Turbine nozzle profile

Patent metadata

Field	Value
Publication number	US-10125623-B2
Application number	US-201615019426-A
Country	US
Kind code	B2
Filing date	Feb 9, 2016
Priority date	Feb 9, 2016
Publication date	Nov 13, 2018
Grant date	Nov 13, 2018

Abstract

Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including an axisymmetric contour.

First claim

We claim:

1. A turbine nozzle comprising:
an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and
at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including an axisymmetric contour
wherein at least one of the suction side or the pressure side of the airfoil includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the coordinate values are non-dimensional values of from 0 to 1 convertible to distances by multiplying the values by a leading edge height expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil profile, wherein the Cartesian coordinate values have an origin at a root of the leading edge of the airfoil.

2. The turbine nozzle of claim 1 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.

3. The turbine nozzle of claim 1 , wherein the turbine nozzle includes a fourth stage nozzle.

4. The turbine nozzle of claim 1 , wherein the at least one endwall directs flow of a working fluid through the axisymmetric contour.

5. The turbine nozzle of claim 1 , wherein the at least one endwall includes an inner endwall or an outer endwall.

6. The turbine nozzle of claim 1 , wherein the axisymmetric contour includes a thickened area having an apex at approximately 50% axial chord downstream of the leading edge.

7. The turbine nozzle of claim 6 , wherein the thickened area extends across at least approximately 10 percent of an axial length of the endwall, and extends across an entire pitch of the turbine nozzle.

8. The turbine nozzle of claim 6 , wherein the thickened area extends across approximately 20 percent to approximately 30 percent of an axial length of the endwall.

9. A static nozzle section comprising:
a set of static nozzles, the set of static nozzles including at least one nozzle having:
an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and
at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including an axisymmetric contour,
wherein at least one of the suction side or the pressure side of the airfoil includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the coordinate values are non-dimensional values of from 0 to 1 convertible to distances by multiplying the values by a leading edge height expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil profile, wherein the Cartesian coordinate values have an origin at a root of the leading edge of the airfoil.

10. The static nozzle section of claim 9 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.

11. The static nozzle section of claim 9 , wherein the turbine nozzle includes a fourth stage nozzle.

12. The static nozzle section of claim 9 , wherein the axisymmetric contour includes a thickened area having an apex at approximately 50% axial chord downstream of the leading edge.

13. The static nozzle section of claim 12 , wherein the thickened area extends across at least approximately 10 percent of an axial length of the endwall, and extends across an entire pitch of the turbine nozzle.

14. The static nozzle section of claim 12 , wherein the thickened area extends across approximately 20 percent to approximately 30 percent of an axial length of the endwall.

15. The static nozzle section of claim 9 , wherein the at least one endwall directs flow of a working fluid through the axisymmetric contour.

16. A turbine nozzle comprising:
an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and
at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge,
wherein at least one of the pressure side or the suction side of the airfoil includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the coordinate values are non-dimensional values of from 0 to 1 convertible to distances by multiplying the values by a leading edge height expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil profile, wherein the Cartesian coordinate values have an origin at a root of the leading edge of the airfoil.

17. The turbine of claim 16 , wherein the at least one endwall includes an axisymmetric contour.

18. The turbine of claim 17 , wherein the axisymmetric contour includes a thickened area having an apex at approximately 50% axial chord downstream of the leading edge.

19. The turbine of claim 17 , wherein the thickened area extends across at least approximately 10 percent of an axial length of the endwall, and extends across an entire pitch of the turbine nozzle.

Assignees

• Gen Electric

Inventors

• Bielek Craig Allen
• Ghute Pradeep Jagannath

Classifications

• F05D2220/30

  in turbines · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F05D2240/128

  Nozzles · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title