Redundant starting/generating system
First Claim
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1. 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.
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Abstract
A power conversion system allows for redundant starting and generating functions and eliminates equipment normally found in a conventional system so that size and weight are reduced.
110 Citations
22 Claims
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1. A power conversion system, comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. 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:
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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. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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19. 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:
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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. - View Dependent Claims (20, 21, 22)
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Specification