A rotor for turbomachines having a plurality of blades, and a damping member housed inside a chamber respectively arranged between each pair of adjacent blades of the rotor. The damping member is pushed, in use, by the centrifugal force against two surfaces, each of which is carried by a respective
A rotor for turbomachines having a plurality of blades, and a damping member housed inside a chamber respectively arranged between each pair of adjacent blades of the rotor. The damping member is pushed, in use, by the centrifugal force against two surfaces, each of which is carried by a respective blade, which limit the respective chamber in a radially outward direction. The damping member is cup-shaped and provided with a base wall facing the two surfaces of the chamber and has three support bosses provided on one surface so that at least one of the three will contact one of the two surfaces and at least one other will contact the other of the two surfaces.
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1. A rotor for turbomachines (A), the rotor comprising a central body having an axis and suitable to rotate about the axis itself; at least one row of blades surrounding the central body and which rotate with the central body about the axis; and a damping system to reduce any vibratory motion of the
1. A rotor for turbomachines (A), the rotor comprising a central body having an axis and suitable to rotate about the axis itself; at least one row of blades surrounding the central body and which rotate with the central body about the axis; and a damping system to reduce any vibratory motion of the blades; the blades of each pair of adjacent blades defining, between them, a housing chamber containing part of said damping system; and each chamber being limited, in a radially outward direction, by a relative closing wall comprising two portions separated by an air gap and belonging one to one and the other to the other of the blades of the relative pair of adjacent blades; wherein the damping system comprises a cup shaped damping member mounted floatingly, at least in a radial direction, inside each chamber and having a substantially flat upper surface, and three bosses projecting radially outwards from the substantially flat upper surface; at least a first of the three bosses facing one of the two portions of the closing wall, and at least a second of the three bosses facing the other of the two portions of the closing wall. 2. The rotor according to claim 1, wherein each blade projects radially outwards with respect to the central body and comprises a root for coupling to the central body, a base and a wing; the bases of the blades defining, together, a ring comprising said walls; and said chambers being defined on the inside of the ring. 3. The rotor according to claim 2, wherein the base of each blade comprises two opposing cup-shaped bodies, which are provided with concavities facing in opposite directions and outwardly in a circumferential direction along the ring; each cup-shaped body facing and being aligned with a corresponding cup-shaped body of an adjacent blade to define the relative chamber. 4. The rotor according to claim 1, wherein said first and second bosses are arranged along a straight line substantially transversal with respect to the relative air gap; said straight line intersecting two opposite edges of the relative substantially flat upper surface at respective points of intersection (C); and each of said first and second bosses being arranged at a distance furthest from the point of intersection (C) that is greater than a width, measured in a circumferential direction, of each of the relative said two portions. 5. The rotor according to claim 1, wherein the three bosses are arranged so as to form the vertices of a triangle (B) on the substantially flat upper surface. 6. The rotor according to claim 5, wherein the triangle (B) is a right-angled triangle (B), a shorter leg of which is substantially transversal with respect to the air gap. 7. The rotor according to claim 5, wherein the weight and of the position of a center of gravity (G) of each damping member is modifiable. 8. The rotor according to claim 7, wherein the center of gravity (G) is adjustably positioned on a radius intersecting the triangle (B). 9. The rotor according to claim 7, wherein each damping member is arranged inside the relative chamber with its concavity facing radially inwards, which is limited externally by the relative radially external surface. 10. The rotor according to claim 9, wherein the weight is adjusted, at least in part, by modifying said substantially flat upper surface. 11. The rotor according to claim 10, wherein the adjustment of the weight and the position of the center of gravity (G) includes providing at least one aperture through said base wall. 12. The rotor according to claim 1, wherein the damping system also provides dynamic balancing of said rotor. 13. The rotor according to claim 1, wherein at least one of said bosses is coated with an anti-wear material. 14. A damping system for turbomachinery that incorporates a rotor having a plurality of blades, each blade having a root and a base; each rotor including part of an internal chamber established between adjacent rotors and located between the base and the root of each of the plurality of blades; the internal chamber including two adjacent and spaced apart closing wall portions, the damping system including a cup shaped damping member positioned within said internal chamber so as to float therein and having substantially flat, radial surface, and three bosses projecting radially outwards from the substantially flat, radial surface; at least a first of the bosses facing one of the two adjacent and spaced apart closing wall portions and a second one of the bosses facing the other of the two adjacent and spaced apart closing wall portions.
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이 특허에 인용된 특허 (7)
Herbert Brandl DE; Rudolf Kellerer DE; Brammajyosula Ravindra CH, Blade arrangement with damping elements.
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