Aircraft with a fuselage that defines at least an interior region and a drive system accommodating region

Patent metadata

Field	Value
Publication number	US-10427775-B2
Application number	US-201615043758-A
Country	US
Kind code	B2
Filing date	Feb 15, 2016
Priority date	Feb 16, 2015
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.

First claim

What is claimed is:

1. A rotary-wing aircraft comprising:
a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region disposed inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement comprising a plurality of interconnected fire protection walls,
at least one engine disposed within the at least one fire protection zone within the at least one associated firewall arrangement such that the at least one associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage,
at least one heat generating auxiliary device distinct from the at least one engine and generating a hot air flow;
at least one auxiliary exhaust nozzle;
the at least one associated firewall arrangement comprising at least one air duct forming at least part of the at least one associated firewall arrangement and arranged between, and in fluid communication with, the at least one heat generating auxiliary device and the at least one auxiliary exhaust nozzle so that the hot air flow that is generated by the at least one heat generating auxiliary device in operation of the aircraft is ducted through the at least one air duct separately from air carrying heat generated by the operation of the at least one engine, wherein the at least one associated firewall arrangement includes the at least one air duct such that the at least one air duct is integral with the at least one associated firewall arrangement, the plurality of interconnected fire protection walls comprising a front fire protection wall, a rear fire protection wall, and a lower fire protection wall.

2. The rotary-wing aircraft according to claim 1 , wherein the heat generating auxiliary device comprises at least one of: a gearbox, at least one heat exchanger, and a unit that generates hot air flow during operation of the aircraft.

3. The rotary-wing aircraft according to claim 1 , wherein the at least one engine is an air breathing propulsion engine and the heat generated in operation of the air breathing propulsion engine is a primary hot air flow, the primary hot air flow ducted separately from the hot air flow ducted through the air duct.

4. The rotary-wing aircraft according to claim 1 , wherein the at least one associated firewall arrangement includes a middle fire protection wall dividing the at least one associated firewall arrangement into a first fire protection zone accommodating a first engine and a second fire protection zone accommodating a second engine with a space extending between the first and second fire protection zones, the at least one air duct disposed and extending between the first and second fire protection zones in the space extending between the first and second fire protection zones.

5. The rotary-wing aircraft according to claim 4 , wherein the at least one associated firewall arrangement defines a component receiving compartment between the first and second fire protection zones.

6. The rotary-wing aircraft according to claim 5 , wherein the drive system accommodating region defines an upper deck region of the fuselage, the upper deck region disposed inside the fuselage adjacent to an upper fuselage side.

7. The rotary-wing aircraft according to claim 5 , wherein the aircraft has at least one counter-torque device, the counter-torque device drivingly coupled to an associated drive shaft, the associated drive shaft is at least partly received in the component receiving compartment.

8. The rotary-wing aircraft according to claim 7 , wherein the fuselage defines a tail boom, the fuselage also defining at least one primary exhaust nozzle in fluid communication with the at least one engine for expelling a primary hot air flow generated by the at least one engine in operation, the at least one air duct provided with at least one auxiliary exhaust nozzle in fluid communication with the at least one heat generating auxiliary device for expelling the hot air flow in operation, the at least one auxiliary exhaust nozzle at least partly arranged in parallel between a longitudinal axis of the aircraft, the at least one primary exhaust nozzle and the tail boom.

9. The rotary-wing aircraft according to claim 7 , wherein the fuselage defines a tail boom, wherein the hot air flow is expelled through the tail boom in operation of the rotary-wing aircraft.

10. The rotary-wing aircraft according to claim 1 , wherein the at least one air duct is provided with at least one exhaust nozzle through which the hot air flow is expelled in operation, the at least one exhaust nozzle adapted for directing an expelled hot air flow at least partly alongside the fuselage.

11. The rotary-wing aircraft according to claim 1 , wherein at least one primary exhaust nozzle is provided for expelling a primary hot air flow generated by the at least one engine in operation, wherein the at least one air duct is provided with at least one auxiliary exhaust nozzle for expelling the hot air flow in operation, the at least one auxiliary exhaust nozzle is at least partly integrated into the at least one primary exhaust nozzle.

12. The rotary-wing aircraft according to claim 1 , wherein the at least one air duct accommodates at least one hot-air hose for ducting the hot air flow.

13. The rotary-wing aircraft according to claim 1 , wherein the at least one air duct comprises thermally insulated material.

14. The rotary-wing aircraft according to claim 1 , wherein the at least one associated firewall arrangement defines a first fire protection zone accommodating a first engine and a second fire protection zone accommodating a second engine, the at least one air duct comprising a first air duct arranged in the first fire protection zone and a second air duct arranged in the second fire protection zone.

15. The rotary-wing aircraft according to claim 1 , wherein the at least one air duct is defined by associated air duct walls that separate, in operation, the hot air flow from the at least one fire protection zone.

16. The rotary-wing aircraft according to claim 15 , wherein the associated air duct walls comprise at least one air duct wall that separates, in operation, the hot air flow from the fuselage.

17. A rotary-wing aircraft comprising:
a fuselage comprising an interior region and a drive system accommodating region, the drive system accommodating region comprising a fire protection zone having a firewall arrangement comprising a plurality of interconnected fire protection walls made of thermally insulated material,
an engine disposed within the fire protection zone within the firewall arrangement, the firewall arrangement defining a fire-resistant separation between the engine and the interior region of the fuselage, a heat generating auxiliary device distinct from the engine, the heat generating auxiliary device capable of generating a hot air flow;
an auxiliary exhaust nozzle; and
the firewall arrangement comprising an air duct made of thermally insulated material disposed between, and in fluid communication with, the heat generating auxiliary device and the auxiliary exhaust nozzle so that hot air generated by the heat generating auxiliary device in operation of the aircraft is ducted through the air duct separately from air carrying heat generated by the operation of the engine, wherein the firewall arrangement includes the air duct such that the air duct is integral with the firewall arrangement, the plurality of interconnected fire protection walls comprising a fr

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Mores Sebastian
• Loeser Frank
• Frese Johannes
• Braeutigam Ralf
• Wehle Christian

Classifications

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64C1/16

  specially adapted for mounting power plant · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64C1/10 Primary

  Bulkheads · CPC title

• B64C1/40 Primary

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title