ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT UTILIZING TURBO-COMPRESSOR

• US 20130174573A1
• Filed: 01/09/2012
• Published: 07/11/2013
• Est. Priority Date: 01/09/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Hipsky, Harold W., Suciu, Gabriel L., Dye, Christopher M.
• Granted Patent: US 8,904,805 B2
• Time in Patent Office: Days
• US Class Current: 60/785
• CPC Class Codes: B64D 13/04 Automatic control of pressure
• CPC Class Codes: B64D 2013/0644 including electric motors or generators
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines

Abstract

An environmental control system includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with a gas turbine engine. A lower pressure tap is associated with a lower pressure location, which is at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into the turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section of the turbocompressor and the turbine section intermix and pass downstream to be delivered to an aircraft use.

Claims

1. An environmental control system for an aircraft comprising:

a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft, and a lower pressure tap to be associated with a lower pressure location, said lower pressure location being at a lower pressure than said higher pressure location;

said lower pressure tap communicating to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor;

said higher pressure tap leading into a turbine section of said turbocompressor such that air in said higher pressure tap drives said turbine section to in turn drive said compressor section of said turbocompressor; and

a combined outlet of said compressor section of said turbocompressor and said turbine section intermixing and passing downstream to be delivered to an aircraft use.

2. The environmental control system as set forth in claim 1, wherein a valve is on said first passage associated with said lower pressure tap.

3. The environmental control system as set forth in claim 2, wherein said valve is a check valve.

4. The environmental control system as set forth in claim 2, wherein a control valve is positioned on said higher pressure tap, and may be closed to drive air through said first passage associated with said lower pressure tap, or to have air pass through said compressor section of said turbocompressor when said control valve is opened.

5. The environmental control system as set forth in claim 4, wherein a redundant valve is provided to be closed if said control valve associated with said higher pressure tap fails.

6. The environmental control system as set forth in claim 5, wherein said redundant valve is positioned to be downstream of a location at which said first passage and said combined outlet intermix into a common conduit.

7. A gas turbine engine comprising:

a fan section delivering air into a main compressor section, said main compressor section compressing air and delivering air into a combustion section, products of combustion passing from said combustion section over turbine sections to drive said fan and main compressor sections; and

an environmental control system including a higher pressure tap at a higher compression location in said main compressor section, and a lower pressure tap at a lower pressure location, said lower pressure location being at a lower pressure than said higher pressure location;

said lower pressure tap communicating to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor;

said higher pressure tap leading into a turbine section of said turbocompressor such that air in said higher pressure tap drives said turbine section to in turn drive said compressor section of said turbocompressor; and

a combined outlet of said compressor section of said turbocompressor and said turbine section intermixing and passing downstream to be delivered to an aircraft use.

8. The environmental control system as set forth in claim 7, wherein a valve is on said first passage associated with said lower pressure tap.

9. The environmental control system as set forth in claim 8, wherein said valve is a check valve.

10. The environmental control system as set forth in claim 8, wherein a control valve is positioned on said higher pressure tap, and may be closed to drive air through said first passage associated with said lower pressure tap when closed, or to have air pass through said compressor section of said turbocompressor when said control valve is opened.

11. The environmental control system as set forth in claim 10, wherein a redundant valve is provided to be closed if said control valve associated with said higher pressure tap fails.

12. The environmental control system as set forth in claim 11, wherein said redundant valve is positioned to be downstream of a location at which said first passage and said combined outlet intermix into a common conduit.

13. An environmental control system for an aircraft comprising:

a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft, and a lower pressure tap to be associated with a lower pressure location said lower pressure location being at a lower pressure than said higher pressure location;

said lower pressure tap communicating to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor;

said higher pressure tap leading into a turbine section of said turbocompressor such that air in said higher pressure tap drives said turbine section to in turn drive said compressor section of said turbocompressor;

a combined outlet of said compressor section of said turbocompressor and said turbine section intermixing and passing downstream to be delivered to an aircraft use;

a check valve on said first passage associated with said lower pressure tap;

a control valve positioned on said higher pressure tap may be closed to drive air through said first passage associated with said lower pressure tap, or to have air pass through said compressor section of said turbocompressor when said control valve is opened; and

a redundant valve provided to be closed if said control valve associated with said higher pressure tap fails, said redundant valve positioned to be downstream of a location at which said first passage and said combined outlet intermix into a common conduit.