On-board inert gas generation turbocompressor systems and methods

• US 8,015,838 B2
• Filed: 12/21/2007
• Issued: 09/13/2011
• Est. Priority Date: 12/21/2007
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Lotterman, Jeff A., Lippold, Timothy J., Isella, Giorgio C., Schryver, Jon E.
• Primary Examiner(s): Jones; Melvin
• Application Number:
  US11/962,591
• Publication Number:
  US 20100310392A1
• Time in Patent Office: 1,362 Days
• Field of Search: 624/01, 624/02, 624/19, 417/405, 415/177
• US Class Current: 62/401
• CPC Class Codes: B64D 13/00 Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space , or structural parts of the aircraft treatment rooms with artificial climate for medical purposes A61G10/02; respiratory apparatus in general A62B; for vehicles in general B60H
• CPC Class Codes: B64D 2013/0677 comprising on board oxygen generator systems
• CPC Class Codes: B64D 2013/0685 with ozone control
• CPC Class Codes: B64D 37/32 Safety measures not otherwise provided for, e.g. preventing explosive conditions extinguishing or preventing fires in aircraft A62C
• CPC Class Codes: F04D 25/04 the pump being fluid-driven pumps driven by exhaust gases F02B37/00, F02B39/00; turbochargers F02C6/12
• CPC Class Codes: F04D 27/02 Surge control surge detection F04D27/001
• CPC Class Codes: F04D 29/582 specially adapted for elastic fluid pumps
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

The present invention provides a system and method for cooling the bleed air supply in an on-board inert gas generation system. The gas generation system cools the bleed air using a turbocompressor in conjunction with heat exchangers. Exhaust from a regenerative heat exchanger providing air to the turbocompressor is ported to a ram air outlet using a flow-restriction/ejector unit.

Claims

1. A thermal control module of a gas generation system comprising:

a turbine wheel connected to a pressurized air supply such that the pressurized air from said pressurized air supply rotates the turbine wheel and said pressurized air becomes cooled air;

a regenerative heat exchanger receiving cooled air from said turbine wheel, receiving pressurized air from said pressurized air supply, cooling said pressurized air to generate cooled air and generating exhaust air;

a compressor rotated by said turbine wheel, receiving the cooled air from said regenerative heat exchanger and generating compressed air; and

an ejector connected to said regenerative heat exchanger providing said exhaust air into ram air flow;

wherein the pressure ratio across the turbine wheel remains stable relative to altitude changes.

2. The thermal control module of claim 1, wherein said air supply has been depleted of ozone.

3. The thermal control module of claim 1, wherein said compressed air is provided to a primary heat exchanger.

4. The thermal control module of claim 1, wherein said air supply to the turbine is controlled with a turbocompressor shutoff valve.

5. The thermal control module of claim 1, wherein said regenerative heat exchanger is a plate-fin heat exchanger.

6. The thermal control module of claim 3, wherein said primary heat exchanger passes ram air through the ram air duct.

7. The thermal control module of claim 6 wherein said primary heat exchanger receives ram air through a ram air inlet.

8. The thermal control module of claim 6 wherein said primary heat exchanger receives fanned air through a ram air inlet.

9. A gas generation system comprising;

a bleed air supply;

a control valve connected to said bleed air supply and controlling flow of said supplied bleed air;

a turbocompressor comprising a turbine and a compressor, and connected to said control valve to receive bleed air;

wherein said turbine is rotated by the received bleed air and said received bleed air is evacuated as turbine exhaust air;

a regenerative heat exchanger receiving bleed air and cooling said bleed air by passing turbine exhaust air in thermally conductive proximity to said bleed air to generate cooled bleed air and expels turbine exhaust air into ram air;

wherein said turbine rotates the compressor and the compressor receives said cooled bleed air and generates compressed air;

a primary heat exchanger receiving compressed air from said turbocompressor;

wherein said primary heat exchanger cools said compressed air by passing said compressed air in thermally conductive proximity to ram air.

10. The gas generation system of claim 9 further comprising an overtemperature valve controlling air flow from said primary heat exchanger and an air separation module.

11. The gas generation system of claim 10, wherein said air separation module provides oxygen enriched air and nitrogen enriched air.

12. The gas generation system of claim 11 wherein said nitrogen enriched air is distributed to a fuel tank.

13. The gas generation system of claim 9 wherein said turbocompressor comprises a turbine and a compressor.

14. The gas generation system of claim 13 wherein said turbine is rotationally connected to said compressor.

15. The gas generation system of claim 9 wherein said turbocompressor provides compressed air to said primary heat exchanger.

16. The gas generation system of claim 9 further comprising a flow restriction device regulating air flow from the regenerative heat exchanger to the ram flow outlet.

17. The gas generation system of claim 9 further comprising an ejector forcing air flow from the regenerative heat exchanger to the ram flow outlet.

18. A method of gas generation thermal control comprising:

generating rotational motion in a turbine using bleed air;

rotating a compressor using said rotational motion;

receiving bleed air at a regenerative heat exchanger;

receiving cooled air from the turbine;

providing cooled bleed air to the compressor;

providing compressed air from the compressor;

porting exhaust air from the regenerative heat exchanger to a ram air outlet.

19. The method of claim 18 wherein a check valve prevents compressed air from circulating.

20. The method of claim 18 wherein said exhaust air is provided to a flow restriction device.