Two-piece firewall and inlet plenum

Patent metadata

Field	Value
Publication number	US-10689126-B2
Application number	US-201715627412-A
Country	US
Kind code	B2
Filing date	Jun 19, 2017
Priority date	Jun 19, 2017
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

In one embodiment, there is described an inlet plenum assembly for a rotary aircraft, including: an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly; the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine; wherein the forward firewall assembly includes a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.

First claim

What is claimed is:

1. An inlet plenum assembly for a rotary aircraft, comprising:
an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly;
the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and
the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine;
wherein the forward firewall assembly comprises a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.

2. The inlet plenum assembly of claim 1 , wherein the forward firewall lower is configured to be mechanically fixed to the rotary aircraft.

3. The inlet plenum assembly of claim 1 , wherein the inlet plenum wall comprises an inlet plenum wall upper and an inlet plenum wall lower, the inlet plenum wall upper configured to removably seat to the inlet plenum wall lower.

4. The inlet plenum assembly of claim 3 , wherein the inlet plenum wall lower is configured to be mechanically fixed to the rotary aircraft.

5. The inlet plenum assembly of claim 3 , further comprising mounting hardware to removably secure the inlet plenum wall upper to the inlet plenum wall lower.

6. The inlet plenum assembly of claim 1 , wherein the mechanical interface for receiving the RGB comprises an RGB seal to provide a seal between the inlet plenum wall and the RGB.

7. The inlet plenum assembly of claim 1 , further comprising mounting hardware to removably secure the forward firewall upper to the forward firewall lower.

8. The inlet plenum assembly of claim 1 , wherein the inlet plenum wall and forward firewall assembly form an abutting “L” shape, wherein a short leg of the “L” is oriented away from an engine air inlet plenum.

9. A rotary aircraft, comprising:
an engine;
a driveshaft rotatably coupled to the engine;
a reduction gearbox (RGB) mechanically coupled to the driveshaft and configured to provide reduction gearing to the driveshaft; and
an inlet plenum assembly, comprising:
an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly;
the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and
the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine;
wherein the forward firewall assembly comprises a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.

10. The rotary aircraft of claim 9 , wherein the forward firewall lower is configured to be mechanically fixed to the rotary aircraft.

11. The rotary aircraft of claim 9 , wherein the inlet plenum wall comprises an inlet plenum wall upper and an inlet plenum wall lower, the inlet plenum wall upper configured to removably seat to the inlet plenum wall lower.

12. The rotary aircraft of claim 11 , wherein the inlet plenum wall lower is configured to be mechanically fixed to the rotary aircraft.

13. The rotary aircraft of claim 11 , further comprising mounting hardware to removably secure the inlet plenum wall upper to the inlet plenum wall lower.

14. The rotary aircraft of claim 9 , wherein the mechanical interface for receiving the RGB comprises an RGB seal to provide a seal between the inlet plenum wall and the RGB.

15. The rotary aircraft of claim 9 , further comprising mounting hardware to removably secure the forward firewall upper to the forward firewall lower.

16. The inlet plenum assembly of claim 9 , wherein the inlet plenum wall and forward firewall assembly form an abutting “L” shape, wherein a short leg of the “L” is oriented away from an engine air inlet plenum.

17. A boundary wall for an inlet plenum assembly of a rotary aircraft, comprising:
a lower member configured to mount to a chassis of the rotary aircraft, and comprising a lower half of a mechanical interface for receiving an operational component of the rotary craft;
an upper member configured to removably seat to the lower member, and comprising an upper half of the mechanical interface; and
a mounting interface for receiving mounting hardware to secure the upper member to the lower member.

18. The boundary wall of claim 17 , wherein the boundary wall is a forward firewall.

19. The boundary wall of claim 18 , wherein the operational component is a reduction gearbox.

20. The boundary wall of claim 19 , wherein the mounting interface comprises a flange with through holes.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Scannell Brent
• Mast Thomas

Classifications

• B64D2045/009

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

• B64C27/12

  Rotor drives · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C1/10

  Bulkheads · CPC title