherein said cartridge is configured to be at least partially captured within an inboard hook of an inlet such that said cartridge is radially constrained at a forward end of said cartridge,
wherein said inlet acoustic liner section and said thermally conforming liner section are supported by an outboard ring,
wherein said inlet acoustic liner section includes a first portion of a honeycomb layer radially inboard of said outboard ring and an inboard perforated layer radially inboard of said honeycomb layer,
wherein said thermally conforming liner section includes a second portion of said honeycomb layer radially inboard of said outboard ring, a septum radially inboard of said second portion of said honeycomb layer and a rub strip radially inboard of said septum,
wherein said inboard hook is forward of an aft inlet bulkhead, and
wherein said first portion of said honeycomb layer has a forward end and an aft end and wherein said first portion of said honeycomb layer has a radial thickness that is greater at said forward end than at said aft end.

2. The fan case as recited in claim 1 , wherein said outboard ring is manufactured of an aluminum alloy.

3. The fan case as recited in claim 1 , wherein said honeycomb layer provides a 3D aero profile.

4. A fan nacelle for a gas turbine engine comprising:
a containment case;
an inlet attached to said containment case at an interface; and
a cartridge which spans said interface,
an impact liner; and
a seal positioned axially between said cartridge and said impact liner to damp movement of said cartridge in an axial direction;
wherein said inlet defines an inboard hook to at least partially capture said cartridge such that said cartridge is radially constrained at a forward end of said cartridge,
wherein an aft end of said cartridge is attached to said containment case with a radially compliant attachment,
wherein said forward end of said cartridge is positioned relative to said inboard hook via radial dampers, and
wherein an inboard surface of said cartridge has a first radial position at said forward end and a second radial position at said aft end and wherein said first radial position is radially inboard of said second radial position.

5. The fan nacelle as recited in claim 4 , wherein said interface includes a forward flange of said containment case and an inlet flange of said inlet.

6. The fan nacelle as recited in claim 4 , wherein said interface is a bolted interface.

7. The fan nacelle as recited in claim 4 , wherein said inboard hook is forward of an aft inlet bulkhead.

8. The fan nacelle as recited in claim 7 , wherein a fan cowl is mounted to said aft inlet bulkhead.

9. The fan nacelle as recited in claim 4 , wherein said cartridge provides a 3D aero profile.

10. The fan nacelle as recited in claim 4 , wherein said cartridge provides a perforated face sheet and a fan rub strip.

11. The fan nacelle as recited in claim 4 , wherein said cartridge provides an inlet acoustic liner section integrated with a thermally conforming liner section.

12. The fan nacelle as recited in claim 4 , wherein said radially compliant attachment axially and circumferentially retains said aft end of said cartridge.

13. The fan nacelle as recited in claim 4 , wherein said radial dampers include a silicone rubber full annulus or segmented seals.

14. A fan nacelle for a gas turbine engine comprising:
a containment case;
an inlet attached to said containment case at an interface; and
a cartridge which spans said interface,
an impact liner; and
a seal positioned axially between said cartridge and said impact liner to damp movement of said cartridge;
wherein said inlet defines an inboard hook to at least partially capture said cartridge such that said cartridge is radially constrained at a forward end of said cartridge,
wherein an aft end of said cartridge is attached to said containment case with a radially compliant attachment,
wherein said cartridge provides a 3D aero profile, and
wherein an inboard surface of said cartridge has a first radial position at said forward end and a second radial position at said aft end and wherein said first radial position is radially inboard of said second radial position.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Robertson Jr Thomas J
• Costa Mark W
• Welch David A

Classifications

• F02C7/045 Primary

  having provisions for noise suppression · CPC title

• F05D2300/5021

  Expansivity · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• B64D2033/0286

  for turbofan engines · CPC title