Hybrid inner fixed structure with metallic and composite construction

Patent metadata

Field	Value
Publication number	US-9885253-B2
Application number	US-201414508637-A
Country	US
Kind code	B2
Filing date	Oct 7, 2014
Priority date	Oct 7, 2013
Publication date	Feb 6, 2018
Grant date	Feb 6, 2018

Abstract

Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.

First claim

We claim:

1. A system for an aircraft comprising:
A titanium bottle section that includes a plurality of sections configured to house and form a sealed fire chamber around an engine, each of the sections comprising titanium; and
at least one bifurcation panel coupled to the bottle section,
wherein the at least one bifurcation panel includes a material that is different from titanium; and
wherein each of the plurality of bottle sections is disposed adjacent and movable relative to a respective one of the at least one of the bifurcation panels.

2. The system of claim 1 , further comprising:
at least one v-blade configured to couple the bottle section and the engine at a forward end of the engine.

3. The system of claim 2 , further comprising one of:
at least one standoff configured to couple the bottle section and the engine at an aft end of the engine; and
at least a second v-blade configured to couple the bottle section and the engine at the aft end of the engine.

4. The system of claim 1 , further comprising:
at least one beam coupled to the at least one bifurcation panel.

5. The system of claim 4 , wherein the at least one beam is integral with the at least one bifurcation panel.

6. The system of claim 4 , wherein the at least one beam is a hinge beam.

7. The system of claim 1 , further comprising:
a duct wall configured as a single piece that is translatable in at least one of a forward direction or an aft direction.

8. The system of claim 1 , further comprising:
a pylon coupled to the at least one bifurcation panel and integral with the at least one bifurcation panel.

9. The system of claim 1 , wherein the titanium bottle section is two sections that form a 360° barrel shape when coupled to one another.

10. The system of claim 1 , wherein the titanium bottle section is at least three sections that form a 360° barrel shape when coupled to one another.

11. The system of claim 10 , wherein a first of the at least three sections is configured to couple to a pylon.

12. The system of claim 11 , wherein the first of the at least three sections is configured to enable at least one of a duct, a wire, a harness, a tube, and an engine support structure to pass through the first of the at least three sections.

13. The system of claim 10 , wherein the at least one bifurcation panel is located within a span of a first of the at least three sections.

14. The system of claim 1 , wherein the at least one bifurcation panel is attached to the bottle section.

15. The system of claim 1 , wherein the at least one bifurcation panel includes a composite material, and wherein the bottle section is configured to transfer loads generated by the engine axially along the bottle section.

16. The system of claim 1 , wherein each section comprises a titanium cellular core between a pair of titanium skins, and the bifurcation panel comprises a cellular core between a pair of skins.

17. A system for a propulsion system of an aircraft, the propulsion system comprising an engine core and a nozzle, the system comprising:
an inner fixed structure including a titanium bottle section, a first bifurcation panel and a second bifurcation panel;
the titanium bottle section including first and second titanium sections, and the titanium bottle section configured to extend circumferentially about and house the engine core upstream of the nozzle, the first titanium section disposed adjacent and movable relative to the first bifurcation panel, and the second titanium section disposed adjacent and movable relative to the second bifurcation panel;
wherein the first bifurcation panel comprises a material that is different from titanium.

18. The system of claim 17 , wherein the material is a composite material.

19. The system of claim 17 , wherein the material comprises fiber reinforcement within a resin matrix.

20. The system of claim 17 , wherein the material comprises carbon fiber.

Assignees

• Rohr Inc

Inventors

• Soria Christian
• Ramlaoui Jihad
• Binks Alan J

Classifications

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F01D25/005

  Selecting particular materials · CPC title