Flow control structures for turbomachines and methods of designing the same

• US 9,845,810 B2
• Filed: 06/24/2015
• Issued: 12/19/2017
• Est. Priority Date: 06/24/2014
• 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): Beebe, Joshua R
• Application Number:
  US14/749,467
• Publication Number:
  US 20150369073A1
• Time in Patent Office: 909 Days
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 5/048 Form or construction
• CPC Class Codes: F01D 5/12 Blades specially adapted for radial flow machines or engines F01D5/04; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F01D 9/045 for radial flow machines or engines
• CPC Class Codes: F01D 9/048 for radial admission
• CPC Class Codes: F01D 9/06 Fluid supply conduits to nozzles or the like
• 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 29/284 for compressors
• CPC Class Codes: F04D 29/4206 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/426 especially adapted for liquid pumps
• CPC Class Codes: F04D 29/441 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/444 Bladed diffusers
• CPC Class Codes: F04D 29/448 bladed diffusers
• CPC Class Codes: F04D 29/526 Details of the casing section radially opposing blade tips ducts F04D29/545
• CPC Class Codes: F04D 29/664 by means of sound absorbing material
• CPC Class Codes: F04D 29/685 Inducing localised fluid recirculation in the stator-rotor interface
• CPC Class Codes: F04D 31/00 Pumping liquids and elastic fluids at the same time
• 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 2250/182 : crenellated, notched
• CPC Class Codes: F05D 2250/294 : grooved
• CPC Class Codes: F05D 2250/52 : Outlet
• CPC Class Codes: G06F 17/10 : Complex mathematical operations function generation by table look-up G06F1/03; evaluation of elementary functions by calculation G06F7/544
• CPC Class Codes: G06F 2113/08 : Fluids
• CPC Class Codes: G06F 30/15 : Vehicle, aircraft or watercraft design
• CPC Class Codes: G06F 30/17 : Mechanical parametric or variational design
• CPC Class Codes: G06F 30/28 : using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]

Abstract

Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.

Claims

1. A turbomachine, comprising:

a downstream element having an inlet, a shroud side and a hub side;

an impeller comprising a hub and a plurality of blades and having an inlet, an exit, and an axis of rotation, each of said plurality of blades having a leading edge and a trailing edge and extending in a spanwise direction from said hub to a shroud side of said blade;

a shroud having a face confronting said shroud sides of said plurality of blades, said shroud and said hub defining an impeller passageway;

said impeller designed and configured to;

discharge a working fluid into said downstream element; and

generate a flow field in said working fluid at said exit including a weak side proximate one of said hub and said shroud and a strong side proximate the other one of said hub and said shroud, wherein a meridional component of an absolute velocity of the flow field is greater on the strong side than the weak side; and

at least one channel extending in a flow-wise direction along a portion of at least one of said shroud side and said hub side of said downstream element at a location downstream of said inlet of said downstream element, said at least one channel having a centerline that has a tangent line extending at an angle, α

, as measured in an absolute frame of reference from a meridional reference plane extending through said axis of rotation, said at least one channel selectively located adjacent the weak side of the flow field and being designed and configured to guide a portion of said weak side of said flow field in a direction that is substantially the same as α

;

wherein said downstream element includes a row of blades having leading edges located proximate said inlet of said downstream element, wherein a portion of said at least one channel is located downstream of said leading edges of said row of blades of said downstream element;

wherein said at least one channel has a beginning location located upstream of said trailing edges of said impeller blades.

2. A turbomachine according to claim 1, wherein said beginning location of said at least one channel is located substantially at said inlet of said impeller.

3. A turbomachine according to claim 2, wherein said at least one channel is designed, configured, and dimensioned for two-phase flow.

4. A turbomachine according to claim 1, wherein the weak side of the flow field includes a divergence region where a flow angle of a first portion of stream tubes in said flow field begins to diverge from a flow angle of other stream tubes in said flow field, wherein a beginning of said at least one channel is located at a meridional location that is adjacent or upstream of said divergence region.

5. A turbomachine according to claim 4, wherein the turbomachine has an operating range and wherein said divergence region has a meridional location that varies across the operating range between a maximum upstream location and maximum downstream location, and wherein said beginning of said at least one channel is located at a meridional location that is adjacent or upstream of said maximum upstream location.

6. A turbomachine according to claim 4, wherein said beginning of said at least one channel is located at a meridional location in said divergence region.

