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:
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 operably coupled to each of the first and second hybrid-electric engines and to each of the first and second ducting systems,
wherein:
the control system runs the first hybrid-electric engine normally and runs the second hybrid-electric engine in a lower power mode during descent, and
the control system is configured 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.
2. The hybrid-electric aircraft system according to claim 1 , wherein, while running the first hybrid-electric engine normally and while running the second hybrid-electric engine in the lower power mode, the control system is further configured to cease extracting air or electro-mechanical loads from the second hybrid-electric engine and to divert electrical power from the first hybrid-electric engine to the second hybrid-electric engine.
3. The hybrid-electric aircraft system according to claim 1 , wherein the control system runs the first hybrid-electric engine normally and runs the second hybrid-electric engine in the lower power mode while simultaneously controlling each of the first and second ducting systems to direct the bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
4. The hybrid-electric aircraft system according to claim 1 , wherein each of the first and second 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 first and second ducting systems comprises:
an environmental control system (ECS) line;
first and second bleed air lines by which the bleed air from the high- and low-pressure compressors of the corresponding one of the first and second hybrid-electric engines is directed to the ECS line; and
controllable valves arranged along the first and second bleed air lines and between the ECS line and the first and second 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 first and second hybrid-electric engines.
6. The hybrid-electric aircraft system according to claim 5 , further comprising a cabin air conditioning system by which each of the ECS lines of the first and second ducting systems are fluidly communicative.
7. A hybrid-electric aircraft system, comprising:
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 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 being configured to run the first hybrid-electric engine at a minimum descent idle level, to run the second hybrid-electric engine at below the minimum descent idle level 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.
8. The hybrid-electric aircraft system according to claim 7 , wherein, while running the first hybrid-electric engine at the minimum descent idle level and while running the second hybrid-electric engine at below the minimum descent idle level, the control system is further configured to cease extracting air or electro-mechanical loads from the second hybrid-electric engine and to divert electrical power from the first hybrid-electric engine to the second hybrid-electric engine.
9. The hybrid-electric aircraft system according to claim 7 , wherein the control system runs the first hybrid-electric engine at the minimum descent idle level and runs the second hybrid-electric engine at below the minimum descent idle level while simultaneously controlling each of the first and second ducting systems to direct the bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
10. The hybrid-electric aircraft system according to claim 7 , wherein the control system runs the first hybrid-electric engine at the minimum descent idle level and runs the second hybrid-electric engine at below the minimum descent idle level during descent.
11. The hybrid-electric aircraft system according to claim 7 , wherein each of the first and second 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 first and second ducting systems comprises:
an environmental control system (ECS) line;
first and second bleed air lines by which the bleed air from the high- and low-pressure compressors of the corresponding one of the first and second hybrid-electric engines is directed to the ECS line; and
controllable valves arranged along the first and second bleed air lines and between the ECS line and the first and second 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 first and second hybrid-electric engines.
13. The hybrid-electric aircraft system according to claim 12 , further comprising a cabin air conditioning system by which each of the ECS lines of the first and second ducting systems are fluidly communicative.
14. A method of operating a hybrid-electric aircraft system comprising first and second hybrid-electric engines, the method comprising:
initiating a fuel conservation mode during descent;
running the first and second hybrid-electric engines normally and in a low power mode, respectively; and
directing bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
15. The method according to claim 14 , wherein the running of the second hybrid-electric engine comprises ceasing extraction of air and electro-mechanical loads from the second hybrid-electric engine.
16. The method according to claim 14 , wherein the running of the second hybrid-electric engine comprises diverting electrical power from the first hybrid-electric engine to the second hybrid-electric engine.
17. The method according to claim 14 , wherein the running comprises:
running the first hybrid-electric engine at a minimum descent idle level; and
running the second hybrid-electric engine at below the minimum descent idle level.
18. The method according to claim 14 , wherein the running of the first and second hybrid-electric engines normally and in the low power mode, respectively, and the directing of bleed air from the first hybrid-electric engine to the second hybrid-electric engine are simultaneous.