System and method for controlling an environment in an aircraft using a vortex cooler

• US 20080271465A1
• Filed: 10/18/2006
• Published: 11/06/2008
• Est. Priority Date: 10/18/2006
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Cessna Aircraft Company (Textron Inc)
• Inventors: Mossberg, Robert E., Beuning, Charles B.
• Granted Patent: US 8,099,966 B2
• Time in Patent Office: Days
• US Class Current: 62/5
• CPC Class Codes: B64D 13/02 the air being pressurised
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: B64D 2013/0618 with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

Disclosed is an air conditioning system for an aircraft which utilizes high pressure bleed air. The bleed air is pressure controlled and introduced into a vortex cooler which can be operated in two modes using a valve. In a first mode, the bleed air is divided into cold and hot streams. The cold stream is directed into the cabin for cooling purposes. The hot stream is released from the aircraft in a manner that it pulls ambient air across a heat exchanger. In a second mode, the bleed air is not divided, but passes through the vortex cooler as a common stream. The second mode is more commonly used in colder ambient air conditions.

Claims

1. A system for controlling at least one condition in a substantially enclosed environment, said system comprising:

a high-pressure air source;

a vortex cooler adapted to receive a pressure controlled supply airflow from said high pressure air source;

said system being operable in a first mode in which said vortex cooler divides said supply airflow into a hot stream and a cold stream;

said system being operable in a second mode in which said supply airflow is released from said vortex cooler in an undivided common stream;

said substantially-enclosed environment being adapted to receive said cold stream when said system is being operated in said first mode; and

said substantially-enclosed environment being adapted to receive said undivided common stream when said system is being operated in said second mode.

2. The system of claim 1 wherein said system includes a heat exchanger which receives, cools, and then exhausts said airflow.

3. The system of claim 2 wherein said heat exchanger is adapted to receive cooling air, and then release said cooling air from an exhaust duct.

4. The system of claim 3 wherein said hot stream is introduced into said exhaust duct in a direction away from said exchanger thus creating a vacuum in said exhaust duct which draws said cooling air across said exchanger even if said aircraft is not in flight.

5. The system of claim 3 wherein said system is adapted such that when operated in said first mode said hot stream is ejected into said exhaust duct from an induction mechanism.

6. The system of claim 5 wherein said induction mechanism is adapted to direct said hot stream into said exhaust duct in a direction away from said heat exchanger.

7. The system of claim 6 wherein said induction mechanism is an elbow.

8. The system of claim 7 wherein said system and said substantially enclosed environment are included in an aircraft and said system is adapted to receive cooling air from outside said aircraft by an air scoop, said system then being adapted to drive said cooling air across said exchanger.

9. The system of claim 8 wherein said induction mechanism is adapted such that when said hot stream is ejected ample suction is created in said exhaust duct to pull cooling air across said heat exchanger to create a temperature drop in said supply airflow when said aircraft is not in flight.

10. The system of claim 1 wherein said hot air stream, upon leaving said vortex cooler, is directed into a conduit, said conduit including a valve, said valve adapted such that, when open, causes said system to be in said first mode, and when closed, causes said system to be in said second mode.

11. The system of claim 10 comprising:

a temperature sensor in one of said substantially enclosed environment and said cold stream; and

a control device adapted to receive a reading from said temperature sensor and open said valve when said temperature exceeds a predetermined temperature.

12. The system of claim 1 including a pressure regulator which regulates the pressure of said pressure controlled supply airflow before reaching said vortex cooler.

13. A system for controlling air temperatures in a substantially enclosed area in an aircraft, said system comprising:

a duct for receiving a supply of pressurized air from an engine;

a heat exchanger disposed in said duct for reducing temperatures in said supply air using available ram air as a cooling medium;

a splitter device for dividing said supply of pressurized air into a hot stream and a cold stream;

a first conduit for receiving said cold stream and directing said cold stream into said substantially enclosed area; and

a second conduit for receiving said hot stream and directing said hot stream away from said heat exchanger in a ram air exhaust duct.

14. The system of claim 13 wherein said splitter device is a vortex tube.

15. A method of maintaining temperatures and pressures in a substantially enclosed environment, said method comprising:

bleeding high-pressure air from a high-pressure air source; and

providing a first mode of operation and a second mode of operation;

said first mode comprising (i) controlling the pressure of said high-pressure air source, (ii) receiving said high-pressure air into a mechanism, (iii) dividing said high pressure air into hot and cold streams using said mechanism, and (iv) releasing said cold stream into said substantially enclosed environment;

said second mode comprising (i) controlling the pressure of said high-pressure air source, (ii) receiving said high-pressure air into said mechanism, (iii) releasing said high-pressure air from said mechanism in an undivided common stream, and (iv) introducing said high pressure air into said substantially enclosed environment.

16. The method of claim 15 comprising:

using a heat exchanger to further control said temperatures in said substantially enclosed environment.

17. The method of claim 16 wherein said substantially enclosed environment is on an aircraft and said first mode further comprises:

releasing said hot stream into an exhaust duct of said heat exchanger to create a vacuum in said exhaust duct thus pulling cooling air across said heat exchanger even when said aircraft is not in flight.

18. The method of claim 17 comprising:

receiving said cooling air using an air scoop located on said aircraft for the purpose of driving said cooling air across said exchanger.

19. The method of claim 17 comprising:

providing a conduit for delivering said hot air stream, upon leaving said mechanism, into said exhaust duct; and

valving said conduit to enable switching between said first and second modes.

20. The method of claim 15 comprising:

providing a pressure regulator for the purpose of controlling the pressure of said high-pressure air and providing a vortex tube to serve as said mechanism.