Customer bleed air pressure loss reduction

Patent metadata

Field	Value
Publication number	US-10119468-B2
Application number	US-201213366597-A
Country	US
Kind code	B2
Filing date	Feb 6, 2012
Priority date	Feb 6, 2012
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

Abstract

A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a compressor delivering air into a combustion section having a combustor, and said combustion section and said compressor being housed in a housing, an air supply system communicating through said housing to deliver air from a location between an upstream end of said compressor, and an upstream end of said combustor;
said air supply system having a duct with an inlet end and extending to an outlet end, said duct being provided with a central insert at an upstream end, said insert ending within said duct upstream of said outlet end;
said central insert providing a venturi effect by reducing a cross-sectional flow area between the insert and an inner wall of the duct at the upstream end, and said insert and duct providing increased cross-sectional flow areas at downstream locations;
a plurality of insert holders center said insert within said duct;
a diffuser is positioned downstream of said compressor, an opening in said housing supplying air to said inlet end, and said diffuser having an outer shroud and an inner shroud with intermediate vanes, and said outer shroud ending at a location upstream of a downstream end of said inner shroud at locations circumferentially aligned with said inlet end; and
said outer shroud only ends at the upstream location at circumferential locations associated with said inlet end, but extends further downstream at other locations.

2. The engine as set forth in claim 1 , wherein said insert has rounded axial ends.

3. The engine as set forth in claim 1 , wherein said duct includes a plurality of ducts, each of said ducts having inlet ends at locations spaced by at least 90° about a cross-sectional center axis of the gas turbine engine.

4. The engine as set forth in claim 3 , wherein said inlet ends are spaced by 180°.

5. The engine as set forth in claim 1 , wherein a flow path through said opening, and into said inlet end of said duct has at least a portion formed with a part-circular radius.

6. The engine as set forth in claim 5 , wherein said opening in said housing leads into said inlet end of said duct, with said inlet end ending downstream of said opening in said housing, with said part-circular radius portion formed in said housing.

7. The engine as set forth in claim 1 , wherein said opening is formed through said housing and into said inlet end of said duct wherein a flow path through said opening, and into said inlet end of said duct has at least a portion formed with a part-circular radius.

8. The engine as set forth in claim 7 , wherein said opening in said housing leads into said inlet end of said duct, with said inlet end ending downstream of said opening in said housing, with said part-circular radius portion formed in said housing.

9. A gas turbine engine comprising:
a compressor delivering air into a combustion section having a combustor, and said combustion section and said compressor being housed in a housing, an air supply system communicating through said housing to deliver air from a location between an upstream end of said compressor, and an upstream end of said combustor;
said air supply system having a duct with a duct inlet end and extending to an outlet end, said duct being provided with a central insert at an upstream end, said central insert providing a venturi effect by reducing the cross-sectional flow between the insert and an inner wall of the duct at the upstream end, and said insert and duct providing increased cross-sectional flow areas at downstream locations, said insert ending within said duct upstream of said outlet end;
said air supply system includes a plurality of said ducts, each of said ducts being provided with an insert, and said ducts inlet ends at locations spaced by at least 90° about a cross-sectional center axis of the gas turbine engine;
a diffuser positioned downstream of said compressor, an opening in said housing supplying air to said duct inlet ends, and said diffuser having an outer shroud and an inner shroud with intermediate vanes, and said outer shroud ending at a location upstream of a downstream end of said inner shroud at locations circumferentially aligned with said duct inlet end, said outer shroud only ends at the upstream location at circumferential locations associated with said duct inlet end, but extends further downstream at other locations; and
a flow path through said opening, and into said inlet end of said duct has at least a portion formed with a part-circular radius.

10. A gas turbine engine comprising:
a compressor delivering air into a combustion section having a combustor, and said combustion section and said compressor being housed in a housing, an air supply system communicating through said housing to deliver air from a location between an upstream end of said compressor, and an upstream end of said combustor;
said air supply system having a duct with an inlet end;
a diffuser positioned downstream of said compressor, and said diffuser having an outer shroud and an inner shroud with intermediate vanes, and said outer shroud ending at a location upstream of the downstream end of said inner shroud at locations circumferentially aligned with said inlet end; and
said outer shroud only ends at the upstream location at circumferential locations associated with said inlet ends, but extends further downstream at other locations.

Assignees

• Wang Cheng Zhang
• Phillips Thomas G
• Cloud David F
• Munsell Peter M
• United Technologies Corp

Inventors

• Wang Cheng-Zhang
• Phillips Thomas G
• Cloud David F
• Munsell Peter M

Classifications

• F05D2270/17

  to control boundary layer · CPC title

• F05D2270/301

  Pressure · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02C6/08 Primary

  the gas being bled from the gas-turbine compressor · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title