Aircraft load shedding system including supplementary power sources for assuring DC and device for cutting off power to the alternators of a turbine engine during acceleration

• US 9,988,158 B2
• Filed: 04/22/2014
• Issued: 06/05/2018
• Est. Priority Date: 04/22/2013
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Lebrun, Arnaud, Lepage, Thomas, McGrath, Darragh
• Primary Examiner(s): Patel, Tulsidas C
• Assistant Examiner(s): Mikailoff, S.
• Application Number:
  US14/785,124
• Publication Number:
  US 20160083106A1
• Time in Patent Office: 1,505 Days
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 4/00 Circuit arrangements for mains or distribution networks not specified as ac or dc
• CPC Class Codes: H02J 7/1415 with a generator driven by a prime mover other than the motor of a vehicle
• CPC Class Codes: H02J 7/1423 with multiple batteries
• CPC Class Codes: H02J 7/143 with multiple generators
• CPC Class Codes: H02J 7/1446 in response to parameters of a vehicle
• CPC Class Codes: H02J 7/345 using capacitors as storage or buffering devices
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: H02P 9/008 wherein the generator is controlled by the requirements of the prime mover
• CPC Class Codes: H02P 9/48 Arrangements for obtaining a constant output value at varying speed of the generator, e.g. on vehicle H02P9/04 - H02P9/46 take precedence
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, includes at least one electrical energy storage capacity, at least one generator driven mechanically by a rotation shaft of the turbine engine and electrical connections between the electrical energy storage capacity, the generator and the aircraft equipment for powering the above-mentioned equipment with DC current, also including at least one alternative for supplying DC current to the equipment, which are autonomous in relation to any mechanical driving by a rotation shaft of the turbine engine, and a device that can cut-off power to the generator(s) and simultaneously activate the alternative current supply. The power cut-off device for triggering power cut-off and activating the alternative current supply is controlled by a control or operating parameter of the turbine engine. The alternative current supply is preferably formed by one or more supercapacitors.

Claims

1. An electric power generation system for supplying current to a piece of equipment for an aircraft propelled by a turbine engine, the electric power generation system comprising:

a capacitor for storing electrical energy;

a current generator designed to be mechanically driven by a rotary shaft of the turbine engine;

electrical connections between said capacitor for storing electrical energy, said generator, and the piece of equipment of the aircraft in order to supply current to said piece of equipment, the electrical connections including;

a first DC bus which receives energy from the current generator,

a battery bus which receives energy from the first DC bus and delivers the energy received from the first DC bus to the capacitor,

a second DC bus which supplies energy from the capacitor to the piece of equipment of the aircraft,

a recharging bus which receives current from the first DC bus and is connected to the first DC bus via a first switch,

an alternative means for providing said piece of equipment with current, the alternative means being autonomous with respect to any mechanical driving by a rotary shaft of the turbine engine, the alternative means being a device for storing electrical energy from current supplied from the recharging bus,

a second switch which connects the alternative means to the first DC bus, such that the alternative means provides energy to the piece of equipment of the aircraft when the second switch is in a closed position; and

a power supply controller configured to shed a load of said generator and to simultaneously activate said alternative means,

wherein said power supply controller is configured to

when an acceleration of the turbine engine is greater than a predetermined value, stop operation of the generator and close the second switch such that the alternative means provides current to the piece of equipment of the aircraft, and

when the acceleration of the turbine engine is less than the predetermined value and the alternative means is not fully charged, restart the generator and operate the generator at a speed higher than a nominal operating speed of the generator, open the second switch, and close the first switch so as to charge the alternative means.

2. The electric power generation system according to claim 1, wherein the device for storing electrical energy of the alternative means is formed by at least one supercapacitor.

3. The electric power generation system according to claim 1, wherein said generator operates at a speed equal to 120% of the nominal operating speed of the generator as soon as said second switch is opened.

4. The electric power generation system according to claim 3, wherein said generator operates at a speed equal to 150% of the nominal operating speed of the generator for a period of less than 30 seconds.

5. A turbine engine comprising an electric power generation system according to claim 1.