Turbine nozzle having non-axisymmetric endwall contour (EWC)
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/14
F01D-009/04
출원번호
US-0060996
(2013-10-23)
등록번호
US-9376927
(2016-06-28)
발명자
/ 주소
Stein, Alexander
Brown, Joe Timothy
Meenakshisundaram, Ravichandran
출원인 / 주소
General Electric Company
대리인 / 주소
Cusick, Ernest G.
인용정보
피인용 횟수 :
5인용 특허 :
68
초록▼
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 suc
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 a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.
대표청구항▼
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; andat least
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; andat 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 a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil,wherein the non-axisymmetric contour includes a first thickened area having an apex at approximately 20% axial chord upstream of the leading edge,wherein the non-axisymmetric contour further includes a second thickened area having an apex at approximately 15-20% of an axial chord length of the leading edge. 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 first stage nozzle. 4. The turbine nozzle of claim 1, wherein the at least one endwall directs flow of a working fluid through a passage trough proximate the pressure side of the airfoil. 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 first thickened area extends across at least approximately 10 percent of an axial length of the endwall, and has a pitch of approximately zero percent to approximately 5 percent from the suction side. 7. The turbine nozzle of claim 1, wherein the first thickened area extends across approximately 20 percent to approximately 30 percent of an axial length of the endwall. 8. The turbine nozzle 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 coordinate values are non-dimensional values of from 0 to 1 convertible to distances by multiplying the values by a trailing 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. 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; andat 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 a non-axisymmetric contour proximate a junction between the endwall and the leading edge of 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 coordinate values are non-dimensional values of from 0 to 1 convertible to distances by multiplying the values by a trailing 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 first stage nozzle. 12. The static nozzle section of claim 9, wherein the non-axisymmetric contour includes a thickened area having an apex at approximately 20% axial chord upstream 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 has a pitch of approximately zero percent to approximately 5 percent from the suction side. 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 a passage trough proximate the pressure side of the airfoil. 16. A turbine comprising: a rotor section; anda static nozzle section at least partially surround the rotor section, the static nozzle section including 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; andat 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: a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil,wherein the non-axisymmetric contour includes a thickened area having an apex at approximately 20% axial chord upstream of the leading edge,wherein the non-axisymmetric contour further includes a second thickened area having an apex at approximately 15-20% of an axial chord length of the leading edge. 17. The turbine of claim 16, wherein the second thickened area extends across at least approximately 10 percent of an axial length of the endwall, and has a pitch of approximately zero percent to approximately 5 percent from the suction side. 18. The turbine of claim 16, 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 trailing 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.
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