Rotary wing aircraft with a firewall arrangement having at least one funnel-shaped lower firewall

Patent metadata

Field	Value
Publication number	US-12258121-B2
Application number	US-202418631332-A
Country	US
Kind code	B2
Filing date	Apr 10, 2024
Priority date	May 5, 2023
Publication date	Mar 25, 2025
Grant date	Mar 25, 2025

Abstract

A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, the upper primary skin being mounted on top of a predetermined number of supporting beams; wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement such that the firewall arrangement defines a fire proof separation at least between the at least one aircraft engine and the aircraft interior region; and wherein the firewall arrangement comprises at least a funnel-shaped lower firewall arranged between the at least one aircraft engine and the upper primary skin of the fuselage.

First claim

What is claimed is:

1. A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, the upper primary skin being mounted on top of a predetermined number of supporting beams;
wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement such that the firewall arrangement defines a fire proof separation at least between the at least one aircraft engine and the aircraft interior region;
wherein the firewall arrangement comprises at least one funnel-shaped lower firewall that is arranged between the at least one aircraft engine and the upper primary skin of the fuselage, the at least one funnel-shaped lower firewall being spaced apart from the upper primary skin by a predetermined separation distance and converging from an outer perimeter to at least one inner collecting point of the at least one funnel-shaped lower firewall;
wherein the at least one funnel-shaped lower firewall comprises at least an outer support surface with a through-hole through which an outer main mount bracket extends at least partly, the outer main mount bracket comprising an outer main mount bracket web that is rigidly attached to a beam web of at least one beam of the predetermined number of supporting beams;
wherein the outer main mount bracket further comprises a plateau abutting against the outer support surface, the plateau being provided with an outer main mount fixation extending through the through-hole of the outer support surface, the outer main mount fixation being connected to an outer main mount that is attached to the at least one aircraft engine.

2. The rotary wing aircraft of claim 1 , further comprising a cover plate that is rigidly attached to the plateau for clamping the at least one funnel-shaped lower firewall between the cover plate and the plateau.

3. The rotary wing aircraft of claim 2 , further comprising a sealing element clamped between the cover plate and the at least one funnel-shaped lower firewall and/or between the plateau and the at least one funnel-shaped lower firewall for sealing the at least one funnel-shaped lower firewall.

4. The rotary wing aircraft of claim 1 , wherein the outer main mount bracket web comprises an upper web section extending from the plateau to the beam web of the at least one beam over the predetermined separation distance, and a lower web section that is rigidly attached to the beam web of the at least one beam.

5. The rotary wing aircraft of claim 4 , further comprising at least one stiffening rib, wherein the at least one stiffening rib is arranged between the at least one funnel-shaped lower firewall and the upper primary skin, and wherein the upper web section comprises a support rib that is rigidly attached to the at least one stiffening rib.

6. The rotary wing aircraft of claim 1 , wherein the outer main mount fixation comprises at least one mounting lug, and wherein the outer main mount is rotatably mounted to the at least one mounting lug via at least one spherical bearing.

7. The rotary wing aircraft of claim 6 , wherein the outer main mount is embodied as a triangular mounting element that is connected to the outer main mount fixation via two spherical bearings.

8. The rotary wing aircraft of claim 1 , wherein the outer main mount is rotatably mounted to an outer main mounting bracket that is rigidly attached to the at least one aircraft engine.

9. The rotary wing aircraft of claim 8 , wherein the outer main mount is rotatably mounted to the outer main mounting bracket via a spherical bearing.

10. The rotary wing aircraft of claim 1 , wherein the at least one funnel-shaped lower firewall further comprises an inner support surface with a through-hole through which an inner main mount bracket extends at least partly, wherein the inner main mount bracket is connected to an inner main mount that is attached to the at least one aircraft engine.

11. The rotary wing aircraft of claim 10 , wherein the inner main mount is rotatably mounted to an inner main mounting bracket that is rigidly attached to the at least one aircraft engine.

12. The rotary wing aircraft of claim 11 , wherein the inner main mounting bracket is further rotatably mounted to an inner lateral mount that is connected to an inner lateral mount bracket.

13. The rotary wing aircraft of claim 10 , wherein the inner main mount bracket is rigidly attached to a beam web of at least one other beam of the predetermined number of supporting beams.

14. The rotary wing aircraft of claim 1 , wherein the at least one funnel-shaped lower firewall further comprises a rear support surface with a rear through-hole through which a rear mount bracket extends at least partly, wherein the rear mount bracket is connected to a rear mount that is attached to the at least one aircraft engine.

15. The rotary wing aircraft of claim 1 , wherein the upper primary skin of the fuselage comprises at least one cut-out, and wherein a center portion of the at least one funnel-shaped lower firewall is arranged inside of the at least one cut-out.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Fink Axel
• Kempf Manuel
• Walch Philipp
• Specht Luca

Classifications

• B64D2045/009

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

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64C27/06

  with single rotor · CPC title

• B64C1/12

  Construction or attachment of skin panels · CPC title