IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
UP-0494178
(2006-07-27)
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등록번호 |
US-7581924
(2009-09-16)
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발명자
/ 주소 |
- Marini, Bonnie D.
- Schiavo, Anthony L.
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출원인 / 주소 |
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인용정보 |
피인용 횟수 :
3 인용 특허 :
33 |
초록
▼
Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the
Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the inner and outer platforms and a portion of the airfoil of a neighboring vane. During engine operation, a high pressure coolant is supplied to at least one of the platforms. The coolant can leak through the seam. Because the seam is located proximate the airfoil, the coolant leakage through the seam can be productively used to cool the transition region between the vane platforms and the airfoil. In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life.
대표청구항
▼
What is claimed is: 1. A turbine vane system comprising: a first turbine vane including a first airfoil with a unitary first outer platform, the first airfoil having an outer end region, an inner end region, an outer peripheral surface, a pressure side, a suction side, a leading edge, a trailing ed
What is claimed is: 1. A turbine vane system comprising: a first turbine vane including a first airfoil with a unitary first outer platform, the first airfoil having an outer end region, an inner end region, an outer peripheral surface, a pressure side, a suction side, a leading edge, a trailing edge, and an airfoil mean line extending from the leading edge to the trailing edge, wherein the first outer platform transitions into the first airfoil in the outer end region, wherein the first outer platform is located substantially entirely on one of the pressure side and the suction side of the first airfoil; and a second turbine vane including a second airfoil with a unitary second outer platform, the second airfoil having an outer end region, an inner end region, a pressure side, a suction side, a leading edge, a trailing edge, and an airfoil mean line extending from the leading edge to the trailing edge, wherein the second outer platform transitions into the second airfoil in the outer end region, wherein the second outer platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first outer platform of the first turbine vane, the second outer platform extending substantially circumferentially from the second airfoil to a circumferential side that is contoured to engage at least a portion of the side of the first airfoil opposite the first outer platform, the first vane being positioned substantially adjacent the second vane such that the outer end region of the first airfoil is substantially cooperatively enclosed by the first outer platform and the circumferential end of the second outer platform, wherein a seam is formed between the substantially adjacent portions of the first and second vanes, the seam including a cooling gap extending proximate the side of the first airfoil opposite the first outer platform. 2. The turbine vane of claim 1 wherein the first outer platform is located substantially entirely on the pressure side of the first airfoil, and wherein the circumferential side of the second outer platform is contoured to engage the suction side of the first airfoil. 3. The turbine vane of claim 1 wherein the first outer platform is located substantially entirely on the suction side of the first airfoil, and wherein the circumferential side of the second outer platform is contoured to engage the pressure side of the first airfoil. 4. The turbine vane of claim 1 wherein the circumferential side is contoured to substantially matingly engage at least a portion of the outer peripheral surface of the first airfoil in the outer end region. 5. The turbine vane of claim 1 wherein the first outer platform does not extend substantially beyond a boundary defined by an imaginary extrapolation of the mean line beyond the first airfoil. 6. The turbine vane of claim 1 wherein the first outer platform does not extend substantially beyond a boundary defined by an imaginary axial line extending from the leading edge of the first airfoil and an imaginary axial line extending from the trailing edge of the first airfoil. 7. The turbine vane system of claim 1 further including a coolant supplied to the outer platform, wherein at least a portion of the coolant flows through the cooling gap, whereby the interface between the circumferential end of the second outer platform and the first airfoil is cooled. 8. The turbine vane system of claim 1 further including a seal operatively positioned along at least a portion of the seam. 9. The turbine vane of claim 1 wherein the first outer platform further includes a platform lip that extends in the outer end region about the opposite one of the pressure side and the suction side of the airfoil from the first platform, whereby the cooling gap is formed in part between the platform lip of the first outer platform and the circumferential end of the second outer platform. 10. The turbine vane of claim 1 wherein the outer peripheral surface of the first airfoil on the opposite one of the pressure side and the suction side of the first airfoil from the first outer platform is exposed in the outer end region, whereby the cooling gap is formed in part between the outer peripheral surface of the first airfoil and the circumferential end of the second outer platform. 