Firewall, pylon of aircraft, and aircraft

Patent metadata

Field	Value
Publication number	US-9334805-B2
Application number	US-201414162077-A
Country	US
Kind code	B2
Filing date	Jan 23, 2014
Priority date	Jan 25, 2013
Publication date	May 10, 2016
Grant date	May 10, 2016

Abstract

In order to provide a firewall that is capable of preventing flame passage through a through-hole without any sealant in a connecting part of a component in which a fastener through-hole is formed, a firewall 50 is provided which can prevent a flame from leaking out of the connecting part which connects a first member 51 to a second member 55 , particularly through the fastener through-hole TH defined therein. In the firewall 50 , the connecting part is a part of a fire-protection chamber 52 . As sealing pieces 51 d and 51 e which also constitute a part of the fire-protection chamber 52 are in contact with each other, the flame is unable to enter into a closed space CA. Thus, the flame would not reach the connecting part, thereby preventing the flame from leaking out of the firewall 50 to the outside of a nacelle 23.

First claim

What is claimed is:

1. A firewall disposed around an engine of an aircraft comprising:
a first member fixed to a component provided around the engine;
a second member detachably connected to the first member by a fastener; and
a fire-protection chamber that at least partially encloses a connecting part between the first and second members, the fire-protection chamber defining a space within, wherein the space is between the engine and the connecting part.

2. The firewall of an aircraft according to claim 1 , wherein the fire-protection chamber forms a closed space therein.

3. The firewall of an aircraft according to claim 1 or claim 2 , wherein:
the first member comprises a pair of sidewalls provided at opposite sides in a width direction thereof, a first joining piece fastened to a pylon strut for supporting the engine, a second joining piece fastened to the second member, and a connecting piece connecting the first joining piece to the second joining piece;
a first sealing piece and a second sealing piece are provided at an inside corner between the second joining piece and the connecting piece;
the pair of sidewalls are attached to the first joining piece, the second joining piece, the connecting piece and the first sealing piece, respectively; and
the second sealing piece is in contact with the first sealing piece.

4. The firewall of an aircraft according to claim 3 , wherein the pair of sidewalls are not attached to the second sealing piece, and the second sealing piece elastically deforms.

5. The firewall of an aircraft according to claim 1 , wherein:
the fire-protection chamber is partly defined by a first sealing piece and a second sealing piece;
the second sealing piece is in contact with the first sealing piece; and
the second sealing piece elastically deforms.

6. The firewall of an aircraft according to claim 5 , wherein the second sealing piece serves as a spring member.

7. The firewall of an aircraft according to claim 1 , wherein the fire-protection chamber is provided with a passageway through which the fire-protection chamber communicates with the outside thereof, and wherein the passageway extends in a different direction from that toward the connecting part.

8. An aircraft pylon comprising:
a pylon strut for supporting an engine of an aircraft; and
a firewall disposed around an engine of an aircraft comprising:
a first member fixed to a component provided around the engine,
a second member detachably connected to the first member by a fastener, and
a fire-protection chamber provided associated with a connecting part between the first and second members;

wherein:
the firewall is fixed to the pylon strut via the first member; and
the second member contacts a fire-resistant seal attached to a nacelle when the nacelle is closed, the nacelle surrounding the engine and capable of being opened and closed.

9. An aircraft comprising:
a pylon including: a pylon strut for supporting an engine of the aircraft; and the firewall according to claim 1 ;
a nacelle for surrounding the engine, wherein the nacelle is capable of being opened and closed; and
a fire-resistant seal attached to the nacelle;
wherein
the firewall is fixed to the pylon strut via the first member; and
the second member contacts the fire-resistant seal when the nacelle is closed.

10. The aircraft pylon according to claim 8 , wherein the fire-protection chamber forms a closed space therein.

11. The aircraft pylon according to claim 8 or claim 10 , wherein:
the first member comprises a pair of sidewalls provided at opposite sides in a width direction thereof, a first joining piece fastened to a pylon strut for supporting the engine, a second joining piece fastened to the second member, and a connecting piece connecting the first joining piece to the second joining piece;
a first sealing piece and a second sealing piece are provided at an inside corner between the second joining piece and the connecting piece;
the pair of sidewalls are attached to the first joining piece, the second joining piece, the connecting piece and the first sealing piece, respectively; and
the second sealing piece is in contact with the first sealing piece.

12. The aircraft pylon according to claim 11 , wherein the pair of sidewalls are not attached to the second sealing piece, and the second sealing piece elastically deforms.

13. The aircraft pylon according to claim 8 , wherein:
the fire-protection chamber is partly defined by a first sealing piece and a second sealing piece;
the second sealing piece is in contact with the first sealing piece; and
the second sealing piece elastically deforms.

14. The aircraft pylon according to claim 13 , wherein the second sealing piece serves as a spring member.

15. The aircraft pylon according to claim 8 , wherein the fire-protection chamber is provided with a passageway through which the fire-protection chamber communicates with the outside thereof, and wherein the passageway extends in a different direction from that toward the connecting part.

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Takeuchi Akira

Classifications

• F02C7/25 Primary

  Fire protection or prevention (in general A62) · CPC title

• B64D2045/009

  Fire detection or protection; Erosion protection, e.g. from airborne particles · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• B64D27/00

  Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title