초록 ▼

A turbomachine includes at least one rotor (6), at least one stator (7), and a casing (1), with the rotor (6) comprising several rotor blades (8) attached to a rotating shaft, and with the stator (7) being provided with stationary stator blades (9), the casing (1) being passed by a fluid flowing thr

A turbomachine includes at least one rotor (6), at least one stator (7), and a casing (1), with the rotor (6) comprising several rotor blades (8) attached to a rotating shaft, and with the stator (7) being provided with stationary stator blades (9), the casing (1) being passed by a fluid flowing through the rotor (6) and stator (7). Provision is made for the removal of fluid on at least one blade (8, 9) of a blade row of the rotor (6) and/or the stator (7) on non-axially symmetrical, aerodynamically critical locations on blade tip and annulus surfaces (SRO).

대표청구항 ▼

What is claimed is: 1. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, means for removal of the fluid provided at at least one blade of a blade row of the rotor

What is claimed is: 1. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, means for removal of the fluid provided at at least one blade of a blade row of the rotor on aerodynamically critical locations on at least one of a blade tip and annulus surfaces, wherein the at least one of the blade tip and annulus surfaces are provided in the form of at least one of surfaces on a hub and casing contours of the annulus, in an area of free blade ends, between a trailing edge plane HK and a plane which is located 25 percent of a meridional chord length Cm before a leading edge plane VK, the means for removal of the fluid being arranged on the annulus surfaces in a circumferentially non-uniform pattern, said pattern repeating in the circumferential direction. 2. A turbomachine in accordance with claim 1, comprising: at least one stator equipped with stationary stator blades which is passed by the fluid, wherein the means for removal of the fluid are also provided at at least one stator blade on aerodynamically critical locations on at least one of a blade tip and annulus surfaces. 3. A turbomachine in accordance with claim 2, comprising at least one arrangement for suction-side, intensity-variable fluid removal on at least one blade of a blade row of the stator. 4. A turbomachine in accordance with claim 2, comprising: means for removal of the fluid provided on at least one blade of a stator row, which means are distributed on a blade suction side over a defined area in a meridional flow direction. 5. A turbomachine in accordance with claim 4, wherein the means for removal of the fluid are arranged such that a meridional extension thereof in meridional flow line-orthogonal direction decreases towards at least one of wall of the annulus. 6. A turbomachine in accordance with claim 5, wherein the fluid is discharged via flow paths on a periphery of the annulus. 7. A turbomachine in accordance with claim 5, wherein the fluid is discharged via at least one of flow paths within the blade and components surrounding the blade. 8. A turbomachine in accordance with claim 7, wherein the fluid is discharged in free flow. 9. A turbomachine in accordance with claim 7, comprising at least one restrictor unit arranged in a flow path of the fluid led away from the annulus. 10. A turbomachine in accordance with claim 2, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 11. A turbomachine in accordance with claim 2, wherein the blade tip and annulus surfaces are provided in the form of at least one of surfaces on a hub and casing contours of the annulus, with firm connection to the blade, between a trailing edge plane HK and a plane which is located 25 percent of a meridional blade chord length Cm before a leading edge plane VK. 12. A turbomachine in accordance with claim 1, wherein the blade tip and annulus surfaces are provided in the form of at least one of surfaces on a hub and casing contours of the annulus, with firm connection to the blade, between a trailing edge plane HK and a plane which is located 25 percent of a meridional blade chord length Cm before a leading edge plane VK. 13. A turbomachine in accordance with claim 1, wherein the means for removal of the fluid are provided on free blade ends, facing at least one of a hub and a casing contour of the annulus. 14. A turbomachine in accordance with claim 1, wherein the fluid is completely discharged from the turbomachine. 15. A turbomachine in accordance with claim 1, wherein the fluid is returned to the turbomachine. 16. A turbomachine in accordance with claim 1, wherein the fluid is discharged via at least one slot. 17. A turbomachine in accordance with claim 1, wherein the fluid is discharged via at least one row of holes. 18. A turbomachine in accordance with claim 1, wherein the fluid is discharged via at least one ramming inlet. 