BULGED NOZZLE FOR CONTROL OF SECONDARY FLOW AND OPTIMAL DIFFUSER PERFORMANCE

• US 20170107835A1
• Filed: 10/15/2015
• Published: 04/20/2017
• Est. Priority Date: 10/15/2015
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Bhaumik, Soumyik Kumar, Chouhan, Rohit
• Granted Patent: US 9,988,917 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/047 Nozzle boxes
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/124 related to the suction side of a stator vane
• CPC Class Codes: F05D 2240/128 Nozzles
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2250/28 patterned
• CPC Class Codes: F05D 2250/711 convex
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

A turbine nozzle configured to be disposed in a turbine includes a suction side, a pressure side, and a bulge disposed on the suction side. The suction side extends between a leading edge and a trailing edge in an axial direction and transverse to a longitudinal axis of the turbine nozzle, and extends a height of the turbine nozzle in a radial direction along the longitudinal axis. The pressure side is disposed opposite the suction side and extends between the leading edge of the turbine nozzle and the trailing edge of the turbine nozzle in the axial direction, and extends the height of the turbine nozzle in the radial direction. The bulge is disposed on the suction side protruding relative to the other portion of the suction side in a direction transverse to both the radial and axial directions. The turbine nozzle has a first periphery defined at a first cross-section at a first location along the height of the turbine nozzle by selected coordinate sets listed in Table 1.

Claims

1. A turbine nozzle configured to be disposed in a turbine comprising:

a suction side extending between a leading edge of the turbine nozzle and a trailing edge of the turbine nozzle in an axial direction and transverse to a longitudinal axis of the turbine nozzle, and extending a height of the turbine nozzle in a radial direction along the longitudinal axis;

a pressure side disposed opposite the suction side and extending between the leading edge of the turbine nozzle and the trailing edge of the turbine nozzle in the axial direction, and extending the height of the turbine nozzle in the radial direction; and

a bulge disposed on the suction side of the turbine nozzle protruding relative to the other portion of the suction side in a direction transverse to both the radial and axial directions;

wherein the turbine nozzle has a first periphery defined at a first cross-section at a first location along the height of the turbine nozzle by selected coordinate sets listed in Table 1.

2. The turbine nozzle of claim 1, wherein the turbine nozzle has a second periphery defined at a second cross-section at a second location along the height of the turbine nozzle different from the first location by selected coordinate sets listed in Table 2.

3. The turbine nozzle of claim 2, wherein the turbine nozzle has a third periphery defined at a third cross-section at a third location along the height of the turbine nozzle different from both the first and second locations by selected coordinate sets listed in Table 3.

4. The turbine nozzle of claim 3, wherein the turbine nozzle has a fourth periphery defined at a fourth cross-section at a fourth location along the height of the turbine nozzle different from the first, second, and third locations by selected coordinate sets listed in Table 4.

5. The turbine nozzle of claim 4, wherein the turbine nozzle has a fifth periphery defined at a fifth cross-section at a fifth location along the height of the turbine nozzle different from the first, second, third, and fourth locations by selected coordinate sets listed in Table 5.

6. The turbine nozzle of claim 5, wherein the bulge begins to protrude at a starting height at a first percentage of the height of the nozzle, reaches a maximum protrusion at a second percentage of the height of the nozzle, and ceases to protrude at an ending height at a third percentage of the height of the nozzle.

7. The turbine nozzle of claim 1, wherein the bulge extends at least more than half of a length of the suction side between the leading edge and the trailing edge.

8. The turbine nozzle of claim 1, wherein the bulge extends along an entire length of the suction side.

9. The turbine nozzle of claim 1, wherein the nozzle has a tilt to the pressure side relative to a plane that extends from a rotational axis of the turbine in the radial direction.

10. The turbine nozzle of claim 9, wherein the tilt to the pressure side is greater than about 0 degrees and equal to or less than about 5 degrees.

