Aircraft starting and generating system

Patent metadata

Field	Value
Publication number	US-10312849-B2
Application number	US-201515550827-A
Country	US
Kind code	B2
Filing date	Feb 18, 2015
Priority date	Feb 18, 2015
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

Abstract

An aircraft starting and generating system includes a starter/generator and an inverter/converter/controller ( 200 ) that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. A four leg inverter is coupled with a DC power output ( 452 ) of the starter/generator and has an inverter/converter/controller (ICC) ( 580 ) with a four leg MOSFET-based bridge configuration that drives the starter/generator in a start mode for starting a prime mover of the aircraft, and converts DC power to AC power in a generate mode of the starter/generator. A four leg bridge gate driver ( 560 ) is configured to drive the four leg MOSFET-based bridge ( 580 ) during start and generate mode using bi-polar pulse width modulation (PWM).

First claim

What is claimed is:

1. An aircraft starting and generating system, comprising:
a starter/generator that includes a main machine, an exciter, and a permanent magnet generator;
a direct current (DC) power output from the starter/generator;
a four leg inverter coupled with the DC power output and having an inverter/converter/controller (ICC) having a four leg metal oxide semiconductor field effect transistor (MOSFET)-based bridge configuration, and that generates DC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts DC power, obtained from the starter/generator after the prime mover have been started, to alternating current (AC) power in a generate mode of the starter/generator; and
a four leg bridge gate driver configured to drive the four leg MOSFET-based bridge;
wherein the four leg bridge gate driver operates to drive the four leg MOSFET-based bridge during start and generate mode using bi-polar pulse width modulation (PWM).

2. The aircraft starting and generating system of claim 1 wherein the four leg MOSFET-based bridge configuration further comprises three legs each having a single phase output of a three phase AC output and a fourth leg having a neutral output.

3. The aircraft starting and generating system of claim 2 wherein the three phase AC output is 400 Hz.

4. The aircraft starting and generating system of claim 1 wherein the four leg MOSFET-based bridge further comprises at least one of a silicon carbide-based bridge or Gallium Nitride-based bridge.

5. The aircraft starting and generating system of claim 1 , further comprising an exciter MOSFET-based bridge that is connected to an exciter stator of the exciter, and an exciter bridge gate driver configured to drive the exciter MOSFET-based bridge.

6. The aircraft starting and generating system of claim 5 wherein the exciter MOSFET-based bridge further comprises at least one of a silicon carbide-based bridge or Gallium Nitride-based bridge.

7. The aircraft starting and generating system of claim 1 , further comprising a main machine MOSFET-based bridge that is connected to a stator of the main machine, and a main machine bridge gate driver configured to drive the main machine MOSFET-based bridge.

8. The aircraft starting and generating system of claim 7 wherein the main machine comprises a main machine MOSFET-based bridge configuration that absorbs excess power of the system in a regeneration mode by storing the excess power in the kinetic energy of the prime mover of the aircraft, and wherein the main machine bridge gate driver operates to drive the main machine MOSFET-based bridge during regeneration mode using Space Vector Pulse Width Modulation.

9. The aircraft starting and generating system of claim 7 wherein the main machine MOSFET-based bridge further comprises at least one of a silicon carbide-based bridge or Gallium Nitride-based bridge.

10. The aircraft starting and generating system of claim 1 wherein the four leg MOSFET-based bridge further comprises an array of individually-controllable MOSFETs.

11. The aircraft starting and generating system of claim 10 wherein the four leg bridge gate driver operates to drive each individually-controllable MOSFET.

12. The aircraft starting and generating system of claim 1 wherein the four leg MOSFET-based bridge further comprises individually-controllable wide bandgap device MOSFETs.

13. The aircraft starting and generating system of claim 12 wherein the MOSFETs further comprise external diodes configured across a body diode of the MOSFETs.

14. A method of controlling an aircraft starting and generating system having a starter/generator that includes a main machine having a DC power output, an exciter, and a permanent magnet generator, a four leg converter coupled with the DC power output and having an inverter/converter/controller (ICC) having a MOSFET-based bridge configuration, and a four leg bridge gate driver configured to drive the MOSFET-based bridge, the method comprising:
if in start mode, supplying power to the four leg MOSFET-based bridge and driving the four leg MOSFET-based bridge during start mode using bi-polar Pulse Width Modulation (PWM), and wherein the driving the main MOSFET-based bridge during start mode starts a prime mover of the aircraft; and
if in generating mode, driving the four leg MOSFET-based bridge using bi-polar PWM to convert DC power, obtained from the DC power output of the starter/generator, to four leg AC power.

15. The method of claim 14 , further comprising, if in motoring mode, supplying power to the four leg MOSFET-based bridge and driving the four leg MOSFET-based bridge during start mode using bi-polar PWM, and wherein the driving the main MOSFET-based bridge during start mode rotates a prime mover of the aircraft.

16. The method of claim 15 further comprising performing diagnostic tests on at least one of the starter/generator or the prime mover.

17. The method of claim 14 , further comprising if in start mode, switching to generating mode after the starting the prime mover of the aircraft.

18. The method of claim 14 wherein, if in generating mode, the driving the MOSFET-based bridge further comprises converting the DC power to 400 Hz AC power.

19. An aircraft comprising:
an engine;
a starter/generator connected to the engine and having a main machine, an exciter, and a permanent magnet generator;
a direct current (DC) power output from the starter/generator;
a four leg inverter coupled with the DC power output and having an inverter/converter/controller (ICC) having a four leg metal oxide semiconductor field effect transistor (MOSFET)-based bridge configuration, and that generates DC power to drive the starter/generator in a start mode for starting the engine, and that converts DC power, obtained from the starter/generator after the engine has been started, to alternating current (AC) power in a generate mode of the starter/generator; and
a four leg bridge gate driver configured to drive the four leg MOSFET-based bridge;
wherein the four leg bridge gate driver operates to drive the four leg MOSFET-based bridge during start and generate mode using bi-polar pulse width modulation (PWM).

20. The aircraft of claim 19 wherein the four leg MOSFET-based bridge configuration further comprises three legs each having a single phase output of a three phase AC output and a fourth leg having a neutral output.

Assignees

• Ge Aviation Systems Llc

Inventors

• Huang Hao

Classifications

• F02N11/04

  the motors being associated with current generators · CPC title

• F02C7/268 Primary

  Starting drives for the rotor {, acting directly on the rotor of the gas turbine to be started} · CPC title

• B60L15/02 Primary

  characterised by the form of the current used in the control circuit · CPC title

• B60L2220/14

  Synchronous machines · CPC title

• H02P21/50

  Vector control arrangements or methods not otherwise provided for in H02P21/00- H02P21/36 · CPC title