Aircraft electrical network

• US 10,131,441 B2
• Filed: 04/22/2016
• Issued: 11/20/2018
• Est. Priority Date: 05/19/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Edwards, Huw L., Smith, Alexander C, Apsley, Judith M., Manolopoulos, Charalampos
• Primary Examiner(s): Badawi, Medhat
• Application Number:
  US15/136,074
• Publication Number:
  US 20160340051A1
• Time in Patent Office: 942 Days
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 27/02 Aircraft characterised by the type or position of power plants fuselages specially adapted for mounting power plants B64C1/16; wings specially adapted for power plants B64C3/32
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 35/02 specially adapted for specific power plants
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An electrical network for an aircraft. The aircraft includes at least one variable pitch propulsor. The electrical network includes a wound field synchronous AC electrical generator having a wound rotor driven by an internal combustion engine. The network further includes a voltage regulator configured to regulate output voltage of the electrical generator by regulating rotor winding magnetic field strength, and a synchronous AC drive motor coupled to a respective variable pitch propulsor and provided with power from the output of the electrical generator.

Claims

1. An aircraft, comprising:

a variable pitch propulsor; and

an electrical network comprising;

a wound field synchronous AC electrical generator having a wound rotor driven by an internal combustion engine;

a voltage regulator configured to regulate an output voltage of the wound field synchronous AC electrical generator by varying an electrical current provided to a winding of the wound rotor to adjust magnetic field strength of the winding; and

a synchronous AC drive motor coupled to the variable pitch propulsor and provided with power from an output of the wound field synchronous AC electrical generator.

2. The aircraft of claim 1, wherein the synchronous AC drive motor comprises a permanent magnet motor.

3. The aircraft of claim 1, wherein the electrical network comprises a frequency converter configured to convert an input frequency generated by the wound field synchronous AC generator to an output frequency provided to the synchronous AC drive motor.

4. The aircraft of claim 3, wherein the electrical network comprises a switching arrangement configurable to either of a starting position, in which the synchronous AC drive motor is electrically coupled to the electrical network via the frequency converter, and a drive position, in which the synchronous AC drive motor is directly electrically coupled to the wound field synchronous AC electrical generator.

5. The aircraft of claim 1, wherein the variable pitch propulsor comprises a variable pitch propeller.

6. The aircraft of claim 4, wherein the electrical network comprises a controller configured to control the electrical network such that, when in the starting position, the variable pitch propulsor is set to a fine pitch and the switching arrangement is configured to the starting position.

7. The aircraft of claim 3, wherein the frequency converter is electrically coupled to a plurality of synchronous AC drive motors.

8. The aircraft of claim 1, wherein the wound field synchronous AC electrical generator comprises a wound field generator with an exciter control system configured to vary the magnetic field strength of the rotor winding to control the output voltage of the wound field synchronous AC electrical generator.

9. The aircraft of claim 1, wherein the internal combustion engine comprises one of a gas turbine engine and a piston engine.

10. The aircraft of claim 1, comprising a plurality of variable pitch propulsors.

11. The aircraft of claim 1, wherein a stator of the wound field synchronous AC electrical generator comprises an equal number of magnetic poles as a stator of the synchronous AC drive motor.

12. A method of controlling the electrical network of the aircraft of claim 1, comprising:

modulating the output voltage of the wound field synchronous AC electrical generator to reduce a phase angle of induced EMF and current phasors in the synchronous AC drive motor.

13. A method of controlling the electrical network of the aircraft of claim 3, comprising:

operating the electrical network in one of a starting mode and a flight mode, wherein when in the starting mode, the synchronous AC drive motor is electrically coupled to the electrical network via the frequency converter and the variable pitch propulsor is set to fine pitch, and when in the drive mode, the synchronous AC drive motor is directly electrically coupled to the wound field synchronous AC electrical generator.

14. The method of claim 13, further comprising:

operating the electrical network in an inflight re-synchronisation mode, wherein stator windings of the synchronous AC drive motor are disconnected from the electrical network, rotor pitch is set such that the variable pitch propulsor is caused to rotate at a speed such that the motor is synchronised with the output frequency of the wound field synchronous AC electrical generator, and the stator windings are subsequently reconnected once the motor achieves synchronization.