Centrifugal compressor with bleed flow splitter for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-8935926-B2
Application number	US-91494710-A
Country	US
Kind code	B2
Filing date	Oct 28, 2010
Priority date	Oct 28, 2010
Publication date	Jan 20, 2015
Grant date	Jan 20, 2015

Abstract

An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.

First claim

What is claimed is:

1. An impeller comprising:
a hub defined about an axis of rotation; and
a plurality of vanes formed around said hub, each of said plurality of vanes defines an offset between a leading edge and a trailing edge,
wherein said offset defines a stepped surface on an axially forward face of said hub, said hub defines a bleed passage including an inlet port located on said stepped surface that extends to an exit port on an axially aft surface of said hub, said exit port located radially outward from said inlet port, and said bleed passage is configured to direct all of a fluid entering said inlet port through said exit port.

2. The impeller as recited in claim 1 , wherein said leading edge defines an axial intake and said trailing edge defines a radial exit.

3. The impeller as recited in claim 1 , wherein said exit port is fluidly connected to an inlet port of said bleed passage with a curved section, said inlet port to said bleed passage includes a first cross-sectional area and said exit port includes a second cross-sectional area, said second cross-sectional area being greater than said first cross-sectional area.

4. A centrifugal compressor assembly comprising:
an impeller with a plurality of vanes formed around a hub which defines an axis of rotation, each of said plurality of vanes defines an offset between a leading edge and a trailing edge, said offset defines a stepped surface on said axially forward face of said hub, said leading edge defines an axial intake and said trailing edge defines a radial exit,
wherein said hub defines a bleed passage including an inlet port located on said stepped surface that extends to an exit port on an axially aft surface of said hub, said exit port located radially outward from said inlet port, and said bleed passage is configured to direct all of a fluid entering said inlet port through said exit port.

5. The centrifugal compressor assembly as recited in claim 4 , wherein said bleed passage splits off from a flow path between said axial intake and said radial exit.

6. A method of providing a bleed flow from a centrifugal compressor comprising:
interfacing a bleed passage with an offset in a plurality of impeller vanes,
wherein said offset is located on an axial aft surface of each of said plurality of vanes adjacent a hub and defines a stepped surface on said axially forward face of said hub, said hub defines a bleed passage including an inlet port located on said stepped surface that extends to an exit port on an axially aft surface of said hub, the exit port located radially outward from the inlet port, and said bleed passage is configured to direct all of a fluid entering said inlet port through said exit port.

Assignees

• Wagner Joel H
• Magge Shankar S
• Santeler Keith A
• United Technologies Corp

Inventors

• Wagner Joel H
• Magge Shankar S
• Santeler Keith A

Classifications

• F04D29/284

  for compressors · CPC title

• F04D29/4246

  comprising more than one outlet · CPC title

• F02C3/08

  the compressor comprising at least one radial stage (F02C3/10 takes precedence) · CPC title

• F02C6/08 Primary

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

• F04D29/286

  multi-stage rotors · CPC title