# US 10,119,468 B2 · Customer bleed air pressure loss reduction

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- Number: US 10,119,468 B2
- Document ID: US10119468B2
- Status: Granted
- Kind: B2
- Application number: 13/366,597
- Filed: 2012-02-06
- Published: 2013-08-08
- Granted: 2018-11-06
- Earliest claimed: 2012-02-06
- Assignees: United Technologies Corporation
- Applicants: Cheng-Zhang Wang; Thomas G. Phillips; David F. Cloud; Peter M. Munsell
- Inventors: Cheng-Zhang Wang; Thomas G. Phillips; David F. Cloud; Peter M. Munsell
- Web page: https://patentgrep.com/patent/US10119468B2

## CPC

- F02C 6/08: the gas being bled from the gas-turbine compressor
- F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings}
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas}
- F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)}
- F05D 2260/601: using an ejector or a jet pump
- F05D 2270/17: to control boundary layer
- F05D 2270/301: Pressure
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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.

## Claims

### Claim 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.

### Claim 2 (depends on 1)

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

### Claim 3 (depends on 1)

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.

### Claim 4 (depends on 3)

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

### Claim 5 (depends on 1)

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.

### Claim 6 (depends on 5)

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.

### Claim 7 (depends on 1)

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.

### Claim 8 (depends on 7)

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.

### Claim 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.

### Claim 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.