METHOD AND APPARATUS FOR STARTING AN AIRCRAFT ENGINE AND OPERATING A POWER ARCHITECTURE FOR AN AIRCRAFT
First Claim
1. A method of starting an aircraft having at least a first turbine engine having a first starter/generator (S/G) and a second turbine engine having a second S/G using at least one bi-directional converter and at least one of an AC power source having an AC power output and a first DC power source having a DC power output, the method comprising:
- selectively starting at least one of the first S/G or second S/G in an AC start mode, where the AC power output is supplied to a first bi-directional converter, which converts the AC power output to a second DC power output supplied to the at least one of the first S/G or second S/G, and in a DC start mode, where the DC power output is supplied to start the at least one of the first S/G or second S/G.
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Accused Products
Abstract
A method and apparatus for starting and operating at least a first starter/generator (S/G) and a second S/G using at least one bi-directional converter and at least one of an AC power source and a first DC power source, including selectively starting at least one of the first S/G or second S/G in an AC start mode or in a DC start mode, and supplying electrical power to a set of electrical loads.
44 Citations
20 Claims
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1. A method of starting an aircraft having at least a first turbine engine having a first starter/generator (S/G) and a second turbine engine having a second S/G using at least one bi-directional converter and at least one of an AC power source having an AC power output and a first DC power source having a DC power output, the method comprising:
selectively starting at least one of the first S/G or second S/G in an AC start mode, where the AC power output is supplied to a first bi-directional converter, which converts the AC power output to a second DC power output supplied to the at least one of the first S/G or second S/G, and in a DC start mode, where the DC power output is supplied to start the at least one of the first S/G or second S/G. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A power architecture for an aircraft, comprising:
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a power-generating source having a direct current (DC) power output; a primary power bus operating with DC power and coupled with the DC power output; a secondary power bus operating with alternating current (AC) power; and at least one bi-directional converter having a DC lead and an AC lead, and configured to bi-directionally convert DC power received at the DC lead to AC power at the AC lead, and to convert AC power received at the AC lead to DC power at the DC lead. - View Dependent Claims (12, 13, 14, 15)
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16. A method of operating a power architecture for an aircraft, comprising:
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supplying DC power from a power-generating source to a primary DC power bus; converting, by a bi-directional converter, DC power from the DC power bus to AC power, and supplying the AC power to an AC power bus; and redundantly supplying the DC power and the AC power to respective DC and AC consuming electrical loads. - View Dependent Claims (17, 18, 19, 20)
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Specification