POWER DISTRIBUTION SYSTEM

• US 20110220759A1
• Filed: 09/23/2009
• Published: 09/15/2011
• Est. Priority Date: 09/26/2008
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Stolte, Ralf-Henning
• Granted Patent: US 8,672,263 B2
• Time in Patent Office: Days
• US Class Current: 244/60
• CPC Class Codes: B64D 2013/0618 with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 35/00 Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
• CPC Class Codes: F02C 7/275 Mechanical drives
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

The invention relates to a power distribution system for an aircraft that comprises at least one engine, comprising at least one torque transmission means that is movably held and is connected to at least one shaft of the engine and extends from the shaft of the engine to an interior region of the aircraft fuselage, and at an end pointing away from the engine comprises at least one interface for introducing a torque. At the interface of the torque transmission means it is possible both to operate mechanical and to start the engine. Consequently in the aircraft it is possible to essentially do without converting mechanical energy to electrical energy and the subsequent use of electrical energy for generating mechanical power. This is particularly favourable in the case of twin-engine commercial aircraft that are used on short hauls.

Claims

1. A power distribution system (2, 50) for an aircraft (62) equipped with at least one engine (8, 10), comprising

at least one torque transmission means (4, 6),

at least one first coupling (16, 18) for transmitting a torque between the torque transmission means (4, 6) and a distribution shaft (30, 42), and

at least one rotatable device of an environmental control system, which device is coupled to the distribution shaft (30, 42),

wherein the torque transmission means (4, 6) is movably held and is connected to at least one shaft of the engine (8, 10), wherein the torque transmission means (4, 6) extends from the shaft of the engine (8, 10) to an interior region of an aircraft fuselage, and wherein at an end pointing away from the engine (8, 10) the torque transmission means (4, 6) comprises at least one interface (12, 14) for introducing a torque and

wherein the rotatable device of the environmental control system is a compressor, an air cycle machine, an evaporative cooling machine or a fan.

2. The power distribution system (2, 50) of claim 1, further comprising at least one motor-generator unit (20, 22) coupled to the distribution shaft (30, 42).

3. The power distribution system (2, 50) of claim 1 or 2, wherein at least one gear arrangement (32, 40) is arranged between the distribution shaft (30, 42) and the rotatable device of the environmental control system.

4. The power distribution system (2, 50) of any one of the preceding claims, comprising two torque transmission means (4, 6), wherein the aircraft (62) comprises two or more engines (8, 10), a left-hand torque transmission means (4) is connected to at least one left-hand engine (8), and to at least one left-hand rotatable device (26, 28) of the environmental control system;

and/or with at least one left-hand motor-generator unit (20) forms a left-hand power distribution train (24), and wherein a right-hand torque transmission means (6) is connected to at least one right-hand engine (10) and to at least one right-hand rotatable device (36, 38) of the environmental control system, and/or with at least one right-hand motor-generator unit (22) forms a right-hand power distribution train (34).

5. The power distribution system (2, 50) of claim 4, further comprising at least one second coupling (44) for transmitting torque between the left-hand drive train (24) and the right-hand drive train (34).

6. The power distribution system (2, 50) of any one of claims 2-5, wherein the at least one motor-generator unit (20, 22) is designed to start at least one of the engines (8, 10).

7. The power distribution system (2, 50) of any one of claims 2-6, wherein the at least one motor-generator unit (20, 22) is designed to provide electrical energy.

8. The power distribution system (2, 50) of any one of the preceding claims, further comprising at least one electrical energy source (48) for operating the at least one rotatable device of the environmental control system and electrical loads of the aircraft when the engines (8, 10) are at a standstill.

10. The use of a power distribution system (2, 50) of any one of claims 1-8 in a means of transport.

11. An aircraft (62) comprising at least one engine (8, 10) and at least one power distribution system (2, 50) of any one of claims 1-8.

9. A method for distributing power in an aircraft, comprising the step of transmitting (52) torque between at least one engine (8, 10) of the aircraft and a rotatable device in an interior region of the aircraft fuselage,

wherein the rotatable device of the environmental control system is a compressor, an air cycle machine, an evaporative cooling machine or a fan.