7. A turbomachine according to claim 1, wherein said impeller has a meridional length, said at least one channel having an ending location located downstream of said leading edges of said row of blades of said downstream element by a distance of at least 10% of said meridional length.

8. A turbomachine according to claim 1, wherein said impeller has a meridional length, said at least one channel having an ending location located downstream of said leading edges of said row of blades of said downstream element by a distance of at least 3% of said meridional length.

9. A turbomachine according to claim 1, wherein said at least one channel is a plurality of channels each having a maximum width and spaced circumferentially about said inlet of said downstream element, said turbomachine further including a plurality of lands each having a maximum width and extending between said plurality of channels.

10. A turbomachine according to claim 9, wherein said maximum width of said plurality of channels is greater than said maximum width of said plurality of lands.

11. A turbomachine according to claim 10, wherein said maximum width of each of said plurality of channels is at least two times greater than said maximum width of said plurality of lands, said plurality lands being configured as flow-guiding ribs.

12. A turbomachine according to claim 9, wherein said maximum width of said plurality of lands is greater than said maximum width of said channels.

13. A turbomachine according to claim 1, wherein said at least one channel includes a first portion located upstream of said trailing edges, said first portion having a substantially constant width.

14. A turbomachine according to claim 13, wherein said at least one channel has a second portion located downstream of said inlet of said downstream element, said second portion having a varying width.

15. A turbomachine according to claim 1, wherein said at least one channel has a beginning location and a width, wherein said width of said at least one channel varies and said channel converges to a point at said beginning location.

16. A turbomachine according to claim 1, wherein said at least one channel has a depth that varies along a length of said channel, said channel having a maximum depth at a location adjacent or downstream of said trailing edges.

17. A turbomachine according to claim 16, wherein said maximum depth is located in said downstream element.

18. A turbomachine according to claim 1, wherein α

is substantially constant across an entire length of said channel.

19. A turbomachine according to claim 1, wherein α

varies across a length of said channel.

20. A turbomachine according to claim 19, wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having an average absolute angle, α

_p, wherein α

_p varies over a first portion of said impeller passageway and approaches an exit angle in an exit portion of said impeller passageway, wherein an upstream portion of said at least one channel is located in said first portion and a downstream portion of said at least one channel is located in said exit portion, wherein said α

of said upstream portion is equal to a first value, and a of said downstream portion is equal to a second value that is different than said first value.

21. A turbomachine according to claim 1, wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having an average absolute angle, α

_p, that approaches a nominal exit angle in an exit portion of said impeller passageway, wherein said α

of a portion of said at least one channel adjacent said impeller exit is substantially the same as said nominal exit angle.

22. A turbomachine according to claim 1, wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having an average absolute angle, α

_p, that approaches a nominal exit angle in an exit portion of said impeller passageway, wherein said at least one channel is designed and configured to guide a portion of said secondary flow portion towards an angle that is substantially the same as α

_p.

23. A turbomachine according to claim 1, wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having an average absolute angle, α

_p, that is equal to an inlet angle at said impeller inlet and approaches a nominal exit angle in an exit portion of said impeller passageway, wherein said α

of a portion of said at least one channel adjacent said impeller exit has a value between said inlet angle and said nominal exit angle.

24. A turbomachine according to claim 1, wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having an average absolute angle, α

_p, that is equal to an inlet angle at said impeller inlet and that approaches a nominal exit angle in an exit portion of said impeller passageway, wherein said at least one channel is designed and configured to guide a portion of said secondary flow portion at an angle that is between said inlet angle and said nominal exit angle.

25. A turbomachine according to claim 1, wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having an average absolute angle α

_p, wherein α

is substantially the same as α

_p.

26. A turbomachine according to claim 1, wherein said at least one channel includes a submerged fluid passageway and at least one opening for providing fluid communication between said impeller passageway and said submerged fluid passageway.

27. A turbomachine according to claim 26, wherein said at least one opening includes a plurality of fluid openings located along said impeller passageway.

28. A turbomachine according to claim 1, wherein said at least one channel is a plurality of channels, at least one of said plurality of channels being located in said shroud side of said downstream element and at least one of said plurality of channels being located in said hub side of said downstream element.

29. A turbomachine according to claim 1, wherein said at least one channel is located in said shroud side of said downstream element.

