Power system for aircraft parallel hybrid gas turbine electric propulsion system
AssigneeUnited Technologies Corporation
InventorsCharles E. Lents, Jonathan Rheaume
Life of this patent
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Abstract
A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.
Claims20
A gas turbine engine comprising:
- a compressor section having a first compressor and a second compressor;
- a turbine section having a first turbine and a second turbine,
- the first compressor is connected to the first turbine via a first shaft;
- the second compressor is connected to the second turbine via a second shaft;
- a motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft;
- and
- a power distribution system connecting the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit, wherein the power distribution system is configured to provide power from the stored power system to the motor.
A gas turbine engine comprising:
- a compressor section having a first compressor and a second compressor;
- a turbine section having a first turbine and a second turbine,
- the first compressor is connected to the first turbine via a first shaft;
- the second compressor is connected to the second turbine via a second shaft;
- a motor connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft;
- a power distribution system connecting the motor to an energy storage unit and a supplementary power unit;
- and
- wherein the supplementary power unit is electrically connected to said motor via said power distribution system such that electricity from the supplementary power unit drives rotation of the motor.
A method for operating a gas turbine engine comprising:
- operating a gas powered turbine engine at a peak efficiency during a first mode of operation;
- providing power to the gas turbine engine from a motor when said engine is operating in a second mode of operation, where the second mode of operation has a higher thrust requirement than the first mode of operation;
- and
- generating at least a portion of the power provided to the motor using a supplemental power unit, wherein the supplemental power unit converts a fuel expenditure into electric power.
Dependencies are inferred from the claim text.