Customer bleed air pressure loss reduction
AssigneeUnited Technologies Corporation
InventorsCheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
Life of this patent
Estimating the term…
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.
Claims22
A bleed air supply system for a gas turbine engine comprising:
- a duct having an inlet end and extending to an outlet end, an inlet end of said duct being provided with a central insert at an upstream end;
- and
- said insert ending within said duct upstream of said outlet end.
A gas turbine engine comprising:
- a compressor delivering air into a combustion section, 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;
- and
- 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.
A gas turbine engine comprising:
- a compressor delivering air into a combustion section, 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 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 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, said outer shroud only ends at the upstream location at circumferential locations associated with said 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.
A gas turbine engine comprising:
- a compressor delivering air into a combustion section, 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 plurality of ducts to move air towards a use;
- and
- said ducts having inlet ends at locations spaced by at least 90° about a cross-sectional center axis of the gas turbine engine.
A gas turbine engine comprising:
- a compressor delivering air into a combustion section, 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
- 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.
Dependencies are inferred from the claim text.