Composite drain pan

Patent metadata

Field	Value
Publication number	US-11248743-B2
Application number	US-201816155208-A
Country	US
Kind code	B2
Filing date	Oct 9, 2018
Priority date	Oct 9, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

In some examples, a drain pan comprises a composite material forming a reservoir and a drain. The composite material comprises a polymeric resin and a reinforcing fiber. The reservoir is to catch a liquid from an engine and to support a step load. The drain is to drain the liquid from the reservoir. In some examples, a method comprises attaching a drain pan to an aircraft proximate an engine. The drain pan comprises a composite material forming a reservoir and a drain. The method further comprises catching a liquid from the engine in the reservoir of the drain pan and draining the liquid from the reservoir through the drain. In addition, the method comprises supporting a step load on the reservoir of the drain pan.

First claim

What is claimed is:

1. An aircraft comprising:
an engine; and
a drain pan comprising:
a composite material comprising a polymeric resin and a reinforcing fiber, wherein the composite material forms:
a reservoir to catch a liquid from the engine,
a drain to drain the liquid from the reservoir,
a flange for supporting a step load on an external portion of the aircraft,

wherein the drain pan is operable to withstand a fire burning at about 2000 degrees Fahrenheit for at least 15 minutes, and
wherein the reservoir formed by the composite material comprises:
a sloped portion sloping toward the drain at a constant slope along a first direction; and
a curved portion sloping toward the drain at a varying slope along a second direction, wherein the first direction and the second direction are perpendicular to one another.

2. The aircraft of claim 1 , further comprising:
a fire-resistant material coating the composite material.

3. The aircraft of claim 1 , wherein the drain pan is a first drain pan and further comprising a second drain pan, and
wherein the first drain pan and the second drain pan abut one another and form a crest from which the liquid can flow into the first drain pan and the second drain pan.

4. A method comprising: attaching a drain pan to an aircraft proximate an engine, the drain pan comprising a composite material forming a reservoir and a drain; catching a liquid from the engine in the reservoir of the drain pan; draining the liquid from the reservoir through the drain; and supporting a step load on the reservoir of the drain pan by a flange of the reservoir, wherein the drain pan is operable to withstand a fire burning at about 2000 degrees Fahrenheit for at least 15 minutes, and wherein the reservoir comprises: a sloped portion sloping toward the drain at a constant slope along a first direction; and a curved portion sloping toward the drain at a varying slope along a second direction, wherein the first direction and the second direction are perpendicular to one another.

5. The method of claim 4 , further comprising:
coating at least a portion of the drain pan with a fire-resistant material.

6. The method of claim 4 , further comprising:
receiving, for a duration of at least 15 minutes, a fire burning at about 2000 degrees Fahrenheit on the drain pan, while simultaneously receiving the fire:
continuing to catch the liquid from the engine in the reservoir of the drain pan; and
continuing to drain the liquid from the reservoir through the drain.

7. The method of claim 4 , wherein the drain pan is a first drain pan, the method further comprising:
attaching a second drain pan to the aircraft, wherein the first drain pan and the second drain pan abut one another and form a crest; and
guiding flow of the liquid from the crest into the first drain pan and the second drain pan.

8. The method of claim 4 , further comprising:
transferring the liquid from the drain to an outlet through a tube coupled to the drain.

9. The aircraft of claim 2 , wherein the fire-resistant material increases a fire-resistance of the drain pan by 25% or more.

10. The aircraft of claim 1 , wherein the liquid comprises one selected from the group consisting of: a petroleum-based fuel, a coolant, a hydraulic fluid, and a lubricant.

11. The aircraft of claim 1 , wherein the polymeric resin comprises a thermosetting polymer.

12. The aircraft of claim 1 , wherein the polymeric resin comprises bismaleimide (BMI) resin and/or epoxy resin.

13. The aircraft of claim 1 , further comprising:
a tube coupled to the drain, the tube transferring the liquid from the drain to an outlet.

14. An aircraft comprising:
an engine; and
a drain pan comprising:
a composite material comprising a polymeric resin and a reinforcing fiber, wherein the composite material forms:
a reservoir to catch a liquid from the engine,
a drain to drain the liquid from the reservoir, and
a flange for supporting a step load on a portion of the aircraft,

wherein the drain pan is operable to withstand a fire burning at about 2000 degrees Fahrenheit for at least 15 minutes,
wherein the drain pan is a first drain pan and further comprising a second drain pan, and
wherein the first drain pan and the second drain pan abut one another and form a crest from which the liquid can flow into the first drain pan and the second drain pan.

15. The aircraft of claim 14 , further comprising:
a fire-resistant material coating the composite material.

16. The aircraft of claim 15 , wherein the fire-resistant material increases a fire-resistance of the drain pan by 25% or more.

17. The aircraft of claim 14 , wherein the reservoir formed by the composite material comprises:
a shape comprising:
a sloped portion sloping toward the drain at a constant slope along a first direction; and
a curved portion sloping toward the drain at a varying slope along a second direction, wherein the first direction and the second direction are perpendicular to one another.

18. The aircraft of claim 14 , wherein the liquid comprises one selected from the group consisting of: a petroleum-based fuel, a coolant, a hydraulic fluid, and a lubricant.

19. The aircraft of claim 14 , wherein the polymeric resin comprises at least one of a thermosetting polymer, bismaleimide (BMI) resin and epoxy resin.

20. The aircraft of claim 14 , further comprising:
a tube coupled to the drain, the tube transferring the liquid from the drain to an outlet.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Emrich Joshua A
• Paquin Patrick
• Terry Eric C
• Scannell Brent
• Mast Thomas

Classifications

• F16N31/006 Primary

  Drip trays · CPC title

• B64C27/04 Primary

  Helicopters · CPC title

• B64D33/00

  Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for · CPC title

• F16N31/002

  Drain pans · CPC title

• F01M11/0004

  Oilsumps · CPC title