Structures and methods for forcing coupling of flow fields of adjacent bladed elements of turbomachines, and turbomachines incorporating the same

• US 9,551,225 B2
• Filed: 04/07/2016
• Issued: 01/24/2017
• Est. Priority Date: 01/23/2013
• Status: Active Grant

• Current Assignee: Concepts NREC, LLC
• Original Assignee: Concepts NREC, LLC
• Inventors: Japikse, David
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): BROWN, ADAM WAYNE
• Application Number:
  US15/093,266
• Publication Number:
  US 20160222789A1
• Time in Patent Office: 292 Days
• US Class Current: 1/1
• CPC Class Codes: B23P 15/006 turbine wheels
• CPC Class Codes: F01D 25/06 for preventing blade vibration means on blade-carrying members or blades F01D5/00
• CPC Class Codes: F01D 5/142 of the blades of successive rotor or stator blade-rows
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/045 for radial flow machines or engines
• CPC Class Codes: F04D 1/00 Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps adapted for pumping specific fluids F04D7/00; priming or boosting F04D9/00
• CPC Class Codes: F04D 17/10 for compressing or evacuating
• CPC Class Codes: F04D 29/162 of a centrifugal flow wheel
• CPC Class Codes: F04D 29/167 of a centrifugal flow wheel
• CPC Class Codes: F04D 29/245 for special effects
• CPC Class Codes: F04D 29/281 for fans or blowers
• CPC Class Codes: F04D 29/284 for compressors
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/325 for axial flow fans blade mountings F04D29/34, blades F04D29/38
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: F04D 29/444 Bladed diffusers
• CPC Class Codes: F04D 29/448 bladed diffusers
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F04D 29/544 : Blade shapes
• CPC Class Codes: F04D 29/666 : by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
• CPC Class Codes: F04D 29/685 : Inducing localised fluid recirculation in the stator-rotor interface
• CPC Class Codes: F05D 2240/121 : related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/126 : Baffles or ribs
• CPC Class Codes: F05D 2240/303 : related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2250/52 : Outlet
• CPC Class Codes: Y10T 29/49229 : Prime mover or fluid pump making

Abstract

Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.

Claims

1. A turbomachine, comprising:

an impeller rotatably disposed adjacent a shroud having a shroud surface, said impeller having a plurality of impeller blades, each of said impeller blades having;

a shroud edge adjacent said shroud surface; and

a trailing edge; and

a diffuser located downstream of said impeller, said diffuser forming at least one diffuser passageway;

wherein said shroud surface includes a plurality of elongate recesses located in said shroud surface and extending downstream along said shroud surface and into said diffuser, said recesses configured to guide a portion of a working fluid in said turbomachine.

2. A turbomachine according to claim 1, wherein said elongate recesses are selected from the group consisting of troughs and channels.

3. A turbomachine according to claim 1, wherein said elongate recesses extend along a curved trajectory.

4. A turbomachine according to claim 1, further comprising raised ribs formed on said shroud surface adjacent said shroud edges of said plurality of impeller blades, wherein said elongate recesses extend between said ribs.

5. A turbomachine according to claim 4, wherein said ribs overlap said trailing edges of said plurality of impeller blades and extend into said diffuser passageway.

6. A turbomachine according to claim 5, wherein said recesses overlap said trailing edges of said plurality of impeller blades and extend into said diffuser passageway.

7. A turbomachine according to claim 1, wherein said diffuser further includes a plurality of diffuser blades having leading edges, said turbomachine further comprising a plurality of raised ribs formed on said shroud surface, wherein at least one of said ribs extends upstream from one of said leading edges of said diffuser blades and overlaps said trailing edges of said plurality of impeller blades.

8. A turbomachine according to claim 7, wherein said diffuser blades have trailing edges, said diffuser further including at least one raised rib extending downstream of said trailing edges of said diffuser blades.

9. A turbomachine according to claim 8, wherein said at least one raised rib extending downstream of said diffuser blades extends from one of said diffuser blade trailing edges.

10. A turbomachine according to claim 7, wherein said diffuser blades are arranged into a low solidity blade row.

11. A turbomachine according to claim 10, wherein said diffuser further includes at least one tandem vane located downstream of said low solidity blade row.

12. A turbomachine according to claim 1, wherein said at least one diffuser passageway has an entrance with a first height and an exit with a second height, said at least one diffuser passageway being tapered, wherein said first height is not equal to said second height.

13. A turbomachine according to claim 12, wherein said first height is greater than said second height.

14. A turbomachine, comprising:

a first bladed element having a shroud surface and a plurality of first blades with trailing edges;

a second bladed element; and

at least one channel located in said shroud surface, a portion of said at least one channel proximate said trailing edges, said at least one channel being designed and configured to guide flow in said first bladed element into said second bladed element, wherein said at least one channel is located upstream of said trailing edges and extends downstream into said second bladed element.

15. A turbomachine according to claim 14, wherein said at least one channel includes a plurality of channels in the shroud surface of the first bladed element.

16. A turbomachine according to claim 15, wherein said second bladed element includes a plurality of second blades defining diffuser passageways extending between adjacent ones of said second blades, wherein said plurality of channels are aligned with said diffuser passageways so that said channels guide flow in the first bladed element into the diffuser passageways.

17. A turbomachine according to claim 15, wherein said second bladed element includes a plurality of second blades having leading edges, at least one of said leading edges of said second bladed element having a contoured surface having at least one leg, wherein said at least one leg extends upstream of the trailing edges and between ones of the plurality of channels.