30. A turbomachine according to claim 1, wherein said at least one channel is a plurality of channels, at least one of said plurality of channels being located in said hub side of said downstream element.

31. A turbomachine according to claim 30, wherein said trailing edges are located downstream of a downstream-most extent of said hub, a beginning location of said at least one channel being adjacent said downstream most extent and upstream of said trailing edges.

32. A turbomachine according to claim 30, wherein said hub overlaps a portion of said hub side of said downstream element, said hub including at least one access opening extending through a width of said hub and providing fluid communication between said impeller passageway and said at least one channel.

33. A turbomachine according to claim 1, wherein said row of blades vaned passageways therebetween, said at least one channel includes a plurality of channels, each of which are substantially aligned with one of said vaned passageway.

34. A turbomachine according to claim 1, wherein said row of blades define a plurality of vaned passageways therebetween, said at least one channel includes a plurality of channels, said plurality of channels being clocked from said plurality of vaned passageways such that said centerlines of said channels are circumferentially offset from centerlines of said vaned passageways.

35. A turbomachine according to claim 1, wherein said downstream element is a diffuser, said shroud side and said hub side of said downstream element defining a diffuser passageway having a width, wherein said diffuser includes at least one strong-side pinch region providing a decrease in said diffuser passageway width that includes a convex surface on the one of said shroud side and said hub side adjacent said strong side of said flow field, said convex surface providing a passage width reduction that is greater than a passage width reduction on the other one of said shroud side and said hub side.

36. A turbomachine according to claim 1, wherein said at least one channel is designed and configured to increase the meridional component of the weak side absolute velocity.

37. A turbomachine according to claim 1, wherein said impeller is a centrifugal impeller.

38. A turbomachine according to claim 1, wherein said at least one channel is formed in at least one of said shroud side and said hub side of said downstream element.

39. A turbomachine according to claim 1, wherein said flow field has a flow-wise average absolute angle distribution, further wherein said angle, α

, of said least one channel has a flow-wise angle distribution that is substantially the same as said flow field flow-wise average absolute angle distribution.

40. A turbomachine according to claim 1,

wherein said flow field includes a primary flow portion and a secondary flow portion, said primary flow portion having a meridional average absolute angle distribution α

_p(% M);

wherein said angle, α

, of said least one channel has a meridional angle distribution α

(% M), α

(% M) being substantially the same as α

_p(% M).

41. A turbomachine, comprising:

a downstream element having a plurality of blades having leading edges, a shroud side and a hub side;

an impeller comprising a plurality of blades; and

at least one stationary channel extending in a flow-wise direction and formed in at least one of said shroud side and said hub side of said downstream element, at least a portion of said at least one channel is located downstream of said leading edges of said plurality of blades of said downstream element;

wherein said at least one channel has a beginning location located upstream of said trailing edges of said impeller blades.

42. A turbomachine according to claim 41, wherein said impeller has a meridional length (M) from an inlet to an exit of the impeller, said at least one channel has a flow-wise curvature that is substantially the same as a flow-wise angle profile of a flow field generated by the impeller across an exit region of the impeller, the exit region extending across at least approximately 10% M of said impeller.

43. A turbomachine according to claim 42, wherein said flow-wise angle profile is an average absolute angle profile of a primary flow portion of the flow field.

44. A turbomachine according to claim 41, wherein said impeller blades have trailing edges, a portion of said at least one stationary channel being located upstream of said trailing edges.

45. A turbomachine according to claim 42, wherein said flow-wise angle profile is an average absolute angle profile of the flow field.

46. A turbomachine, comprising:

an impeller having a plurality of blades having trailing edges;

a shroud having a face confronting said plurality of blades;

a downstream element having an inlet;

wherein the downstream element is a diffuser; and

at least one stationary channel extending in a flow-wise direction and formed in said shroud;

wherein said at least one channel has a flow-wise curvature that is designed and configured to be substantially the same as a flow-wise angle profile of a flow field generated by the impeller over a flow-wise distance extending from a location upstream of the impeller blade trailing edge to a location downstream of the downstream element inlet;

wherein said impeller has a meridional length (M) from an inlet to an exit of the impeller, wherein the location upstream of the impeller blade trailing edges is at least 10% M upstream of the trailing edges.

47. A turbomachine according to claim 46, wherein the location upstream of the impeller blade trailing edges is at least 30% M upstream of the trailing edges.