Hybrid-electric single engine descent failure management
AssigneeRtx Corporation
InventorMarc J. Muldoon
Life of this patent
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Abstract
A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, first and second ducting systems fluidly communicative with each other and with the first and second hybrid-electric engines, respectively, and a control system. The control system is operably coupled to each of the first and second hybrid-electric engines and to each of the first and second ducting systems. The control system is configured to run the first hybrid-electric engine normally, to run the second hybrid-electric engine in a lower power mode and to control each of the first and second ducting systems to direct bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
Claims20
A hybrid-electric aircraft system, comprising:
- hybrid-electric engines;
- ducting systems fluidly communicative with each other and with the hybrid-electric engines, respectively;
- and
- a control system operably coupled to each of the hybrid-electric engines and to each of the ducting systems,
- the control system runs one of the hybrid-electric engines in a first mode and runs another of the hybrid-electric engines in a second mode during certain flight operations, and
- the control system is configured to control each of the ducting systems to direct bleed air from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
A hybrid-electric aircraft system, comprising:
- hybrid-electric engines;
- ducting systems fluidly communicative with each other and with the hybrid-electric engines, respectively;
- and
- a control system operably coupled to each of the hybrid-electric engines and to each of the ducting systems,
- the control system being configured to run one of the hybrid-electric engines at a first idle level, to run another one of the hybrid-electric engines at a second idle level below the first idle level and to control each of the ducting systems to direct bleed air from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
A method of operating a hybrid-electric aircraft system comprising hybrid-electric engines, the method comprising:
- initiating a fuel conservation mode;
- running the hybrid-electric engines in first and second modes, respectively;
- and
- directing bleed air from one of the hybrid-electric engines running in the first mode to another of the hybrid-electric engines running in the second mode.
Dependencies are inferred from the claim text.