IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0605857
(2006-11-28)
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등록번호 |
US-7704044
(2010-05-20)
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발명자
/ 주소 |
|
출원인 / 주소 |
- Florida Turbine Technologies, Inc.
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
2 인용 특허 :
15 |
초록
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A rotor disc and rotor blade assembly in which the rotor blades include curved shear pins to secure the blade to the rotor disc. The blade includes an airfoil portion with an airfoil outline shape at the junction of the airfoil with the platform, and the root extends below the platform and has the g
A rotor disc and rotor blade assembly in which the rotor blades include curved shear pins to secure the blade to the rotor disc. The blade includes an airfoil portion with an airfoil outline shape at the junction of the airfoil with the platform, and the root extends below the platform and has the general shape of the airfoil at the junction. An opening in the rotor disc also has the shape of the airfoil outline such that the root will fit snuggly within the opening in the rotor disc. Curved slots in both the opening and the root wall are formed on both sides of the opening and the blade root. Shear pins having a rectangular cross sectional shape fit within the slots to secure the blade to the disc. Because the root curvature follows the airfoil shape, the shear pins are located below the airfoil walls and absorb the shear stress caused by bending forces acting on the airfoil from the fluid reaction.
대표청구항
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I claim the following: 1. A rotor assembly for a turbomachine, comprising: a rotor disk having at least one opening to receive a rotor blade; a rotor blade having an airfoil portion and a root portion, the airfoil portion having a pressure side wall and a suction side wall; the root portion of the
I claim the following: 1. A rotor assembly for a turbomachine, comprising: a rotor disk having at least one opening to receive a rotor blade; a rotor blade having an airfoil portion and a root portion, the airfoil portion having a pressure side wall and a suction side wall; the root portion of the blade having sides following substantially the shape of the airfoil side walls; slots formed on the rotor disk opening and on the blade root, the slots having a curvature generally following the curvature of the airfoil wall above the slot; and, a shear pin located within the slot to secure the blade against radial movement within the rotor disk opening. 2. The rotor assembly of claim 1, and further comprising: the opening in the rotor disk is a fir tree shaped member secured in a fir tree shaped slot in the rotor disk; and, the opening for the blade root being formed in the fir tree member. 3. The rotor assembly of claim 1, and further comprising: the shear pins having substantially a rectangular cross section shape such that the shear pin is capable of flexing in the curved slot while maintaining high shear stress resistance. 4. The rotor assembly of claim 1, and further comprising: a plug inserted within the opening to engage the blade root and provide a preload to the shear pin. 5. The rotor assembly of claim 4, and further comprising: the plug being threadably engaged with the opening in order to apply the preload to the shear pin. 6. The rotor assembly of claim 1, and further comprising: the shear pin being formed substantially from a nickel alloy. 7. The rotor assembly of claim 1, and further comprising: slots are formed on both sides of the root walls and the rotor disk opening; and, a shear pin inserted into both of the slots to retain the blade within the rotor disk against radial movement. 8. The rotor assembly of claim 4, and further comprising: an abutment member positioned between the plug and the blade root. 9. The rotor assembly of claim 1, and further comprising: the slots on the blade root are on an inner surface of the blade root and face inward and toward each other. 10. The rotor assembly of claim 1, and further comprising: the slots on the blade root are on an outer surface of the blade root and face outward and away each other. 11. A rotor assembly for a turbomachine, comprising: a rotor disk having at least one opening to receive a rotor blade; a rotor blade having an airfoil portion and a root portion, the airfoil portion having a pressure side wall and a suction side wall; the opening in the rotor disk and the blade root sides each having a slot of substantially the same size; and, a shear pin located within the slot to secure the blade against radial movement within the rotor disk opening, the slots and the shear pin having a substantially rectangular cross sectional shape in which the height of the shear pin in the blade radial direction is at least twice the length of the width of the shear pin. 12. The rotor assembly of claim 11, and further comprising: the opening in the rotor disk is a fir tree shaped member secured in a fir tree shaped slot in the rotor disk; and, the opening for the blade root being formed in the fir tree member. 13. The rotor assembly of claim 11, and further comprising: a plug inserted within the opening to engage the blade root and provide a preload to the shear pin. 14. The rotor assembly of claim 13, and further comprising: the plug being threadably engaged with the opening in order to apply the preload to the shear pin. 15. The rotor assembly of claim 11, and further comprising: the shear pin being formed substantially from a nickel alloy. 16. The rotor assembly of claim 11, and further comprising: slots are formed on both sides of the root walls and the rotor disk opening; and, a shear pin inserted into both of the slots to retain the blade within the rotor disk against radial movement. 17. The rotor assembly of claim 13, and further comprising: an abutment member positioned between the plug and the blade root. 18. The rotor assembly of claim 11, and further comprising: the slots on the blade root are on an inner surface of the blade root and face inward and toward each other. 19. The rotor assembly of claim 11, and further comprising: the slots on the blade root are on an outer surface of the blade root and face outward and away each other. 20. A rotor blade for use in a turbomachine, the rotor blade comprising: an airfoil portion having a pressure side wall and a suction side wall; a root portion extending from the airfoil portion, the root portion having side walls of substantially the same shape as the pressure and suction side walls; and, a slot located on each of the root side walls, the slots having a substantially rectangular cross sectional shape in which the height is at least twice the length as the overall width of the two slots combined, and each slot having a bottom such that each slot can be filled with a shear pin. 21. The rotor blade of claim 20, and further comprising: the slots on the blade root are on an inner surface of the blade root and face inward and toward each other. 22. The rotor blade of claim 20, and further comprising: the slots on the blade root are on an outer surface of the blade root and face outward and away each other. 23. A rotor blade for use in a turbomachine, the rotor blade comprising: an airfoil portion having a pressure side wall and a suction side wall; a root portion extending from the airfoil portion, the root portion having side walls of substantially the same shape as the pressure and suction side walls; a slot located on each of the root side walls, the slots having a substantially rectangular cross sectional shape in which the height is at least twice the length as the overall width of the two slots combined; and, the blade root having an abutment face within an opening of the root to engage with a plug member.
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