11. The turbine vane of claim 1 wherein the first turbine vane further includes a first inner platform unitary with the first airfoil, wherein the first inner platform transitions into the first airfoil in the inner end region, wherein the first inner platform is located substantially entirely on one of the pressure side and the suction side of the first airfoil, wherein the second turbine vane includes a second inner platform unitary with the second airfoil, wherein the second inner platform transitions into the second airfoil in the inner end region, wherein the second inner platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first inner platform of the first turbine vane, the second inner platform extending substantially circumferentially from the second airfoil to a circumferential side that is contoured to engage at least a portion of the side of the first airfoil opposite the first outer platform, and wherein the inner end region of the first airfoil is substantially cooperatively enclosed by the first inner platform and the circumferential end of the second inner platform, wherein a seam is formed between the substantially adjacent portions of the first and second vanes, the seam including a cooling gap extending proximate the side of the first airfoil opposite the first inner platform. 12. The turbine vane of claim 11 wherein the first inner platform and the first outer platform are located on the same one of the pressure side and the suction side of the first airfoil, and wherein the second inner platform and the second outer platform are located on the same one of the pressure side and the suction side of the second airfoil. 13. A turbine vane system comprising: a first turbine vane including a first airfoil with a unitary first inner platform, the first airfoil having an outer end region, an inner end region, an outer peripheral surface, a pressure side, a suction side, a leading edge, and a trailing edge, wherein the first inner platform transitions into the first airfoil in the inner end region, wherein the first inner platform is located substantially entirely on one of the pressure side and the suction side of the first airfoil; and a second turbine vane including a second airfoil with a unitary second inner platform, the second airfoil having an outer end region, an inner end region, a pressure side, a suction side, a leading edge, and a trailing edge, wherein the second inner platform transitions into the second airfoil in the inner end region, wherein the second inner platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first inner platform of the first turbine vane, the second inner platform extending substantially circumferentially from the second airfoil to a circumferential side that is contoured to engage at least a portion of the side of the first airfoil opposite the first inner platform, the first vane being positioned substantially adjacent the second vane such that the inner end region of the first airfoil is substantially cooperatively enclosed by the first inner platform and the circumferential end of the second inner platform, wherein a seam is formed between the substantially adjacent portions of the first and second vanes, the seam including a cooling gap extending proximate the side of the first airfoil opposite the first inner platform. 14. A method of cooling a portion of an airfoil comprising: providing a turbine engine, the turbine engine including a first turbine vane and a second turbine vane, the first turbine vane including a first airfoil with a unitary first platform, the first airfoil having an outer end region, an inner end region, an outer peripheral surface, a pressure side, a suction side, a leading edge, and a trailing edge, wherein the first platform transitions into the first airfoil in one of the inner end region and the outer end region, wherein the first platform is located substantially entirely on one of the pressure side and the suction side of the first airfoil; and the second turbine vane including a second airfoil with a unitary second platform, the second airfoil having an outer end region, an inner end region, a pressure side, a suction side, a leading edge, and a trailing edge, wherein the second platform transitions into the second airfoil in one of the outer end region and the inner end region, wherein the second platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first platform of the first turbine vane, the second platform extending substantially circumferentially from the second airfoil to a circumferential side that is contoured to engage at least a portion of the side of the first airfoil opposite the first platform, the first vane being positioned substantially adjacent the second vane such that one of the outer end region and the inner end region of the first airfoil is substantially cooperatively enclosed by the first platform and the circumferential end of the second platform, wherein a seam is formed between the substantially adjacent portions of the first and second vanes, the seam including a cooling gap extending proximate the side of the first airfoil opposite the first platform; and supplying a coolant to the first and second platforms such that a portion of the coolant leaks through the cooling gap, whereby a portion of the first airfoil proximate the cooling gap is cooled by the leaking coolant. 15. The method of claim 14 further including the step of directing the leakage toward the first airfoil. 16. The method of claim 15 wherein the directing step includes operatively positioning at least one seal along at least a portion of the cooling seam. 17. The method of claim 14 wherein the first platform is located substantially entirely on the pressure side of the first airfoil, and wherein the circumferential side of the second platform is contoured to engage the suction side of the first airfoil. 18. The method of claim 14 wherein the first platform is located substantially entirely on the suction side of the first airfoil, and wherein the circumferential side of the second platform is contoured to engage the pressure side of the first airfoil. 19. The method of claim 14 wherein the circumferential side of the second platform is contoured to substantially matingly engage at least a portion of the outer peripheral surface of the first airfoil in one of the first and second end regions. 20. The method of claim 14 wherein the first platform further includes a platform lip that extends about the opposite one of the pressure side and the suction side of the airfoil from the first platform, whereby the cooling gap is formed in part between the platform lip of the first platform and the circumferential end of the second platform.
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