[특허]Composite blade and platform assembly

Florida Turbine Technologies, Inc.

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Composite blade and platform assembly

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/30
미국특허분류(USC)	416/193.A; 416/002; 416/220.0R
출원번호	UP-0715042 (2007-03-06)
등록번호	US-7762781 (2010-08-13)
발명자 / 주소	Brown, Wesley Matheny, Alfred P.
출원인 / 주소	Florida Turbine Technologies, Inc.
대리인 / 주소	Ryznic, John
인용정보	피인용 횟수 : 16 인용 특허 : 24

초록
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A turbine blade and platform assembly in which the platform is a separate piece that is secured to the blade through shear pins that extend along slots formed between opposed abutting parts of the blade and the platform. Because the platform is detached from the blade, the blade can be made of a single crystal superalloy with a reduction in casting defects. The platform has one or more airfoil shaped openings or slots on the outer surface in which a blade is inserted. The shear pins are inserted to secure the platform to the blade. In another embodiment, the blade root is inserted into an opening formed in the rotor disk, and shear pins are inserted into slots formed in the root and the disk opening in order to secure the blade to the rotor disk. With this embodiment, the blade can be made of a ceramic material because only compressive forces are formed to hold the blade in place.

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청구항
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We claim: 1. A turbine blade for use in a gas turbine engine, the blade comprising: a root portion having a fir tree configuration; an airfoil portion extending from the root portion; a platform edge portion formed between the airfoil portion and the root portion, the platform edge portion having a shear pin retaining slot extending substantially parallel to the blade chordwise direction; a blade platform with an airfoil shaped slot formed therein, the airfoil slot having a shear pin retaining slot; and, a shear pin secured within the slots of the platform edge and the airfoil slot to secure the platform to the blade. 2. The turbine blade of claim 1, and further comprising: the airfoil slot in the platform includes shear pin slots on the pressure side and the suction side of the slot; and, the blade platform edge portion includes shear pin slots on the pressure side and the suction side of the edge portions so that two shear pins secure the platform to the blade. 3. The turbine blade of claim 2, and further comprising: the shear pin slots in the platform and the blade follow substantially the curvature of the airfoil at the junction to the platform; and, each of the two shear pin slots open onto a side of the platform to allow for the insertion of the two shear pins. 4. The turbine blade of claim 1, and further comprising: the turbine blade is a single crystal superalloy. 5. The turbine blade of claim 1, and further comprising: the platform includes a plurality of airfoil slots in order to secure a plurality of blades to the platform. 6. The turbine blade of claim 1, and further comprising: the platform includes a pressure side edge and a suction side edge, each edge having a slot to receive a seal that provides a seal between adjacent platforms. 7. The turbine blade of claim 1, and further comprising: the shear pin is the only means of connection to prevent radial displacement of the platform with respect to the blade. 8. The turbine blade of claim 1, and further comprising: the shear pin is the only means of connection to prevent radial displacement of the platform with respect to the blade. 9. A turbine blade for use in a gas turbine engine, the blade comprising: a root portion with a pressure side retaining slot and a suction side retaining slot to receive a shear pin to secure the blade to a slot in a rotor disk; an airfoil portion extending from the root portion; a platform edge portion formed between the airfoil portion and the root portion, the platform edge portion having a shear pin retaining slot extending substantially parallel to the blade chordwise direction; a blade platform with an airfoil shaped slot formed therein, the airfoil slot having a shear pin retaining slot; and, a shear pin secured within the slots of the platform edge and the airfoil slot to secure the platform to the blade. 10. The turbine blade of claim 9, and further comprising: the turbine blade is made substantially from a ceramic material. 11. The turbine blade of claim 9, and further comprising: the airfoil slot in the platform includes shear pin slots on the pressure side and the suction side of the slot; and, the blade platform edge portion includes shear pin slots on the pressure side and the suction side of the edge portions so that two shear pins secure the platform to the blade. 12. The turbine blade of claim 9, and further comprising: the shear pin slots in the platform and the blade follow substantially the curvature of the airfoil at the junction to the platform; and, each of the two shear pin slots open onto a side of the platform to allow for the insertion of the two shear pins. 13. The turbine blade of claim 9, and further comprising: the platform includes a plurality of airfoil slots in order to secure a plurality of blades to the platform. 