IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0675969
(2007-02-16)
|
등록번호 |
US-7785074
(2010-09-20)
|
우선권정보 |
IT-MI2006A0340(2006-02-27) |
발명자
/ 주소 |
- Novori, Alessio
- Arinci, Paolo
- Lorusso, Salvatore
|
출원인 / 주소 |
|
대리인 / 주소 |
Potomac Patent Group PLLC
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
18 |
초록
▼
A blade of a rotor of a second stage of a compressor can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), where the axis (Z) is a radial axis intersecting the central axis of the compressor. The blade has a profile which can be identified by a
A blade of a rotor of a second stage of a compressor can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), where the axis (Z) is a radial axis intersecting the central axis of the compressor. The blade has a profile which can be identified by a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. The blade also has a non-linearly variable trend of decreasing maximum thickness defined by the closed curves, substantially parallel to a base portion of the blade itself, fixable to the rotor. The variable trend of maximum thickness is substantially situated midway up the blade and is suitable for shifting the natural resonance frequencies of the blade itself outside a functioning velocity range of the rotor.
대표청구항
▼
What is claimed is: 1. A blade of a rotor of a second stage of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having a
What is claimed is: 1. A blade of a rotor of a second stage of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having an aerodynamic profile which can be identified by a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising: a base portion fixable to the rotor, the aerodynamic profile identified by a first substantially concave surface, which is pressurized, and a second substantially convex surface which is in depression and which is opposite to the first concave surface, said two surfaces being continuous and joined to each other to form the aerodynamic profile of said blade extending from a foot at said base portion to a free end of said blade distal from said base portion, wherein each closed curve substantially parallel to said base portion has a maximum thickness determined by a maximum distance between said first surface and said second surface, said maximum thickness of each closed curve, along the height of the blade in the direction of the free end of the blade, having a non-linearly variable trend decreasing at a higher rate from said base portion to a first predetermined height, then at a lower rate from the first predetermined height to a second predetermined height, said variable trend of maximum thickness halfway up the blade being suitable for shifting one or more natural resonance frequencies of the blade itself outside a functioning velocity range of said rotor. 2. The blade according to claim 1, wherein along the height of the blade in the direction of its free end, said maximum thickness has a trend according to a polynomial function of the sixth degree. 3. The blade according to claim 2, wherein said polynomial function of the sixth degree is: Tmax=−21.119*h6+70.467*h5−85.603*h4+44.523*h3−7.8323*h2−1.1541*h+0.997 wherein h represents the percentage of the height of the blade, and wherein Tmax is the maximum adimensionalized thickness relating to the closed curve corresponding to that percentage of the height of the blade. 4. The blade according to claim 1, wherein the profile of said blade comprises an antiwear coating. 5. The blade according to claim 4, wherein said coating has a thickness ranging from 0 mm to 0.5 mm. 6. A rotor of a second stage of a compressor, wherein the rotor comprises: a series of blades according to claim 1. 7. The rotor according to claim 6, wherein said series of blades constrained to an outer surface of said rotor and said series of blades is also uniformly distributed thereon in order to maximize the efficiency of the rotor itself. 8. A compressor comprising a rotor according to claim 6. 9. The blade according to claim 1, wherein said first predetermined height is about 25% of the height of the blade. 10. The blade according to claim 9, wherein said second predetermined height is above about 50% of the height of the blade. 11. The blade according to claim 10, further comprising said maximum thickness of each closed curve variable trend decreasing at a higher rate from said second predetermined height to a third predetermined height than the rate from the first predetermined height to the second predetermined height. 12. The blade according to claim 11, further comprising said maximum thickness of each closed curve variable trend decreasing at a lower rate from said third predetermined height to the free end than the rate from the second predetermined height to the third predetermined height. 13. The blade according to claim 1, wherein said second predetermined height is above about 50% of the height of the blade. 14. A blade of a rotor of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having an aerodynamic profile which can be identified by a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising: a base portion fixable to the rotor, the aerodynamic profile identified by a first substantially concave surface, which is pressurized, and a second substantially convex surface which is in depression and which is opposite to the first, said two surfaces being continuous and joined to each other to form the aerodynamic profile of said blade extending from a foot at said base portion to a free end of said blade distal from said base portion, said closed curves defined according to Table I, whose values, expressed in millimeters, refer to a profile at room temperature. 15. The blade according to claim 14, wherein the aerodynamic profile of said blade has a tolerance of +/−2 mm in a normal direction with respect to the profile of the blade itself. 16. A blade of a rotor of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having a profile which can be identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising said closed curves defined according to Table I, whose values, expressed in millimeters, refer to a profile at room temperature. 17. The blade according to claim 16, wherein the profile of said blade has a tolerance of +/−2 mm in a normal direction with respect to the profile of the blade itself. 18. The blade according to claim 16 wherein the values of the coordinates of Table I are multiplied by a corrective constant to obtain a scaled profile maintaining the same form. 19. A rotor of a second stage of a compressor, the rotor comprising a series of blades according to claim 16. 20. A blade of a rotor of a compressor, said blade having a profile which can be identified by a series of closed intersection curves between the profile itself and planes substantially perpendicular to a central axis of the blade, said blade comprising: a base portion fixable to the rotor; and a blade portion connected with a first end to the base portion and having a second end free standing, wherein the aerodynamic profile is identified by a first substantially concave surface, and a second substantially convex surface which is opposite to the first concave surface, said two surfaces being continuous and joined to each other to form the aerodynamic profile of said blade extending from a foot at said base portion to the second end of said blade distal from said base portion, wherein each closed curve is substantially parallel to said base portion and has a maximum thickness determined by a maximum distance between said first surface and said second surface, said maximum thickness of each closed curve, along the height of the blade in the axial direction of the blade, having a non-linearly variable trend decreasing at a higher rate from said base portion to a first predetermined height, then at a lower rate from the first predetermined height to a second predetermined height, and the second predetermined height being substantially half of the height of the blade.
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