Radial vaned diffusion system with integral service routings

• US 20080056892A1
• Filed: 08/29/2006
• Published: 03/06/2008
• Est. Priority Date: 08/29/2006
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Barton, Michael T., Kington, Harry L., Palmer, Donald L.
• Granted Patent: US 7,717,672 B2
• Time in Patent Office: Days
• US Class Current: 415/191
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: 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
• CPC Class Codes: F04D 29/444 Bladed diffusers
• CPC Class Codes: F04D 29/624 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/644 especially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2250/52 Outlet
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A radial diffuser comprises a housing, a plurality of diffuser vanes, and a plurality of integral service vanes. The housing includes an air inlet and an air outlet, and defines a radial section extending radially outward from the air inlet, an axial section extending axially to the air outlet, and a transition including a bend and extending between the radial and axial sections. The diffuser vanes are coupled to the housing, and are disposed in, and define diffusion flow passages. The integral service vanes are coupled to the housing, extend around the bend, and define transition flow passages, each in fluid communication with at least one diffusion flow passage. At least some of the integral service vanes include a service passage extending therethrough and configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.

Claims

1. A radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising:

a housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition between the air inlet and air outlet, the radial section extending at least substantially radially outward from the air inlet to the transition, the axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section;

a plurality of diffuser vanes coupled to the housing and disposed in the radial section, the plurality of diffuser vanes defining a plurality of diffusion flow passages through the radial section; and

a plurality of integral service vanes coupled to the housing and extending around the bend in the transition, the plurality of integral service vanes defining a plurality of transition flow passages through the transition, each transition flow passage in fluid communication with at least one diffusion flow passage, at least a portion of the integral service vanes including a service passage extending therethrough, each service passage configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.

2. The radial diffuser of claim 1, wherein:

the bend provides an at least substantially continuous turn between the radial section and the axial section.

3. The radial diffuser of claim 1, wherein:

the plurality of integral service vanes have an average thickness that is greater than the average thickness of the plurality of diffuser vanes.

4. The radial diffuser of claim 1, wherein:

the number of integral service vanes is equal to the number of diffuser vanes.

5. The radial diffuser of claim 1, wherein:

each integral service vane is connected to a corresponding diffuser vane.

6. The radial diffuser of claim 1, wherein:

the plurality of diffuser vanes are made at least in part from a first material;

the plurality of integral service vanes are made at least in part from a second material; and

the second material is lighter than the first material.

7. The radial diffuser of claim 6, wherein:

the first material is steel.

8. The radial diffuser of claim 6, wherein:

the second material is selected from the group consisting of titanium, aluminum, and plastic.

9. The radial diffuser of claim 1, further comprising:

one or more splitter vanes disposed in the transition and configured to deswirl the diffused air.

10. The radial diffuser of claim 1, further comprising:

a plurality of post-transition vanes disposed in the axial section and configured to at least partially deswirl the diffused air.

11. The radial diffuser of claim 1, further comprising:

one or more service conduits extending through one or more of the service passages.

12. The radial diffuser of claim 11, wherein:

the one or more service conduits are made of metal tubing.

13. The radial diffuser of claim 1, wherein:

one or more of the service passages are further configured to allow a structural tie with one or more external structures.

14. A compressor comprising:

a compressor housing;

an impeller rotationally mounted within the compressor housing and having a leading edge and a trailing edge, the impeller operable, upon rotation thereof, to discharge a flow of air having a velocity magnitude and a pressure magnitude from the trailing edge; and

a radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising;

a diffuser housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition between the air inlet and air outlet, the air inlet in fluid communication with the impeller trailing edge to thereby receive the flow of air discharged therefrom, the radial section extending at least substantially radially outward from the air inlet to the transition, the axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section;

a plurality of diffuser vanes coupled to the diffuser housing and disposed in the radial section, the plurality of diffuser vanes defining a plurality of diffusion flow passages through the radial section; and

a plurality of integral service vanes coupled to the diffuser housing and extending around the bend in the transition, the plurality of integral service vanes defining a plurality of transition flow passages through the transition, each transition flow passage in fluid communication with at least one diffusion flow passage, at least a portion of the integral service vanes including a service passage extending therethrough, each service passage configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.

15. The compressor of claim 14, wherein:

the plurality of integral service vanes have an average thickness that is greater than the average thickness of the plurality of diffuser vanes.

16. The compressor of claim 14, wherein:

the plurality of diffuser vanes are made at least in part from a first material;

the plurality of integral service vanes are made at least in part from a second material; and

the second material is lighter than the first material.

17. The compressor of claim 14, further comprising:

one or more splitter vanes disposed in the transition and configured to deswirl the diffused air.

18. A gas turbine engine, comprising:

an engine housing;

a compressor, a combustor, and a turbine all mounted in flow series within the housing, the compressor including at least;

a compressor housing;

an impeller rotationally mounted within the compressor housing and having a leading edge and a trailing edge, the impeller operable, upon rotation thereof, to discharge a flow of air having a velocity magnitude and a pressure magnitude from the trailing edge; and

a radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising;

a diffuser housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition between the air inlet and air outlet, the air inlet in fluid communication with the impeller trailing edge to thereby receive the flow of air discharged therefrom, the radial section extending at least substantially radially outward from the air inlet to the transition, the axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section;

a plurality of diffuser vanes coupled to the diffuser housing and disposed in the radial section, the plurality of diffuser vanes defining a plurality of diffusion flow passages through the radial section; and

a plurality of integral service vanes coupled to the diffuser housing and extending around the bend in the transition, the plurality of integral service vanes defining a plurality of transition flow passages through the transition, each transition flow passage in fluid communication with at least one diffusion flow passage, at least a portion of the integral service vanes including a service passage extending therethrough, each service passage configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.

19. The gas turbine engine of claim 18, wherein:

the plurality of integral service vanes have an average thickness that is greater than the average thickness of the plurality of diffuser vanes.

20. The gas turbine engine of claim 18, wherein:

the plurality of diffuser vanes are made at least in part from a first material;

the plurality of integral service vanes are made at least in part from a second material; and

the second material is lighter than the first material.

21. The gas turbine engine of claim 18, further comprising:

one or more splitter vanes disposed in the transition and configured to deswirl the diffused air.