Hybrid-electric single engine descent failure management
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.
1. 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,
wherein the control system runs the one of the hybrid-electric engines in the first mode and runs the another of the hybrid-electric engines in the second mode during descent.
2. The hybrid-electric aircraft system according to claim 1 , wherein, while running the one of the hybrid-electric engines in the first mode and while running the another of the hybrid-electric engines in the second mode, the control system is further configured to:
cease extracting air or electro-mechanical loads from the another of the hybrid-electric engines, and
divert electrical power from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
3. The hybrid-electric aircraft system according to claim 1 , wherein the control system runs the one of the hybrid-electric engines in the first mode and runs the another of the hybrid-electric engines in the second mode while simultaneously controlling each of the ducting systems to direct the bleed air from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
4. The hybrid-electric aircraft system according to claim 1 , wherein each of the hybrid-electric engines comprises:
a gas turbine engine with a combustor, high-and low-pressure compressors and high-and low-pressure turbines; and
high-and low-spool electric machines to drive operations of the gas turbine engine.
5. The hybrid-electric aircraft system according to claim 4 , wherein each of the ducting systems comprises:
an environmental control system (ECS) line;
bleed air lines by which the bleed air from the high-and low-pressure compressors of the corresponding one of the hybrid-electric engines is directed to the ECS line; and
controllable valves arranged along the bleed air lines and between the ECS line and the bleed lines to control flows of the bleed air to the ECS line from the high- and low-pressure compressors of the corresponding one of the hybrid-electric engines.
6. The hybrid-electric aircraft system according to claim 5 , further comprising a cabin air conditioning system by which the ECS lines of the ducting systems are fluidly communicative.
7. 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.
8. The hybrid-electric aircraft system according to claim 7 , wherein, while running the one of the hybrid-electric engines at the first idle level and while running the another of the hybrid-electric engines at the second idle level below the first idle level, the control system is further configured to:
cease extracting air or electro-mechanical loads from the another of the hybrid-electric engines, and
divert electrical power from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
9. The hybrid-electric aircraft system according to claim 7 , wherein the control system runs the one of the hybrid-electric engines at the first idle level and runs the another of the hybrid-electric engines at the second idle level below the first idle level while simultaneously controlling each of the ducting systems to direct the bleed air from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
10. The hybrid-electric aircraft system according to claim 7 , wherein the control system runs the one of the hybrid-electric engines at the first idle level and runs the another of the hybrid-electric engines at the second idle level below the first idle level during descent.
11. The hybrid-electric aircraft system according to claim 7 , wherein each of the hybrid-electric engines comprises:
a gas turbine engine with a combustor, high-and low-pressure compressors and high-and low-pressure turbines; and
high-and low-spool electric machines to drive operations of the gas turbine engine.
12. The hybrid-electric aircraft system according to claim 11 , wherein each of the ducting systems comprises:
an environmental control system (ECS) line;
bleed air lines by which the bleed air from the high-and low-pressure compressors of the corresponding one of the hybrid-electric engines is directed to the ECS line; and
controllable valves arranged along the bleed air lines and between the ECS line and the bleed lines to control flows of the bleed air to the ECS line from the high-and low-pressure compressors of the corresponding one of the hybrid-electric engines.
13. The hybrid-electric aircraft system according to claim 12 , further comprising a cabin air conditioning system by which the ECS lines of the ducting systems are fluidly communicative.
14. 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,
wherein the initiating is executed during descent.
15. The method according to claim 14 , wherein the running of the another of the hybrid-electric engines comprises ceasing extraction of air and electro-mechanical loads from the another of the hybrid-electric engines.
16. The method according to claim 14 , wherein the running of the another of the hybrid-electric engines comprises diverting electrical power from the one of the hybrid-electric engines to the another of the hybrid-electric engines.
17. The method according to claim 14 , wherein the running comprises:
running the one of the hybrid-electric engines at a first idle level; and
running the another of the hybrid-electric engines at a second idle level below the first idle level.
18. The method according to claim 14 , wherein the running of the one of the hybrid-electric engines and the another of the hybrid-electric engines in the first and second modes, respectively, and the directing of bleed air from the one of the hybrid-electric engines to the another of the hybrid-electric engines are simultaneous.