Environmental cooling systems for aircraft
View Patent ↗A method for supplying pressurized air to an aircraft includes that bleed air is bled from a portion of a turbomachine of the aircraft and a thrust output of the turbomachine is increased to increase a pressure of the bleed air in a predetermined environmental condition. The method also includes that modes of an environmental control system (ECS) are switched from a first operating mode configured to receive bleed air from each engine of the aircraft in a first environmental condition to a second operating mode configured to receive bleed air from at least one engine of the aircraft in a second environmental condition. The method further includes that engine thrust is increased in at least one engine and engine thrust is reduced from at least the other engine to maintain a constant total thrust when the ECS is in the second operating mode.
1. A method for supplying pressurized air to an aircraft, comprising:
bleeding bleed air from a portion of a turbomachine of the aircraft;
increasing a thrust output of the turbomachine to increase a pressure of the bleed air in a predetermined environmental condition;
switching modes of an environmental control system (ECS) from a first operating mode configured to receive bleed air from each engine of the aircraft in a first environmental condition, wherein the pressure of the bleed air is about equal from each engine, to a second operating mode configured to receive bleed air from at least one engine of the aircraft in a second environmental condition, wherein the pressure of the bleed air is different between at least two engines; and
increasing engine thrust in at least one engine and reducing engine thrust from at least the other engine to maintain a constant total thrust when the ECS is in the second operating mode.
2. The method of claim 1 , wherein the turbomachine is a first turbomachine, further comprising reducing a thrust output of a second turbomachine of the aircraft to maintain a constant total thrust.
3. The method of claim 1 , wherein increasing the thrust output includes increasing the thrust output of a first turbomachine and a second turbomachine that is symmetrically located relative to the first turbomachine.
4. The method of claim 3 , wherein the thrust output of the first and second turbomachines is increased by about an equal amount to prevent asymmetric thrust induced yaw.
5. The method of claim 3 , further comprising reducing a thrust output of a third turbomachine of the aircraft to maintain a constant total thrust.
6. The method of claim 5 , wherein reducing the thrust output further includes reducing the thrust output of a fourth turbomachine that is symmetrically located relative to the third turbomachine to prevent asymmetric thrust induced yaw.
7. The method of claim 1 , wherein switching modes of the ECS includes switching at least one ECS pack from a first cooling mode to a second cooling mode.
8. The method of claim 7 , wherein switching modes of the ECS includes maintaining a constant cooling mode in at least one ECS pack.
9. The method of claim 1 , wherein switching modes can include shutting off bleed air from the engines connected to the single mode ECS packs using at least one ECS packs.
10. The method of claim 1 , wherein the turbomachine is a first turbomachine, further comprising reducing a thrust output of a second turbomachine of the aircraft to maintain a constant total thrust, and wherein increasing the thrust output includes increasing the thrust output of a first turbomachine and a second turbomachine that is symmetrically located relative to the first turbomachine.
11. The method of claim 10 , wherein the thrust output of the first and second turbomachines is increased by about an equal amount to prevent asymmetric thrust induced yaw.
12. The method of claim 10 , further comprising reducing a thrust output of a third turbomachine of the aircraft to maintain a constant total thrust.
13. The method of claim 12 , wherein reducing the thrust output further includes reducing the thrust output of a fourth turbomachine that is symmetrically located relative to the third turbomachine to prevent asymmetric thrust induced yaw.
14. The method of claim 10 , wherein switching modes of the ECS includes switching at least one ECS pack from a first cooling mode to a second cooling mode.
15. The method of claim 14 , wherein switching modes of the ECS includes maintaining a constant cooling mode in at least one ECS pack.
16. The method of claim 10 , wherein switching modes can include shutting off bleed air from the engines connected to the single mode ECS packs using at least one ECS packs.
17. The method of claim 1 , wherein the turbomachine is a first turbomachine, further comprising reducing a thrust output of a second turbomachine of the aircraft to maintain a constant total thrust, and
wherein switching modes of the ECS includes switching at least one ECS pack from a first cooling mode to a second cooling mode.
18. The method of claim 17 , wherein switching modes of the ECS includes maintaining a constant cooling mode in at least one ECS pack.
19. The method of claim 1 , wherein increasing the thrust output includes increasing the thrust output of a first turbomachine and a second turbomachine that is symmetrically located relative to the first turbomachine, and
wherein switching modes of the ECS includes switching at least one ECS pack from a first cooling mode to a second cooling mode.
20. The method of claim 19 , wherein switching modes of the ECS includes maintaining a constant cooling mode in at least one ECS pack.