NON-UNIFORM VARIABLE VANES

• US 20130094942A1
• Filed: 10/12/2011
• Published: 04/18/2013
• Est. Priority Date: 10/12/2011
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Manwaring, Steven Roy, MacKay, Raymond Angus
• Application Number:
  US13/271,617
• Publication Number:
  US 20130094942A1
• Time in Patent Office: Days
• US Class Current: 415/148
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49321 Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Abstract

Non-uniform variable stator vanes for a single stage of a gas turbine engine stage include non-uniform airfoils with a non-uniformity between airfoils of first and second portions of the stator vanes. The variable stator vanes may further include all outer buttons, from which the airfoils inwardly extend, in all of the variable stator vanes being equally sized and shaped and the same all inner buttons if used. The airfoils in the first and second portions may be counter-clockwise and clockwise biased respectively with respect to a nominal airfoil position. The airfoils in the first and second portions may be counter-clockwise and clockwise leaned respectively with respect to the nominal airfoil position. Outer ends of the airfoils in the first and second portions may be counter-clockwise and clockwise shifted respectively with respect to the nominal airfoil position.

Claims

1. A plurality of same stage variable stator vanes comprising:

non-uniform same stage variable stator vanes having non-uniform airfoils;

at least first and second portions of the plurality of non-uniform same stage variable stator vanes;

each of the variable stator vanes having a rotational axis;

each of the airfoils extending inwardly from an outer button centered about a rotational axis; and

a non-uniformity between airfoils of the variable stator vanes of the first portions and airfoils of the variable stator vanes of the second portion.

2. The plurality of same stage variable stator vanes as claimed in claim 1 further comprising all of the outer buttons in all of the variable stator vanes being equally sized and shaped.

3. The plurality of same stage variable stator vanes as claimed in claim 1 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise biased with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise biased with respect to the nominal airfoil position.

4. The plurality of same stage variable stator vanes as claimed in claim 1 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise leaned with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise leaned with respect to the nominal airfoil position.

5. The plurality of same stage variable stator vanes as claimed in claim 4 wherein the airfoils in the first and second portions are counter-clockwise and clockwise leaned about inner ends of the airfoils respectively and each of the inner ends equally positioned with respect to the rotational axis of each respective vane.

6. The plurality of same stage variable stator vanes as claimed in claim 1 further comprising:

the airfoils extending between airfoil outer and inner ends of the airfoils,

the non-uniformity including the outer ends of the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise shifted with respect to a nominal airfoil position, and

the outer ends of the airfoils in the second portion of the plurality of variable stator vanes being clockwise shifted with respect to the nominal airfoil position.

7. The plurality of same stage variable stator vanes as claimed in claim 1 further comprising each of the airfoils disposed between the outer button and a spaced apart inner button and an inner spindle extending inwardly from the inner button.

8. The plurality of same stage variable stator vanes as claimed in claim 7 further comprising all of the outer buttons in all of the variable stator vanes being equally sized and shaped and all of the inner buttons in all of the variable stator vanes being equally sized and shaped.

9. The plurality of same stage variable stator vanes as claimed in claim 7 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise biased with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise biased with respect to the nominal airfoil position.

10. The plurality of same stage variable stator vanes as claimed in claim 9 further comprising all of the outer buttons in all of the variable stator vanes being equally sized and shaped and all of the inner buttons in all of the variable stator vanes being equally sized and shaped.

11. The plurality of same stage variable stator vanes as claimed in claim 7 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise leaned with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise leaned with respect to the nominal airfoil position.

12. The plurality of same stage variable stator vanes as claimed in claim 11 wherein the airfoils in the first and second portions are counter-clockwise and clockwise leaned about inner ends of the airfoils respectively and each of the inner ends equally positioned with respect to the rotational axis of each respective vane.

13. The plurality of same stage variable stator vanes as claimed in claim 7 further comprising:

the airfoils extending between airfoil outer and inner ends of the airfoils,

the non-uniformity including the outer ends of the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise shifted with respect to a nominal airfoil position, and

the outer ends of the airfoils in the second portion of the plurality of variable stator vanes being clockwise shifted with respect to the nominal airfoil position.

14. A gas turbine engine assembly comprising:

a gas turbine engine casing radially outwardly supporting a variable vane assembly including at least one circular row of non-uniform same stage variable stator vanes having non-uniform airfoils;

each of the variable stator vanes having a rotational axis;

each of the airfoils extending inwardly from an outer button centered about a rotational axis;

each of the variable stator vanes including an outer spindle extending outwardly from the outer button;

the outer spindles rotatably disposed through outer trunnions mounted in outer openings in the casing;

at least first and second portions of the plurality of same stage variable stator vanes; and

a non-uniformity between airfoils of the variable stator vanes of the first portions and airfoils of the variable stator vanes of the second portion.

15. A gas turbine engine assembly as claimed in claim 14 further comprising all of the outer buttons in all of the variable stator vanes being equally sized and shaped and the outer openings being equiangularly spaced around the casing.

16. A gas turbine engine assembly as claimed in claim 14 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise biased with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise biased with respect to the nominal airfoil position.

17. A gas turbine engine assembly as claimed in claim 14 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise leaned with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise leaned with respect to the nominal airfoil position.

18. A gas turbine engine assembly as claimed in claim 17 wherein the airfoils in the first and second portions are counter-clockwise and clockwise leaned about inner ends of the airfoils respectively and each of the inner ends equally positioned with respect to the rotational axis of each respective vane.

