US 12,258,121 B2
Rotary wing aircraft with a firewall arrangement having at least one funnel-shaped lower firewall
Axel Fink, Donauwörth (DE); Manuel Kempf, Donauwörth (DE); Philipp Walch, Rain am Lech (DE); and Luca Specht, Petershausen (DE)
Assigned to AIRBUS HELICOPTERS DEUTSCHLAND GMBH, Donauwörth (DE)
Filed by AIRBUS HELICOPTERS DEUTSCHLAND GMBH, Donauwörth (DE)
Filed on Apr. 10, 2024, as Appl. No. 18/631,332.
Claims priority of application No. 23171892 (EP), filed on May 5, 2023.
Prior Publication US 2024/0367784 A1, Nov. 7, 2024
Int. Cl. B64C 27/00 (2006.01); B64C 1/12 (2006.01); B64C 27/06 (2006.01); B64D 27/02 (2006.01); B64D 45/00 (2006.01)
CPC B64C 27/006 (2013.01) [B64C 1/12 (2013.01); B64D 27/02 (2013.01); B64D 45/00 (2013.01); B64C 27/06 (2013.01); B64D 2045/009 (2013.01)] 15 Claims
OG exemplary drawing
 
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.