Turbine bucket having non-axisymmetric endwall contour and profile

Patent metadata

Field	Value
Publication number	US-2017226863-A1
Application number	US-201615019461-A
Country	US
Kind code	A1
Filing date	Feb 9, 2016
Priority date	Feb 9, 2016
Publication date	Aug 10, 2017
Grant date	—

Abstract

Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket 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 a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.

First claim

We claim:

1 . A turbine bucket 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 a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.

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

3 . The turbine bucket of claim 1 , wherein the turbine bucket includes a second stage bucket.

4 . The turbine bucket of claim 1 , wherein the base directs flow of a working fluid across a passage trough proximate the suction side of the airfoil.

5 . The turbine bucket of claim 1 , wherein the base is radially inboard of the airfoil.

6 . The turbine bucket of claim 1 , wherein the non-axisymmetric endwall contour includes a thickened area.

7 . The turbine bucket of claim 6 , wherein the thickened area has an apex at approximately 0 percent to approximately 5 percent of an axial chord length of the endwall, and wherein the thickened area has an approximately zero percent to approximately 10 percent pitch from the suction side.

8 . The turbine bucket of claim 6 , wherein the thickened area has an apex at approximately 65 percent to approximately 85 percent of an axial chord length of the endwall, and wherein the thickened area has an approximately zero percent to approximately 10 percent pitch from the suction side.

9 . The turbine bucket of claim 7 , 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 Z coordinate values are non-dimensional values of from 0 to 1 convertible to Z distances by multiplying the values by an airfoil 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, the X, Y, and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil, wherein the Cartesian coordinate values have an origin at a root of the leading edge of the airfoil.

10 . A turbine rotor section comprising:
a set of buckets, the set of buckets including at least one bucket 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
a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil,
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 Z coordinate values are non-dimensional values of from 0 to 1 convertible to Z distances by multiplying the Z values by an airfoil 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, the X, Y, and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil, wherein the Cartesian coordinate values have an origin at a root of the leading edge of the airfoil.

11 . The turbine rotor section of claim 10 , further comprising a fillet connecting a surface of the base to a surface of the airfoil.

12 . The turbine rotor section of claim 10 , wherein the turbine bucket includes a second stage bucket.

13 . The turbine rotor section of claim 10 , wherein the non-axisymmetric endwall contour includes a thickened area.

14 . The turbine rotor section of claim 13 , wherein the thickened area has an apex at approximately 0 percent to approximately 5 percent of an axial chord length of the endwall, and wherein the thickened area has an approximately zero percent to approximately 10 percent pitch from the suction side.

15 . The turbine rotor section of claim 13 , wherein the thickened area has an apex at approximately 65 percent to approximately 85 percent of an axial chord length of the endwall, and wherein the thickened area has an approximately zero percent to approximately 10 percent pitch from the suction side.

16 . The turbine rotor section of claim 10 , wherein the base directs flow of a working fluid across a passage trough proximate the suction side of the airfoil.

17 . A turbine bucket 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 a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, 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 Z distances by multiplying the Z values by an airfoil 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, the X, Y, and Z distances being scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil, wherein the Cartesian coordinate values have an origin at a root of the leading edge of the airfoil.

18 . The turbine bucket of claim 17 , wherein the base includes a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.

19 . The turbine bucket of claim 18 , wherein the non-axisymmetric endwall contour includes a thickened area.

20 . The turbine bucket of claim 19 , wherein the thickened area is characterized by one of:
having an apex at approximately 65 percent to approximately 85 percent of an axial chord length of the endwall, and wherein the thickened area has an approximately zero percent to approximately 10 percent pitch from the suction side, or having an apex at approximately 0 percent to approximately 5 percent of an axial chord length of the endwall, and wherein the thickened area has an approximately zero percent to approximately 10 percent pitch from the suction side.

Assignees

• Gen Electric

Inventors

• Brozyna Lee Larned
• Ciray Mehmet Suleyman
• Jones Mark Andrew

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2250/73

  asymmetric · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title