11. A system, comprising:

a turbine, comprising;

a first annular wall;

a second annular wall; and

a last stage comprising a plurality of nozzles disposed annularly between the first and second annular walls about a rotational axis of the turbine, wherein each nozzle of the plurality of nozzles comprises;

a height extending between the first and second annular walls;

a leading edge;

a trailing edge disposed downstream of the leading edge;

a suction side extending between the leading edge and the trailing edge in an axial direction, and extending the height of the nozzle in a radial direction;

a pressure side disposed opposite the suction side and extending between the leading edge of the nozzle and the trailing edge of the nozzle in the axial direction, and extending the height of the nozzle in the radial direction;

a bulge disposed on the suction side of the nozzle that protrudes in a direction transverse to a radial plane extending from the rotational axis; and

a first periphery defined at a first cross-section at a first location along the height of each nozzle of the plurality of nozzles by selected coordinate sets listed in Table 1.

12. The system of claim 11, wherein each nozzle of the plurality of nozzles comprises a second periphery defined at a second cross-section at a second location along the height of each nozzle of the plurality of nozzles different from the first location by selected coordinate sets listed in Table 2.

13. The system of claim 12, wherein each nozzle of the plurality of nozzles comprises a third periphery defined at a third cross section at a third location along the height of each nozzle of the plurality of nozzles different from both the first and second locations by selected coordinate sets listed in Table 3.

14. The system of claim 13, wherein each nozzle of the plurality of nozzles comprises a fourth periphery defined at a fourth cross section at a fourth location along the height of each nozzle of the plurality of nozzles different from the first, second, and third locations by selected coordinate sets listed in Table 4.

15. The system of claim 14, wherein each nozzle of the plurality of nozzles comprises a fifth periphery defined at a fifth cross section at a fifth location along the height of each nozzle of the plurality of nozzles different from the first, second, third, and fourth locations by selected coordinate sets listed in Table 5.

16. The system of claim 11, wherein the leading edge and the trailing edge have a tilt toward the pressure side relative to the radial plane extending from the rotational axis in the radial direction.

17. The system of claim 16, wherein each nozzle of the plurality of nozzles is angled to the pressure side by about 3 degrees relative to the radial plane.

18. The system of claim 11, wherein the maximum protrusion of the bulge is between about 0.5% and about 5.0% of the height of the nozzle.

19. The system of claim 11, wherein the maximum protrusion of the bulge occurs between about 20% and about 40% of the height of the nozzle.

20. A system, comprising:

a turbine, comprising;

a first annular wall;

a second annular wall; and

a last stage comprising a plurality of nozzles disposed annularly between the first and second annular walls about a rotational axis of the turbine, wherein each nozzle of the plurality of nozzles comprises;

a height between the first and second annular walls;

a leading edge;

a trailing edge disposed downstream of the leading edge;

a suction side extending between the leading edge and the trailing edge in an axial direction, and extending the height of the nozzle in a radial direction;

a pressure side disposed opposite the suction side and extending between the leading edge of the nozzle and the trailing edge of the nozzle in the axial direction, and extending the height of the nozzle in the radial direction;

a bulge disposed on the suction side of the nozzle that protrudes in a direction transverse to a radial plane extending from the rotational axis; and

a first periphery defined at a first cross section at a first location along the height of each nozzle of the plurality of nozzles by selected coordinate sets listed in Table 1;

a second periphery defined at a second cross section at a second location along the height of each nozzle of the plurality of nozzles different from the first location by selected coordinate sets listed in Table 2;

a third periphery defined at a third cross section at a third location along the height of each nozzle of the plurality of nozzles different from both the first and second locations by selected coordinate sets listed in Table 3;

a fourth periphery defined at a fourth cross section at a fourth location along the height of each nozzle of the plurality of nozzles different from the first, second, and third locations by selected coordinate sets listed in Table 4; and

a fifth periphery defined at a fifth cross section at a fifth location along the height of each nozzle of the plurality of nozzles different from the first, second, third, and fourth locations by selected coordinate sets listed in Table 5;

wherein each nozzle of the plurality of nozzles is angled relative to the radial plane toward the pressure side.