ENVIRONMENTAL CONTROL SYSTEM UTILIZING CABIN DISCHARGE AIR TO POWER A CYCLE

• US 20160311538A1
• Filed: 04/24/2015
• Published: 10/27/2016
• Est. Priority Date: 04/24/2015
• 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: Bruno, Louis J., Surawski, Eric, Army, Donald E. Jr., Zywiak, Thomas M., Hipsky, Harold W., Kline, Erin G., Rusich, Richard, Maljanian, John M. Jr., D'Orlando, Paul M.
• Granted Patent: US 9,783,307 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• 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: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air directly flows from a source to either a compressor of the air cycle machine or the at least one heat exchanger in accordance with a high pressure, low pressure, or pressure boost operation mode. The system and method also can also utilize recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.

Claims

1. An environmental control system, comprising:

an air cycle machine comprising a compressor; and

an inlet configured to supply a flow of bleed air directly to the compressor of the air cycle machine.

2. The environmental control system of claim 1, further comprises:

a secondary heat exchanger; and

a quench loop connecting an exhaust of the secondary heat exchanger to the flow of the bleed being supplied directly to the compressor,

wherein the quench loop is configured to reduce an energy of the bleed air before the bleed air directly enters the compressor.

3. The environmental control system of claim 2, further comprises:

a high pressure water separator configured to condition the bleed air before the bleed air is passed to a chamber; and

a turbine of the air cycle machine configured to receive the conditioned bleed air from the high pressure water separator,

wherein as the conditioned bleed air expands across the turbine, work is extracted by the air cycle machine to compress the bleed air received directly by the compressor.

4. The environmental control system of claim 1, further comprises:

a flow valve configured to cause the flow of the bleed air to bypass the compressor and flow directly into the secondary heat exchanger.

5. The environmental control system of claim 1, wherein the air cycle machine comprises a turbine, and

wherein recirculated air expands across the turbine based on energy ratio to turn a shaft of the air cycle machine.

6. The environmental control system of claim 1, wherein the environmental control system is included within an aircraft.

7. An environmental control system, comprising:

a secondary heat exchanger;

an air cycle machine comprising a compressor;

an inlet configured to supply a flow of bleed air directly to the environmental control system; and

a flow valve configured to;

cause the flow of the bleed air to bypass the compressor and flow directly into the secondary heat exchanger or

cause the flow of the bleed air to flow directly to the compressor.

8. The environmental control system of claim 7, wherein the air cycle machine comprises a turbine, and

wherein recirculated air expands across the turbine based on an energy ratio to turn a shaft of the air cycle machine.

9. The environmental control system of claim 7, further comprises:

a second flow valve configured to cause the flow of air exiting the secondary heat exchanger to flow directly to the chamber.

10. The environmental control system of claim 9, wherein the flow valve is configured to cause bleed air to flow directly to the compressor, and

wherein recirculated air expands across the turbine based on an energy ratio to turn a shaft of the air cycle machine thereby providing energy to drive the compressor.

11. The environmental control system of claim 7, wherein the environmental control system is included within an aircraft.