ELECTRIC PROPULSION SYSTEM
First Claim
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1. A propulsion system for an aeronautical device comprising:
- an electric propulsor;
a gas turbine engine comprising a compressor section, a turbine section, and a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine;
an electric machine coupled to the rotary component of the gas turbine engine, the electric machine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine;
an electric communication bus electrically connecting the electric machine to the electric propulsor; and
a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.
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Abstract
A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.
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Citations
20 Claims
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1. A propulsion system for an aeronautical device comprising:
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an electric propulsor; a gas turbine engine comprising a compressor section, a turbine section, and a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine; an electric machine coupled to the rotary component of the gas turbine engine, the electric machine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine; an electric communication bus electrically connecting the electric machine to the electric propulsor; and a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
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16. A propulsion system for an aeronautical device comprising:
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an electric propulsor; a first gas turbine engine comprising a rotary component; a first electric machine coupled to the rotary component of the first gas turbine engine, the first electric machine being a center-tapped to ground AC electric generator; a second gas turbine engine comprising a rotary component; and a second electric machine coupled to the rotary component of the second gas turbine engine, the second electric machine being a center-tapped to ground AC electric generator; and an electric communication bus electrically connecting the first electric machine and second electric machine to the electric propulsor, the electric communication bus comprising at least one AC-to-DC converter for converting an AC voltage from the first electric machine and an AC voltage from the second electric machine to a positive DC voltage and a negative DC voltage for powering the electric propulsor. - View Dependent Claims (17, 18)
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19. A propulsion system for an aeronautical device comprising:
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an electric propulsor; a first gas turbine engine comprising a rotary component; a first electric machine coupled to the rotary component of the first gas turbine engine, the first electric machine being a DC electric generator configured to generate a positive DC voltage; a second gas turbine engine comprising a rotary component; and a second electric machine coupled to the rotary component of the second gas turbine engine, the second electric machine being a DC electric generator configured to generate a negative DC voltage; and an electric communication bus electrically connecting the first electric machine and second electric machine to the electric propulsor to provide the electric propulsor a net differential voltage equal to about twice a magnitude of the positive DC voltage. - View Dependent Claims (20)
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Specification