Redundant starting/generating system

Claim 2

A power conversion system, comprising: a pair of prime movers; a pair of generators each coupled to a prime mover; a load bus; a power source; a pair of power converter units interconnecting the generators, the load bus and the power source; and a supervisory control operable in a starting mode to cause either of the power converter units to condition power from either of the power source and one of the generators and provide such conditioned power to another of the generators to cause such other generator to operate as a motor and thereby start the prime mover coupled thereto.

Claim 3

The power conversion system of claim 1, wherein each power converter unit 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.

Claim 4

The power conversion system of claim 1, wherein at least one electrically driven pump is coupled to and receives power from the load bus.

Claim 5

The power conversion system of claim 3, wherein the prime movers comprise aircraft engines.

Claim 6

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

Claim 7

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

Claim 8

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

Claim 9

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

Claim 10

The power conversion system of claim 8, wherein the power source comprises a battery and each converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link, an inverter coupled between the DC link and the second switch matrix and a bidirectional converter coupled between the battery and the DC link.

Claim 11

A power conversion system for an aircraft having first and second generators coupled to first and second aircraft engines, respectively, and a third generator coupled to an auxiliary power unit (APU) wherein the aircraft further includes a first load bus coupled to an electrically driven hydraulic pump and a second, variable frequency bus, comprising: a first switch matrix coupled to the generators; first through third power converter units coupled to the first switch matrix; a second switch matrix coupled between the first through third power converter units and the load buses; a DC power source coupled to the power converter units; a supervisory control operable in a starting mode to cause any one of the power converter units to provide conditioned power obtained from the DC power source to the third generator to cause the third generator to operate as a motor and start the APU and subsequently operable to cause any one of the power converter units to provide power developed by the third generator to one of the first and second generators to cause such generator to operate as a motor and thereby start the aircraft engine coupled thereto and further operable in a generating mode to provide power developed by the generators to the load buses.

Claim 12

A power conversion system for an aircraft having first and second generators coupled to first and second aircraft engines, respectively, and a third generator coupled to an auxiliary power unit (APU) wherein the aircraft further includes a first load bus coupled to an electrically driven hydraulic pump and a second, variable frequency bus, comprising: a first switch matrix coupled to the generators; first through third power converter units coupled to the first switch matrix; a second switch matrix coupled between the first through third power converter units and the load buses; a DC power source coupled to the power converter units; a supervisory control operable in a starting mode to cause any one of the power converter units to provide conditioned power obtained from the DC power source to the third generator to cause the third generator to operate as a motor and start the APU and subsequently operable to cause any one of the power converter units to provide power developed by the third generator to one of the first and second generators to cause such generator to operate as a motor and thereby start the aircraft engine coupled thereto and further operable in a generating mode to provide power developed by the generators to the load buses.

Claim 13

The power conversion system of claim 10, wherein the supervisory control comprises a contactor control for the first and second switch matrices.

Claim 14

The power conversion system of claim 11, wherein the power converter units are identical to one another.

Claim 15

The power conversion system of claim 12, wherein the DC power source comprises a battery.

Claim 16

The power conversion system of claim 13, wherein each power converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link, an inverter coupled between the DC link and the second switch matrix and a bidirectional converter coupled between the battery and the DC link.

Claim 17

The power conversion system of claim 14, wherein the bidirectional converter includes a charger for the battery.

Claim 18

The power conversion system of claim 14, wherein each power converter unit includes a charger for the battery wherein the charger is separate from the bidirectional converter.

Claim 19

The power conversion system of claim 14, further including a DC bus and contactors operable to connect the DC bus to the bidirectional converter.

Claim 20

The power conversion system of claim 10, further including an external AC power source coupled to the first switch matrix.

Claim 21

A power conversion system for an aircraft having first and second generators coupled to first and second aircraft engines, respectively, and a third generator 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 400 Hz. bus, 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 third power converter units coupled to the first switch matrix; a second switch matrix coupled between the first through third power converter units and the first and second sets of load buses; a battery; and a supervisory control for controlling the first and second switch matrices and the power converter units and operable in a starting mode to cause any one of the power converter units to provide conditioned power obtained from the battery to the third generator to cause such generator to operate as a motor and start the APU and subsequently operable to cause any one of the power converter units to provide power developed by the third generator sequentially to the remaining generators to cause the remaining generators to operate as motors and thereby sequentially start the aircraft engines and further operable in a generating mode to cause the generators to provide conditioned AC power to the first set of power buses, variable frequency AC power to the second set of load buses, DC power to the DC bus and 400 Hz. power to the 400 Hz. bus; wherein each power converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link, an inverter coupled between the DC link and the second switch matrix and a bidirectional converter coupled between the battery and the DC link.

Claim 22

A power conversion system for an aircraft having first and second generators coupled to first and second aircraft engines, respectively, and a third generator 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 400 Hz. bus, 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 third power converter units coupled to the first switch matrix; a second switch matrix coupled between the first through third power converter units and the first and second sets of load buses; a battery; and a supervisory control for controlling the first and second switch matrices and the power converter units and operable in a starting mode to cause any one of the power converter units to provide conditioned power obtained from the battery to the third generator to cause such generator to operate as a motor and start the APU and subsequently operable to cause any one of the power converter units to provide power developed by the third generator sequentially to the remaining generators to cause the remaining generators to operate as motors and thereby sequentially start the aircraft engines and further operable in a generating mode to cause the generators to provide conditioned AC power to the first set of power buses, variable frequency AC power to the second set of load buses, DC power to the DC bus and 400 Hz. power to the 400 Hz. bus; wherein each power converter unit comprises a rectifier circuit coupled between the first switch matrix and a DC link, an inverter coupled between the DC link and the second switch matrix and a bidirectional converter coupled between the battery and the DC link.

Claim 23

The power conversion system of claim 19, wherein the supervisory control comprises a contactor control for the first and second switch matrices.

Claim 24

The power conversion system of claim 20, wherein the bidirectional converter includes a charger for the battery.

Claim 25

The power conversion system of claim 21, further including an external AC power source coupled to the first switch matrix.