IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0801187
(2015-07-16)
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등록번호 |
US-9909436
(2018-03-06)
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발명자
/ 주소 |
- Golden, Christopher Lee
- Earnhardt, Dustin Michael
- Iduate, Michelle Jessica
- Lewis, Bryan David
- Porter, Christopher Donald
- Weber, David Wayne
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
35 |
초록
▼
Embodiments of the present disclosure provide a cooling structure for a stationary blade, which can include: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine; and a substantially crescent-shaped chamber positioned within the endwall and radially displaced
Embodiments of the present disclosure provide a cooling structure for a stationary blade, which can include: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine; and a substantially crescent-shaped chamber positioned within the endwall and radially displaced from a trailing edge of the airfoil, the substantially crescent-shaped chamber receiving a cooling fluid from a cooling circuit, wherein the substantially crescent-shaped chamber extends from a fore section positioned proximal to one of a pressure side surface and a suction side surface of the airfoil to an aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber.
대표청구항
▼
1. A cooling structure for a stationary blade, comprising: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine, the airfoil including a pressure side surface, a suction side surface, a leading edge, and a trailing edge;a substantially crescent-shaped chamber
1. A cooling structure for a stationary blade, comprising: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine, the airfoil including a pressure side surface, a suction side surface, a leading edge, and a trailing edge;a substantially crescent-shaped chamber positioned within the endwall, the substantially crescent-shaped chamber receiving a cooling fluid from a cooling circuit, wherein the substantially crescent-shaped chamber includes: a fore section positioned proximal to one of the pressure side surface and the suction side surface of the airfoil,a transition section positioned directly radially beneath the trailing edge of the airfoil and in thermal communication with the trailing edge of the airfoil through the endwall, andan aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, such that the aft section is oriented substantially perpendicularly with respect to the fore section and substantially in parallel with a perimeter surface of the endwall;an inlet positioned within the endwall, fluidly connecting an impingement cavity of the airfoil to the fore section of the substantially crescent-shaped chamber; andan outlet positioned within the endwall, fluidly connecting the aft section of the substantially crescent-shaped chamber to a fluid cavity positioned outside the airfoil and the substantially crescent-shaped chamber;wherein the cooling fluid in the fore section is in thermal communication with a portion of the endwall proximal to one of the pressure side surface and the suction side surface of the airfoil, the cooling fluid in the aft section is in thermal communication with a portion of the endwall proximal to the trailing edge of the airfoil, and wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber, such that the cooling fluid within the aft section is transmitted from the transition section of the substantially crescent-shaped chamber. 2. The cooling structure of claim 1, wherein the aft section of the substantially crescent-shaped chamber only receives the cooling fluid from the transition section of the substantially crescent-shaped chamber. 3. The cooling structure of claim 1, further comprising a plurality of thermally conductive fixtures extending through at least one of the fore section and the aft section of the substantially crescent-shaped chamber. 4. The cooling structure of claim 3, wherein the substantially crescent-shaped chamber further includes a perimeter wall, and further comprising a plurality of access zones positioned substantially along the perimeter wall of the substantially crescent-shaped chamber, each of the plurality of access zones being free of thermally conductive fixtures therein. 5. The cooling structure of claim 3, wherein the transition section is free of thermally conductive fixtures therein. 6. The cooling structure of claim 1, wherein an axial length component of the fore section of the substantially crescent-shaped chamber is at least one-half of an axial length component of one of the pressure side surface and the suction side surface of the airfoil. 7. The cooling structure of claim 1, wherein the transition section includes a protrusion extending from a radial surface of the transition section, the protrusion being configured to direct the cooling fluid from the fore section into the aft section of the substantially crescent-shaped chamber. 8. The cooling structure of claim 7, wherein a width of the transition section between the fore section and the aft section is equal to an axial width of the trailing edge of the airfoil. 9. The cooling structure of claim 1, wherein the substantially crescent-shaped chamber comprises one of at least two substantially crescent-shaped chambers positioned within the endwall, and wherein the airfoil comprises one of a pair of airfoils protruding substantially radially from the endwall. 10. A stationary blade comprising: an airfoil including a pressure side surface, a suction side surface, a leading edge, and a trailing edge, wherein the airfoil further includes a cooling circuit therein;an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine;a substantially crescent-shaped chamber positioned within the endwall, the substantially crescent-shaped chamber receiving a cooling fluid from the cooling circuit, wherein the substantially crescent-shaped chamber includes: a fore section positioned proximal to one of the pressure side surface and the suction side surface of the airfoil,a transition section positioned directly radially beneath the trailing edge of the airfoil and in thermal communication with the trailing edge of the airfoil through the endwall, andan aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, such that the aft section is oriented substantially perpendicularly with respect to the fore section and substantially in parallel with a perimeter surface of the endwall;an inlet positioned within the endwall, fluidly connecting an impingement cavity of the airfoil to the fore section of the substantially crescent-shaped chamber; andan outlet positioned within the endwall, fluidly connecting the aft section of the substantially crescent-shaped chamber to a fluid cavity positioned outside the airfoil and the substantially crescent-shaped chamber;wherein the cooling fluid in the fore section is in thermal communication with a portion of the endwall proximal to one of the pressure side surface and the suction side surface of the airfoil, the cooling fluid in the aft section is in thermal communication with a portion of the endwall proximal to the trailing edge of the airfoil, and wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber, such that the cooling fluid within the aft section is transmitted from the transition section of the substantially crescent-shaped chamber. 