Fault tolerant starting/generating system

• US 6,037,752 A
• Filed: 06/30/1997
• Issued: 03/14/2000
• Est. Priority Date: 06/30/1997
• Status: Expired due to Term

• Current Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Glennon, Timothy F.
• Primary Examiner(s): Ponomarenko, Nicholas
• Application Number:
  US08/884,748
• Time in Patent Office: 988 Days
• Field of Search: 290/4 C, 290/4 D, 290/31, 290/36 R, 290/38 R, 290/47, 322/7, 322/9, 322/22, 322/23, 322/24, 307/19
• US Class Current: 322/22
• CPC Class Codes: F02N 11/04 the motors being associated with current generators
• CPC Class Codes: H05K 7/1432 specially adapted for power drive units or power converters

Abstract

A power conversion system allows for redundant starting and generating functions together with fault tolerant operation through the multiple use of power conversion equipment.

Claims

1. A power conversion system, comprising:

first and second prime movers;

first and second pairs of generators coupled to the first and second prime movers, respectively;

a load bus;

a power source; and

a power converter interconnecting the generators, the load bus and the power source and operable in a starting mode of operation such that power from the power source is conditioned and supplied to one of the generators of the first pair of generators to cause the one generator to operate as a motor and start the first prime mover and the power converter being subsequently operable to provide power from the one generator to a generator of the second pair of generators to cause such generator to operate as a motor and thereby start the second prime mover.

2. The power conversion system of claim 1, wherein power for the generator of the second pair of generators is developed by the one generator of the first pair of generators.

3. The power conversion system of claim 1, wherein power for the generator of the second pair of generators is developed by the power source.

4. The power conversion system of claim 1, wherein the power converter is further operable in a generating mode to condition power developed by at least one of the generators and to deliver such conditioned power to the load bus.

5. The power conversion system of claim 1, wherein the prime movers comprise aircraft engines.

6. The power conversion system of claim 1, wherein the power source comprises a battery.

7. The power conversion system of claim 1, wherein the power source comprises an AC power source.

8. The power conversion system of claim 1, wherein the load bus receives variable frequency power from at least one of the generators.

9. The power conversion system of claim 1, wherein the power converter comprises a plurality of identical power converter units and further including additional load buses, a first switch matrix coupled between the generators and the power converter units and a second switch matrix coupled between the power converter units and the load buses.

10. The power conversion system of claim 9, wherein the power source comprises a battery and each power converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link and an inverter coupled between the DC link and the second switch matrix.

11. The power conversion system of claim 9, wherein each of the first and second switch matrices comprises a rotary device including a housing having a plurality of sets of housing contacts and a rotor having a set of rotor contacts selectively engageable with one of the sets of housing contacts.

12. A power conversion system for an aircraft, comprising:

first and second aircraft engines;

an auxiliary power unit (APU);

first and second pairs of generators coupled to the first and second aircraft engines, respectively, and a third pair of generators coupled to the APU;

a first load bus coupled to an electrically driven hydraulic pump;

a second, variable frequency bus;

a first switch matrix coupled to the generators;

first through sixth power converter units coupled to the first switch matrix;

a second switch matrix coupled between the first through sixth power converter units and the load buses; and

a control operable in a starting mode to cause at least one of the power converter units to provide conditioned power to at least one of the generators to cause the at least one generator to operate as a motor and start the APU or the aircraft engine coupled thereto and subsequently operable to cause the at least one of the power converter units to provide power selectively to each of the remaining generators to cause the remaining generators to operate as motors and thereby start the APU and/or aircraft engines coupled thereto and further operable in a generating mode to provide power developed by one or more of the generators to the load buses.

13. The power conversion system of claim 12, wherein power for the remaining generators is developed by the at least one generator.

14. The power conversion system of claim 12, wherein power for the remaining generators is developed by the power source.

15. The power conversion system of claim 12, wherein the control comprises a contactor control for the first and second switch matrices.

16. The power conversion system of claim 15, wherein the power converter units are identical to one another.

17. The power conversion system of claim 12, wherein each of the first and second switch matrices comprises a rotary device including a stator having a plurality of sets of stator contacts and a rotor having a set of rotor contacts selectively engageable with one of the sets of stator contacts.

18. The power conversion system of claim 12, wherein each power converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link and an inverter coupled between the DC link and the second switch matrix.

19. A power conversion system for an aircraft having first and second pairs of generators coupled to first and second aircraft engines, respectively, and a third pair of generators coupled to an auxiliary power unit (APU) wherein the aircraft further includes a first set of load buses coupled to electrically driven hydraulic pumps, a second set of load buses coupled to variable frequency loads and a DC bus coupled to DC loads, comprising:

a first switch matrix coupled to the generators;

identical first through sixth power converter units coupled to the first switch matrix;

a second switch matrix coupled between the first through sixth power converter units and the first and second sets of load buses; and

a control for controlling the first and second switch matrices and the power converter units and operable in a starting mode to cause at least one of the power converter units to provide conditioned power to one of the generators to cause the one generator to operate as a motor and start the APU or the aircraft engine coupled thereto and subsequently operable to cause the at least one of the power converter units to provide power developed by the one generator selectively to each of the remaining generators to cause the remaining generators to operate as motors and thereby start the APU and/or aircraft engines coupled thereto and further operable in a generating mode to provide conditioned AC power to the first set of load buses, variable frequency AC power to the second set of load buses and DC power to the DC bus;

wherein each power converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link and an inverter coupled between the DC link and the second switch matrix.

20. The power conversion system of claim 19, wherein each of the first and second switch matrices comprises a rotary device including a stator having a plurality of sets of stator contacts and a rotor having a set of rotor contacts selectively engageable with one of the sets of stator contacts.