14. The turbine blade of claim 9, and further comprising: the platform includes a pressure side edge and a suction side edge, each edge having a slot to receive a seal that provides a seal between adjacent platforms. 15. A turbine rotor having a rotor disk with a plurality of turbine blades extending radially therefrom, the blades including a platform extending between adjacent blades to form a gas flow path, the rotor comprising: an opening in the disk to receive a blade; each blade having a root portion with means to secure the blade root to the rotor disk; each blade having a platform edge portion with a shear pin slot; a platform with an airfoil shaped slot, the slot having a shear pin retaining slot therein; and, a shear pin secured within the slots of the platform and the blade to secure the platform to the blade in the radial direction. 16. The turbine rotor of claim 15, and further comprising: the means to secure the blade root to the rotor disk is a fir tree configuration; and, the blade is made substantially from a single crystal superalloy. 17. The turbine rotor of claim 15, and further comprising: the means to secure the blade root to the rotor disk is a shear pin retaining slot formed on the suction side and the pressure side of the root portion of the blade; an opening formed in the rotor disk to securely fit the blade root, the opening having pressure side and suction side shear pin retaining slots; and, two shear pins inserted into the slots to secure the blade to the disk against radial displacement. 18. The turbine rotor of claim 17, and further comprising: the turbine blade is made substantially from a ceramic material. 19. The turbine rotor of claim 15, and further comprising: the platform includes a plurality of airfoil slots to receive a plurality of blades, each airfoil slot having a shear pin retaining slot to engage a shear pin with a blade to secure the platform against radial displacement with respect to the blade. 20. The turbine rotor of claim 15, and further comprising: the platform includes a pressure side edge and a suction side edge, each edge having a seal slot to receive a seal that provides a seal between adjacent platforms. 21. The turbine rotor of claim 15, and further comprising: the shear pin slots in the platform and the blade follow substantially the curvature of the airfoil at the junction to the platform; and, each of the two shear pin slots open onto a side of the platform to allow for the insertion of the two shear pins. 22. The turbine rotor of claim 15, and further comprising: the platform includes a pressure side edge and a suction side edge, each edge having a slot to receive a seal that provides a seal between adjacent platforms. 23. A multiple piece turbine rotor blade comprising: an airfoil section and a root section formed as a single piece from a single crystal superalloy material; the root section having a fir tree configuration for securing the blade within a slot of a rotor disk; a one piece platform having a slot in a shape of the airfoil such that the airfoil fits within the slot to minimize leakage, the platform having a pressure side platform and a suction side platform; the one piece platform being made from a material different than the airfoil; the airfoil and root section and the platform each having a slot opposed to one another; and, a shear pin secured within the slots of the platform and the airfoil and root slot to secure the platform to the airfoil and root section. 24. The multiple piece turbine rotor blade of claim 23, and further comprising: both the pressure side and the suction side of the platform and the airfoil and root section have slots with a shear pin secured within both slots. 25. The multiple piece turbine rotor blade of claim 24, and further comprising: the shear pin slots in the platform and the airfoil and root section follow substantially the curvature of the airfoil at a junction to the platform; and, each of the two shear pin slots open onto a side of the platform to allow for the insertion of the two shear pins. 26. The multiple piece turbine rotor blade of claim 24, and further comprising: the platform includes a plurality of airfoil slots in order to secure a plurality of airfoil and root sections to the platform; and, the platform includes two slots for each airfoil and root section with one slot on the pressure wall side and the second slot on the suction wall side. 27. The multiple piece turbine rotor blade of claim 26, and further comprising: the shear pin slots in the platform and the airfoil and root section follow substantially the curvature of the airfoil at a junction to the platform; and, each of the shear pin slots open onto a side of the platform to allow for the insertion of the shear pins.

이 특허에 인용된 특허 (24)

이 특허를 인용한 특허 피인용횟수: 16

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Composite blade and platform assembly

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