BLENDED FLOW AIR CYCLE SYSTEM FOR ENVIRONMENTAL CONTROL

• US 20130133348A1
• Filed: 11/28/2011
• Published: 05/30/2013
• Est. Priority Date: 11/28/2011
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Squier, Steven E.
• Granted Patent: US 9,555,893 B2
• Time in Patent Office: Days
• US Class Current: 62/172
• 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: B64D 2013/0648 with energy recovery means, e.g. using turbines
• CPC Class Codes: B64D 2013/0688 with means for recirculating cabin air
• CPC Class Codes: F25B 9/004 the refrigerant being air
• CPC Class Codes: F25B 9/10 with several cooling stages
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

An aircraft air provision system includes a power turbine that receives bleed air at a first pressure and provides rotational energy to a shaft and outputs output air at an intermediate pressure. The system also includes a compressor coupled to the shaft that receives input air at a second pressure that is lower than the first pressure and outputs compressed air having a pressure equal to the intermediate pressure and a mix chamber coupled to outputs of both the power turbine and the compressor where the output air and the compressed air are mixed. The system also includes a cooling turbine coupled to the shaft and that is in fluid communication with an output of the mix chamber.

Claims

1. An aircraft air provision system comprising:

a power turbine that receives bleed air at a first pressure and that provides rotational energy to a shaft and outputs output air at an intermediate pressure;

a compressor coupled to the shaft that receives input air at a second pressure that is lower than the first pressure and outputs compressed air having a pressure equal to the intermediate pressure;

a mix chamber coupled to outputs of both the power turbine and the compressor where the output air and the compressed air are mixed; and

a cooling turbine coupled to the shaft and that is in fluid communication with an output of the mix chamber.

2. The system of claim 1, wherein the bleed air is received from a bleed air supply that includes an engine having a compressor section.

3. The system of claim 2, further comprising:

a precooling heat exchanger in fluid communication with an input of the power turbine and configured to cool air exiting the compressor section.

4. The system of claim 3, wherein the precooling heat exchanger utilizes air from a fan of the engine to cool air exiting the compressor section.

5. The system of claim 3, wherein the input air is received from an output of the precooling heat exchanger.

6. The system of claim 1, wherein the input air is received from a ram air scoop.

7. The system of claim 1, further comprising:

a heat exchanger coupled between the mix chamber and the cooling turbine that utilizes air from a same source as the input air to cool air that exits the output of the mix chamber.

8. The system of claim 7, further comprising:

a fan coupled to the shaft, wherein the fan draws air through the heat exchanger.

9. The system of claim 1, further comprising:

a cabin air recirculation system coupled to an output of the cooling turbine.

10. A method of providing air to cabin of an aircraft comprising:

providing bleed air to a power turbine at a first pressure to produce rotational energy on a shaft and produce output air at an intermediate pressure;

compressing air at a second pressure, in a compressor coupled to the shaft, into compressed air having a pressure equal to the intermediate pressure, wherein the second pressure is less than the first pressure;

providing the output air and the compressed air having a pressure at the intermediate pressure to a mix chamber coupled to outputs of both the power turbine and the compressor;

mixing the compressed air and the output air in the mix chamber to form mixed air; and

providing the mixed air to a cooling turbine coupled to the shaft.

11. The method of claim 10, wherein the bleed air is provided by a bleed air supply that includes an engine having a compressor section.

12. The method of claim 11, further comprising:

cooling the bleed air in a precooling heat exchanger in fluid before providing it to the power turbine.

13. The method of claim 12, wherein the precooling heat exchanger utilizes air from a fan of the engine to cool air exiting the compressor section.

14. The method of claim 13, wherein input air to compress is received from an output of the precooling heat exchanger.

15. The method of claim 10, wherein input air to compress is received from a ram air scoop.

16. The method of claim 10, further comprising:

cooling the mixed air before providing it to the cooling turbine.