19. A gas turbine engine assembly as claimed in claim 14 further comprising:

the airfoils extending between airfoil outer and inner ends of the airfoils,

the non-uniformity including the outer ends of the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise shifted with respect to a nominal airfoil position, and

the outer ends of the airfoils in the second portion of the plurality of variable stator vanes being clockwise shifted with respect to the nominal airfoil position.

20. A gas turbine engine assembly as claimed in claim 14 wherein the gas turbine engine casing is the same or has the same design as a previously manufactured gas turbine engine or a family of gas turbine engines with uniform same stage variable stator vanes having uniform airfoils.

21. A gas turbine engine assembly as claimed in claim 20 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise biased with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise biased with respect to the nominal airfoil position.

22. A gas turbine engine assembly as claimed in claim 20 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise leaned with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise leaned with respect to the nominal airfoil position.

23. A gas turbine engine assembly as claimed in claim 22 wherein the airfoils in the first and second portions are counter-clockwise and clockwise leaned about inner ends of the airfoils respectively and each of the inner ends equally positioned with respect to the rotational axis of each respective vane.

24. A gas turbine engine assembly as claimed in claim 23 further comprising:

the airfoils extending between airfoil outer and inner ends of the airfoils,

the non-uniformity including the outer ends of the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise shifted with respect to a nominal airfoil position, and

the outer ends of the airfoils in the second portion of the plurality of variable stator vanes being clockwise shifted with respect to the nominal airfoil position.

25. A gas turbine engine assembly as claimed in claim 14 further comprising each of the airfoils disposed between the outer button and a spaced apart inner button and an inner spindle extending inwardly from the inner button.

26. A gas turbine engine assembly as claimed in claim 25 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise biased with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise biased with respect to the nominal airfoil position.

27. A gas turbine engine assembly as claimed in claim 25 further comprising all of the outer buttons in all of the variable stator vanes being equally sized and shaped and all of the inner buttons in all of the variable stator vanes being equally sized and shaped and the outer openings being equiangularly spaced around the casing.

28. A gas turbine engine assembly comprising:

a gas turbine engine casing radially outwardly supporting a variable vane assembly including at least one circular row of non-uniform same stage variable stator vanes having non-uniform airfoils;

each of the variable stator vanes having a rotational axis;

each of the airfoils extending inwardly from an outer button centered about a rotational axis;

each of the variable stator vanes including an outer spindle extending outwardly from the outer button;

the outer spindles rotatably disposed through outer trunnions mounted in outer openings in the casing;

first and second portions of the plurality of same stage variable stator vanes disposed in first and second 180 degree sectors respectively of the row of the variable stator vanes;

the first and second portions of the vanes having equal numbers of the vanes; and

a non-uniformity between airfoils of the variable stator vanes of the first portions and airfoils of the variable stator vanes of the second portion.

29. A gas turbine engine assembly as claimed in claim 28 further comprising all of the outer buttons in all of the variable stator vanes being equally sized and shaped and the outer openings being equiangularly spaced around the casing.

30. A gas turbine engine assembly as claimed in claim 28 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise biased with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise biased with respect to the nominal airfoil position.

31. A gas turbine engine assembly as claimed in claim 28 wherein the non-uniformity includes the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise leaned with respect to a nominal airfoil position and the airfoils in the second portion of the plurality of variable stator vanes being clockwise leaned with respect to the nominal airfoil position.

32. A gas turbine engine assembly as claimed in claim 31 wherein the airfoils in the first and second portions are counter-clockwise and clockwise leaned about inner ends of the airfoils respectively and each of the inner ends equally positioned with respect to the rotational axis of each respective vane.

33. A gas turbine engine assembly as claimed in claim 30 further comprising:

the airfoils extending between airfoil outer and inner ends of the airfoils,

the non-uniformity including the outer ends of the airfoils in the first portion of the plurality of variable stator vanes being counter-clockwise shifted with respect to a nominal airfoil position, and

the outer ends of the airfoils in the second portion of the plurality of variable stator vanes being clockwise shifted with respect to the nominal airfoil position.

34. A gas turbine engine assembly as claimed in claim 39 wherein the gas turbine engine casing is the same or has the same design as a previously manufactured gas turbine engine or a family of gas turbine engines with uniform same stage variable stator vanes having uniform airfoils.

35. A method for manufacturing a gas turbine engine assembly a gas turbine engine casing radially outwardly supporting a variable vane assembly including at least one circular row of non-uniform same stage variable stator vanes, the method comprising:

providing counter-clockwise biased airfoils in a first one of upper and lower sectors of a single stage of non-uniform same stage variable stator vanes and clockwise biased airfoils in a second one of the upper and lower sectors of the single stage of non-uniform same stage variable stator vanes;

manufacturing the vanes with the counter-clockwise biased and the clockwise biased airfoils disposed between spaced apart outer and inner buttons centered about rotational axis of each of the variable stator vanes;

manufacturing the vanes with each of the variable stator vanes including an outer spindle extending outwardly from the outer button and an inner spindle extending inwardly from the inner button; and

assembling the outer spindles rotatably disposed through outer trunnions mounted in outer openings in a casing.

36. The method as claimed in claim 35 further comprising manufacturing the all the vanes with the outer buttons in all of the variable stator vanes being equally sized and shaped and all of the inner buttons in all of the variable stator vanes being equally sized and shaped.

37. The method as claimed in claim 36 wherein the gas turbine engine casing is the same or has the same design as a previously manufactured gas turbine engine or a family of gas turbine engines with uniform same stage variable stator vanes having uniform airfoils.