AUXILIARY POWER SUPPLY METHOD THROUGH AN AUXILIARY POWER UNIT AND CORRESPONDING ARCHITECTURE

• US 20150089921A1
• Filed: 03/18/2013
• Published: 04/02/2015
• Est. Priority Date: 05/10/2012
• Status: Abandoned Application

• Current Assignee: Safran Power Units
• Original Assignee: Microturbo SA
• Inventors: Rideau, Jean-Francois, Silet, Fabien
• Application Number:
  US13/845,862
• Publication Number:
  US 20150089921A1
• Time in Patent Office: Days
• US Class Current: 60/39.091
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F02C 9/46 Emergency fuel control
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)

Abstract

An auxiliary power supply architecture includes one APU and a fuel supply basic circuit with a common fuel storage tank, a primary circulation conduct and secondary conducts for injecting such fuel into the combustion chambers of the APU unit through appropriate injectors. Such architecture also includes another independent fuel supply circuit to supply the APU unit with an emergency tank, a specific primary conduct for emergency fuel circulation and secondary conducts for injecting emergency fuel into the combustion chambers through appropriate injectors.

Claims

1. An auxiliary power supply method for an aircraft, being equipped with main engines and power consumers, through an auxiliary power supply unit (APU), provided with a combustion chamber, said method comprising:

in a primary mode, supplying non propulsive power with said APU to consumers of the aircraft from a source of a common fuel being common to the engines of the aircraft and to the APU,

performing a basic circulation of said common fuel up to the combustion chamber of the APU,

in an emergency mode, providing emergency power to vital systems of the aircraft with said APU, and

supplying the combustion chamber of the APU unit with emergency fuel from a specific source according to an independent circulation being separated, at least in one part connected with the specific source, from the basic circulation.

2. The supply method according to claim 1, further comprising, in an emergency mode, injecting the emergency fuel for combustion in the APU separately from injecting the common fuel in the primary mode.

3. The supply method according to claim 1, wherein, the common fuel being kerosene, the emergency fuel is hydrogen being directly stocked in a solid, liquid or gaseous state within the specific source.

4. The supply method according to claim 3, further comprising producing the hydrogen with an appropriate refining of kerosene being stocked within the specific source.

5. The supply method according to claim 1, wherein, upon failure detection, the emergency mode is triggered by a centralized command that releases the emergency fuel, drains fuel circulations, controls a specific fuel flow rate, and switches the independent circulation into the basic circulation and leads to firing of the APU.

6. A power supply architecture for supplying auxiliary power, comprising:

an auxiliary power supply unit (APU),

a fuel supply basic circuit, wherein said fuel supply basic circuit comprises a common fuel storage tank for an aircraft propulsion assembly including the APU, a primary circulation conduct for a common fuel and secondary conducts for injecting said common fuel into a combustion chamber of the APU through appropriate injectors, and

an independent fuel supply circuit to supply the APU with fuel, said independent fuel supply circuit comprising an emergency tank, a specific primary conduct for emergency fuel circulation and secondary conducts for injecting emergency fuel into the combustion chamber of the APU through appropriate injectors.

7. The power supply architecture according to claim 6, wherein, the emergency fuel is hydrogen, the specific primary circuit comprises a refining arrangement for converting kerosene being stocked in the tank into hydrogen via a reformer.

8. The power supply architecture according to claim 6, wherein the fuel injection secondary conducts for the basic circuit and the independent circuit are distinct, with injectors being dedicated to the common fuel and other injectors dedicated to the emergency fuel.

9. The power supply architecture according to claim 6, wherein the fuel injection secondary conducts for the basic circuit and the independent circuit are grouped together so that, the primary and secondary conducts being respectively mounted upstream and downstream from a switching valve, the secondary conducts circulate the common fuel or the emergency fuel up to the injectors being common to such fuels.

10. The power supply architecture according to claim 8, wherein the emergency tank comprises one storage part for hydrogen in a solid state and one buffer storage part for hydrogen in a liquid state and is associated with a pyrotechnical generator as well as to a control valve mounted on the primary conduct on a hydrogen gas output.

11. The power supply architecture according to claim 6, further comprising an emergency electronic command unit piloting a hydrogen flow rate control valve, a pyrotechnical generator as well as the APU based on information regarding valve opening and pressure at the APU level.

12. The power supply architecture according to claim 6, wherein a strong pressure draining system piloted by the electronic command unit is provided for draining circuit residues.