Bulged nozzle for control of secondary flow and optimal diffuser performance

Patent metadata

Field	Value
Publication number	US-9988917-B2
Application number	US-201514884140-A
Country	US
Kind code	B2
Filing date	Oct 15, 2015
Priority date	Oct 15, 2015
Publication date	Jun 5, 2018
Grant date	Jun 5, 2018

Abstract

A turbine nozzle disposed in a turbine includes a suction side having a bulge, and a pressure side. The suction side and the pressure side extend opposite one another between a leading edge and a trailing edge in an axial direction transverse to a longitudinal axis of the turbine nozzle, and extends a radial direction along the longitudinal axis. 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.

First claim

The invention claimed is:

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 from 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 0 degrees and equal to or less than 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 3 degrees relative to the radial plane.

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

19. The system of claim 11 , wherein the maximum protrusion of the bulge occurs between 20% and 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 fr

Assignees

• Gen Electric

Inventors

• Bhaumik Soumyik Kumar
• Chouhan Rohit

Classifications

• F05D2250/28

  patterned · CPC title

• F05D2240/128

  Nozzles · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/047

  Nozzle boxes · CPC title

• F05D2250/711

  convex · CPC title