Environmental cooling systems for aircraft
An environmental control system (ECS) for a multi-engine aircraft includes a controller configured to switch the ECS between a plurality of operating modes. The plurality of operating modes includes 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. The plurality of operating modes includes 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.
1. An environmental control system (ECS) for a multi-engine aircraft, comprising:
a controller configured to switch the ECS between a plurality of operating modes, the plurality of operating modes comprising:
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; and
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,
wherein the controller is operatively connected to a thrust controller to cause engine thrust to increase in at least one engine and to reduce thrust from at least one other engine to maintain a constant total thrust when the ECS is in the second operating mode.
2. The system of claim 1 , wherein bleed air from at least one engine is shut off in the second environmental condition.
3. The system of claim 1 , wherein the controller is operatively connected to the thrust controller to increase or reduce thrust symmetrically to prevent asymmetric thrust induced yaw.
4. The system of claim 1 , further comprising a plurality of ECS packs, each ECS pack connected to a respective one of the engines, wherein at least one of the plurality of ECS packs is a mode changing ECS pack that is operative to change from a first cooling mode in the first operational mode to a second cooling mode in the second operational mode, wherein the second cooling mode allows the ECS pack to operate with higher bleed air pressure than the first cooling mode.
5. The system of claim 4 , wherein each ECS pack includes a heat exchanger operative to cool the bleed air.
6. The system of claim 4 , wherein the plurality of ECS packs includes two mode changing packs connected to symmetric engines, and wherein two single mode ECS packs are connected to the remaining engines.
7. The system of claim 6 , wherein the single mode ECS packs are configured to shut off bleed air from their respective engines when the ECS is in the second operating mode.
8. An aircraft, comprising:
a plurality of engines; and
an environmental control system (ECS), comprising:
a controller configured to switch the ECS between a plurality of operating modes, the plurality of operating modes comprising:
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; and
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,
wherein the controller is operatively connected to a thrust controller to cause engine thrust to increase in at least one engine and to reduce thrust from at least one other engine to maintain a constant total thrust when the ECS is in the second operating mode.
9. The aircraft of claim 8 , wherein bleed air from at least one engine is shut off in the second environmental condition.
10. An environmental control system (ECS) for a multi-engine aircraft, comprising:
a controller configured to switch the ECS between a plurality of operating modes, the plurality of operating modes comprising:
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;
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
a plurality of ECS packs, each ECS pack connected to a respective one of the engines, wherein at least one of the plurality of ECS packs is a mode changing ECS pack that is operative to change from a first cooling mode in the first operational mode to a second cooling mode in the second operational mode, wherein the second cooling mode allows the ECS pack to operate with higher bleed air pressure than the first cooling mode.
11. The system of claim 10 , wherein the controller is operatively connected to a thrust controller to cause engine thrust to increase in at least one engine and to reduce thrust from at least one other engine to maintain a constant total thrust when the ECS is in the second operating mode.
12. The system of claim 10 , wherein bleed air from at least one engine is shut off in the second environmental condition.
13. The system of claim 11 , wherein the controller is operatively connected to the thrust controller to increase or reduce thrust symmetrically to prevent asymmetric thrust induced yaw.
14. The system of claim 10 , wherein each ECS pack includes a heat exchanger operative to cool the bleed air.
15. The system of claim 10 , wherein the plurality of ECS packs includes two mode changing packs connected to symmetric engines, and wherein two single mode ECS packs are connected to the remaining engines.
16. The system of claim 15 , wherein the single mode ECS packs are configured to shut off bleed air from their respective engines when the ECS is in the second operating mode.