Reduced bleed vapor compression cycle environmental control system for aircraft

• US 6,908,062 B2
• Filed: 12/09/2003
• Issued: 06/21/2005
• Est. Priority Date: 05/08/2001
• Status: Expired due to Term

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Jules Ricardo Munoz, Luca Bertuccioli, Roger W. Radomsky Jr
• Inventors: Bertuccioli, Luca, Munoz, Jules Ricardo, Radomsky, Roger W. Jr.
• Primary Examiner(s): Swiatek, Robert P.
• Application Number:
  US10/731,184
• Publication Number:
  US 20040155147A1
• Time in Patent Office: 560 Days
• Field of Search: 244/53.R, 244/118.5, 454/71, 454/76, 622/41
• US Class Current: 244/118.5
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: B64D 2013/0614 with subsystems for cooling avionics
• 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

The present invention relates to A reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.

Claims

1. An environmental control system for an aircraft comprising:

means for receiving air external to the aircraft;

means for compressing said external air to a desired pressure;

means for cooling said compressed air to a desired temperature;

said cooling means comprising a vapor compression cycle;

said vapor compression cycle loop including evaporation means for removing heat from said compressed air, a refrigerant flowing through said loop and heat from said compressed air being transferred to said refrigerant in said evaporation means, and means for compressing said refrigerant exiting said evaporation means;

said external air compression means comprising a first compressor, said refrigerant compressing means comprising a second compressor, and means for driving said first and second compressors;

said driving means comprising a turbine and means for supplying engine bleed air to said turbine; and

said first and second compressors and said turbine being located on a single shaft.

2. An environmental control system for an aircraft comprising:

means for receiving air external to the aircraft;

means for compressing said external air to a desired pressure;

means for cooling said compressed air to a desired temperature;

said cooling means comprising a vapor compression cycle;

said vapor compression cycle loop including evaporation means for removing heat from said compressed air, a refrigerant flowing through said loop and heat from said compressed air being transferred to said refrigerant in said evaporation means, and means for compressing said refrigerant exiting said evaporation means;

said loop further including means for removing heat from said compressed refrigerant; and

additional external air being supplied to said loop and said heat removing means comprising a condenser for receiving said compressed refrigerant from said refrigerant compressing means and for transferring heat from said refrigerant to said additional external air.

3. An environmental control system according to claim 2, wherein said loop further includes means for reducing pressure in said refrigerant exiting said heat removing means.

4. An environmental control system according to claim 3, wherein said pressure reducing means comprises an expansion valve.

5. A method for delivering cooled air at a desired pressure to a compartment on an aircraft comprising the steps of:

providing an air compressor;

inputting air external to said aircraft into said air compressor and compressing said external air;

cooling said external air after said external air exits said air compressor;

delivering said cooled external air to said compartment;

said cooling step comprising providing a refrigerant loop having an evaporator through which a refrigerant flows and passing said compressed external air through said evaporator and transferring heat from said compressed external air to said refrigerant;

compressing said refrigerant exiting said evaporator using a refrigerant compressor; and

providing a turbine, bleeding air from an engine to drive said turbine, and driving both said air compressor and said refrigerant compressor using said turbine.

6. A method for delivering cooled air at a desired pressure to a compartment on an aircraft comprising the steps of:

providing an air compressor;

inputting air external to said aircraft into said air compressor and compressing said external air;

cooling said external air after said external air exits said air compressor;

delivering said cooled external air to said compartment;

said cooling step comprising providing a refrigerant loop having an evaporator through which a refrigerant flows and passing said compressed external air through said evaporator and transferring heat from said compressed external air to said refrigerant;

compressing said refrigerant exiting said evaporator using a refrigerant compressor; and

providing said loop with heat removal means, supplying additional external air to said heat removal means, and transferring heat from said compressed refrigerant to said additional external air by passing said compressed refrigerant through said heat removal means.

7. A method according to claim 6, further comprising reducing pressure of said refrigerant exiting said heat removal means and passing said refrigerant at said reduced pressure to said evaporator.

8. An environmental control system for an aircraft comprising:

means for receiving air external to the aircraft;

means for compressing said external air to a desired pressure;

means for cooling said compressed air to a desired pressure;

said cooling means comprising a vapor compression cycle loop;

said vapor compression cycle loop containing an evaporator for removing heat from said compressed air; and

means for delivering air exiting said compressing means directly to said evaporator and for delivering cooled air exiting said evaporator to a compartment onboard said aircraft.

9. An environmental control system according to claim 8, wherein a refrigerant flows through said loop and heat from said compressed air is transferred to said refrigerant in said evaporator.

10. An environmental control system according to claim 9, wherein said loop further includes means for compressing said refrigerant exiting said evaporator.

11. An environmental control system according to claim 10, further comprising said external air compression means comprising a first compressor, said refrigerant compressing means comprising a second compressor, and means for driving said first and second compressors.

12. An environmental control system according to claim 11, wherein said driving means comprises a turbine and means for supplying engine bleed air to said turbine.

13. An environmental control system according to claim 10, wherein said loop further includes means for removing heat from said compressed refrigerant.

14. An environmental control system according to claim 8, further comprising said delivering means comprising means for delivering said cooled air to a cabin onboard said aircraft.

15. An environmental control system according to claim 14, further comprising means for removing moisture from said external air prior to delivering said cooled air to said cabin.

16. An environmental control system according to claim 15, wherein said moisture removing means comprises a water separator.

17. A method for delivering cooled air at a desired pressure to a compartment on an aircraft comprising the steps of:

providing an air compressor;

inputting air external to said aircraft into said air compressor and compressing said external air;

cooling said external air after said external air exits said air compressor;

said cooling step comprising providing a refrigerant loop having an evaporator through which a refrigerant flows and passing said external air through said evaporator and transferring heat from said compressed external air to said refrigerant; and

delivering said external air exiting said compressor directly to said evaporator; and

delivering said air exiting said evaporator to said compartment.

18. A method according to claim 17, further comprising removing moisture from said cooled external air prior to delivering said cooled external air to said compartment.

19. A method according to claim 17, further comprising compressing said refrigerant exiting said evaporator using a refrigerant compressor.

20. A method according to claim 17, wherein said delivering step comprises delivering said cooled external air to a cabin onboard said aircraft.