IPC분류정보
| 국가/구분 |
United States(US) Patent
등록
|
| 국제특허분류(IPC7판) |
|
| 출원번호 |
US-0019461
(2016-02-09)
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| 등록번호 |
US-10190417
(2019-01-29)
|
|
발명자
/ 주소 |
- Brozyna, Lee Larned
- Ciray, Mehmet Suleyman
- Jones, Mark Andrew
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| 출원인 / 주소 |
|
| 대리인 / 주소 |
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| 인용정보 |
피인용 횟수 :
0 인용 특허 :
46 |
초록
▼
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 suc
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.
대표청구항
▼
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; anda base c
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; anda 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 the non-axisymmetric endwall contour includes a thickened area having an approximately zero percent to approximately 10 percent pitch as measured from the suction side of the airfoil and a passage trough having a depression with an apex at approximately 15-20 percent of a chord length of the suction side of the airfoil,wherein the thickened area has an apex at approximately 65 percent to approximately 85 percent of an axial chord length of the endwall. 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 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. 7. The turbine bucket of claim 1, wherein the depression spans 20-25 percent pitch as measured from the suction side of the airfoil. 8. 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; anda 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. 9. The turbine rotor section of claim 8, further comprising a fillet connecting a surface of the base to a surface of the airfoil. 10. The turbine rotor section of claim 8, wherein the turbine bucket includes a second stage bucket. 11. The turbine rotor section of claim 8, wherein the non-axisymmetric endwall contour includes a thickened area. 12. The turbine rotor section of claim 11, 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. 13. The turbine rotor section of claim 11, 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. 14. The turbine rotor section of claim 8, wherein the base directs flow of a working fluid across a passage trough proximate the suction side of the airfoil. 15. 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; anda 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. 16. The turbine bucket of claim 15, wherein the base includes a non-axisymmetric endwall contour proximate a junction between the base and the airfoil. 17. The turbine bucket of claim 16, wherein the non-axisymmetric endwall contour includes a thickened area. 18. The turbine bucket of claim 17, 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, orhaving 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.
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