IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0526257
(2006-09-22)
|
등록번호 |
US-7762773
(2010-08-13)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
6 인용 특허 :
17 |
초록
▼
A turbine airfoil of a turbine engine having cooling channels positioned on side surface edges of a platform of the airfoil. The platform may include at least one angled side surface that may be aligned with a side surface of a platform of an adjacent turbine blade. The airfoil may include a suction
A turbine airfoil of a turbine engine having cooling channels positioned on side surface edges of a platform of the airfoil. The platform may include at least one angled side surface that may be aligned with a side surface of a platform of an adjacent turbine blade. The airfoil may include a suction side edge formed from a first surface at an obtuse angle relative to an upper surface of the platform and a second surface at an obtuse angle relative to a bottom surface of the platform. One or more film cooling slots may be positioned in the first surface and may include a diffusion portion. A damper may also be positioned in a groove between the second surface and an adjacent platform. The damper may include cooling slots on a side surface proximate to the second surface of the suction side edge.
대표청구항
▼
I claim: 1. A turbine airfoil, comprising: a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and a co
I claim: 1. A turbine airfoil, comprising: a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and a cooling system formed from at least one cavity in the elongated, hollow airfoil; a platform positioned at an intersection of the generally elongated, hollow airfoil and the root, wherein the platform includes a leading edge, a trailing edge opposite the leading edge, a pressure side edge positioned proximate to a pressure side of the generally elongated, hollow airfoil and a suction side edge positioned proximate to a suction side of the generally elongated, hollow airfoil; wherein the suction side edge is positioned at an acute angle relative to a longitudinal axis of the platform; and wherein the suction side edge is formed from at least two surfaces, a first surface positioned at an obtuse angle relative to an upper surface of the platform and a second surface positioned at an obtuse angle relative to a bottom surface of the platform and intersecting the first surface such that the first and second surfaces are positioned in different planes. 2. The turbine airfoil of claim 1, wherein the first surface comprises at least one film cooling slot. 3. The turbine airfoil of claim 2, wherein the at least one film cooling slot further comprises a diffusion portion positioned adjacent to the upper surface of the platform. 4. The turbine airfoil of claim 3, wherein the diffusion portion comprises a first backside wall angled between about five degrees and about twenty five degrees from the first surface. 5. The turbine airfoil of claim 4, wherein the diffusion portion comprises a first backside wall angled about ten degrees from the first surface. 6. The turbine airfoil of claim 3, wherein the diffusion portion comprises a first angled sidewall angled between about five degrees and about twenty five degrees from a first sidewall of the at least one film cooling slot. 7. The turbine airfoil of claim 6, wherein the diffusion portion comprises a second angled sidewall angled between about five degrees and about twenty five degrees from a second sidewall of the at least one film cooling slot that is positioned generally opposite to the first sidewall of the at least one film cooling slot. 8. The turbine airfoil of claim 7, wherein the first and second angled sidewalls are angled at about ten degrees relative to the first and second sidewalls. 9. The turbine airfoil of claim 1, further comprising at least one damper positioned between the second surface adjacent to the bottom surface of the platform and a side surface of a platform of an adjacent turbine blade. 10. The turbine airfoil of claim 9, wherein the at least one damper has a suction side surface that is generally aligned with the second surface of the suction side edge and has a pressure side surface that is generally aligned with a side surface of a platform of an adjacent turbine blade. 11. The turbine airfoil of claim 10, further comprising at least one cooling slot positioned in the suction side surface and extending generally parallel to the suction side surface of the at least one damper. 12. The turbine airfoil of claim 1, wherein the pressure side edge is positioned at an acute angle relative to an upper surface of the platform. 13. A turbine airfoil, comprising: a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and a cooling system formed from at least one cavity in the elongated, hollow airfoil; a platform positioned at an intersection of the generally elongated, hollow airfoil and the root, wherein the platform includes a leading edge, a trailing edge opposite the leading edge, a pressure side edge positioned proximate to a pressure side of the generally elongated, hollow airfoil and a suction side edge positioned proximate to a suction side of the generally elongated, hollow airfoil; wherein the suction side edge is positioned at an acute angle relative to a longitudinal axis of the platform; at least one damper positioned at least partially in a groove between the suction side edge and a pressure side edge of an adjacent turbine airfoil; and wherein the suction side edge is formed from at least two surfaces, a first surface positioned at an obtuse angle relative to an upper surface of the platform and a second surface positioned at an obtuse angle relative to a bottom surface of the platform and intersecting the first surface such that the first and second surfaces are positioned in different planes. 14. The turbine airfoil of claim 13, wherein the first surface comprises at least one film cooling slot. 15. The turbine airfoil of claim 14, wherein the at least one film cooling slot further comprises a diffusion portion positioned adjacent to the upper surface of the platform. 16. The turbine airfoil of claim 15, wherein the diffusion portion comprises a first backside wall angled between about five degrees and about twenty five degrees from the first surface, a first angled sidewall angled between about five degrees and about twenty five degrees from a first sidewall of the at least one film cooling slot, and a second angled sidewall angled between about five degrees and about twenty five degrees from a second sidewall of the at least one film cooling slot that is positioned generally opposite to the first sidewall of the at least one film cooling slot. 17. The turbine airfoil of claim 16, wherein the first backside wall is angled about ten degrees from the first surface and the first and second angled sidewalls are angled at about ten degrees relative to the first and second sidewalls. 18. The turbine airfoil of claim 13, wherein the at least one damper has a suction side surface that is generally aligned with a side of the suction side edge and has a pressure side that is generally aligned with a side surface of a pressure side edge of an adjacent turbine blade and further comprises at least one cooling slot positioned in the suction side surface.
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