11. The stationary blade of claim 10, wherein the aft section of the substantially crescent-shaped chamber only receives the cooling fluid from the transition section of the substantially crescent-shaped chamber. 12. The stationary blade of claim 10, further comprising a plurality of thermally conductive fixtures extending through at least one of the fore section and the aft section of the substantially crescent-shaped chamber. 13. The stationary blade of claim 12, wherein the transition section is free of thermally conductive fixtures therein. 14. The stationary blade of claim 13, wherein a width of the transition section between the fore section and the aft section is equal to an axial width of the trailing edge of the airfoil. 15. The stationary blade of claim 12, wherein the substantially crescent-shaped chamber further includes a perimeter wall, and further comprising a plurality of access zones positioned substantially along the perimeter wall of the substantially crescent-shaped chamber, each of the plurality of access zones being free of thermally conductive fixtures therein. 16. The stationary blade of claim 10, wherein the transition section includes a protrusion extending from a radial surface of the transition section, the protrusion being configured to direct the cooling fluid from the fore section into the aft section of the substantially crescent-shaped chamber. 17. A doublet turbine nozzle comprising: a first airfoil having a first cooling circuit therein;an endwall coupled to a radial end of the first airfoil, relative to a rotor axis of a turbomachine;a second airfoil having a second cooling circuit therein, the second airfoil being oriented substantially in parallel with the first airfoil, wherein the endwall is coupled to a radial end of the airfoil, relative to the rotor axis of the turbomachine, and wherein each of the first airfoil and the second airfoil further includes a pressure side surface, a suction side surface, a leading edge, and a trailing edge;a first substantially crescent-shaped chamber positioned within the endwall, the first substantially crescent-shaped chamber receiving a first cooling fluid from the first cooling circuit,wherein the first substantially crescent-shaped chamber includes: a fore section positioned proximal to the suction side surface of the first airfoil,a transition section positioned directly radially beneath the trailing edge of the first airfoil and in thermal communication with the trailing edge of the first airfoil through the endwall, andan aft section positioned proximal to the trailing edge of the first airfoil and the other of the pressure side surface and the suction side surface of the first airfoil, such that the aft section is oriented substantially perpendicularly with respect to the fore section and substantially in parallel with a perimeter surface of the endwall;a first inlet positioned within the endwall, fluidly connecting an impingement cavity of the first airfoil to the fore section of the first substantially crescent-shaped chamber;a first outlet positioned within the endwall, fluidly connecting the aft section of the first substantially crescent-shaped chamber to a fluid cavity positioned outside the first airfoil and the first substantially crescent-shaped chamber;wherein the first cooling fluid in the fore section of the first substantially crescent-shaped chamber is in thermal communication with a portion of the endwall proximal to one of the pressure side surface and the suction side surface of the first airfoil, the first cooling fluid in the aft section of the first substantially crescent-shaped chamber is in thermal communication with a portion of the endwall proximal to the trailing edge of the first airfoil, and wherein the aft section of the first substantially crescent-shaped chamber is in fluid communication with the fore section of the first substantially crescent-shaped chamber, such that the cooling fluid within the aft section is transmitted from the transition section of the first substantially crescent-shaped chamber;a second substantially crescent-shaped chamber positioned within the endwall, the second substantially crescent-shaped chamber receiving a second cooling fluid from the second cooling circuit, wherein the second substantially crescent-shaped chamber includes: a fore section positioned proximal to the suction side surface of the second airfoil,a transition section positioned directly radially beneath the trailing edge of the second airfoil and in thermal communication with the trailing edge of the second airfoil through the endwall, andan aft section positioned proximal to the trailing edge of the second airfoil and the other of the pressure side surface and the suction side surface of the second airfoil, such that the aft section is oriented substantially perpendicularly with respect to the fore section and substantially in parallel with the perimeter surface of the endwall;a second inlet positioned within the endwall, fluidly connecting an impingement cavity of the second airfoil to the fore section of the second substantially crescent-shaped chamber; anda second outlet positioned within the endwall, fluidly connecting the aft section of the second substantially crescent-shaped chamber to a fluid cavity positioned outside the second airfoil and the second substantially crescent-shaped chamber;wherein the second cooling fluid in the fore section of the second substantially crescent-shaped chamber is in thermal communication with a portion of the endwall proximal to one of the pressure side surface and the suction side surface of the second airfoil, the second cooling fluid in the aft section of the second substantially crescent-shaped chamber is in thermal communication with a portion of the endwall proximal to the trailing edge of the second airfoil, and wherein the aft section of the second substantially crescent-shaped chamber is in fluid communication with the fore section of the second substantially crescent-shaped chamber, such that the cooling fluid within the aft section is transmitted from the transition section of the second substantially crescent-shaped chamber. 18. The doublet turbine nozzle of claim 17, further comprising a plurality of thermally conductive fixtures extending through one of the first and second substantially crescent-shaped chambers in one of the fore section and the aft section thereof. 19. The doublet turbine nozzle of claim 17, wherein the aft section of the first substantially crescent-shaped chamber only receives the cooling fluid from the transition section of the first substantially crescent-shaped chamber, and wherein the aft section of the second substantially crescent-shaped chamber only receives the cooling fluid from the transition section of the second substantially crescent-shaped chamber. 20. The doublet turbine nozzle of claim 18, wherein the transition section of each substantially crescent-shaped chamber further includes a protrusion extending from an axial surface of the transition section, the protrusion being configured to direct the cooling fluid from the fore section into the aft section of the substantially crescent-shaped chamber.
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