19. A turbomachine as in claim 1, wherein the means for removal of the fluid are in the form of at least one interrupted circumferential slot. 20. A turbomachine as in claim 1, wherein the means for removal of the fluid are in the form of at least one continuous circumferential slot which varies in its meridional positioning around a circumference of the annulus surfaces. 21. A turbomachine as in claim 1, wherein the means for removal of the fluid are in the form of at least one pattern of repeating holes. 22. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, at least one stator equipped with stationary stator blades which is passed by the fluid, means for removal of the fluid provided at at least one stator blade on aerodynamically critical locations, wherein the means for fluid removal is provided on at least one stator free blade end, facing at least one of a hub and a casing contour of the annulus. 23. A turbomachine in accordance with claim 22, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 24. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, at least one stator equipped with stationary stator blades which is passed by the fluid, means for removal of the fluid provided on at least one blade of a stator row, which means are distributed on a blade side over a defined area in a meridional flow direction, wherein the defined area has a meridional streamwise extent which is at a maximum at a given blade height and which decreases from the maximum as the defined area extends toward at least one end of the blade, wherein at the maximum meridional streamwise extent, the means for removal of fluid includes a plurality of openings spaced apart from one another along the meridional flow direction. 25. A turbomachine in accordance with claim 24, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 26. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, means for removal of the fluid provided at at least one blade of a blade row of the rotor on aerodynamically critical locations, wherein the means for fluid removal is on at least one rotor free blade end, facing at least one of a hub and a casing contour of the annulus. 27. A turbomachine in accordance with claim 26, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 28. A turbomachine comprising: at least one stator equipped with stationary stator blades which is passed by a fluid, a casing which is passed by the fluid flowing through the stator, means for removal of the fluid provided at at least one blade of a blade row of the stator on aerodynamically critical locations on at least one of a blade tip and annulus surfaces, wherein the at least one of the blade tip and annulus surfaces are provided in the form of at least one of surfaces on a hub and casing contours of the annulus, in an area of free blade ends, between a trailing edge plane HK and a plane which is located 25 percent of a meridional chord length Cm before a leading edge plane VK, the means for fluid removal being arranged on the annulus surfaces in a circumferentially non-uniform pattern, said pattern repeating in the circumferential direction. 29. A turbomachine in accordance with claim 28, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 30. A turbomachine as in claim 28, wherein the means for removal of the fluid are in the form of at least one interrupted circumferential slot. 31. A turbomachine as in claim 28, wherein the means for removal of the fluid are in the form of at least one continuous circumferential slot which varies in its meridional positioning around a circumference of the annulus surfaces. 32. A turbomachine as in claim 28, wherein the means for removal of the fluid are in the form of at least one pattern of repeating holes. 33. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, means for removal of the fluid provided at at least one blade of a blade aerodynamically critical locations on at least one of a blade tip and annulus surfaces, wherein the at least one of the blade tip and annulus surfaces are provided in the form of at least one of surfaces on a hub and casing contours of the annulus, with firm connection to the blade, between a trailing edge plane HK and a plane which is located 25 percent of a meridional blade chord length Cm before a leading edge plane VK, the means for removal of the fluid including at least one aperture positioned within a blade passage between adjacent blades and being more centered towards a suction side than a pressure side of the adjacent blades, the aperture having a maximum width that does nor exceed 15% of an exit spacing of the adjacent blades. 34. A turbomachine in accordance with claim 33, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 35. A turbomachine comprising: at least one stator equipped with stationary stator blades which is passed by a fluid, a casing which is passed by the fluid flowing through the stator, means for removal of the fluid provided at at least one blade of a blade row of the stator on aerodynamically critical locations on at least one of a blade tip and annulus surfaces, wherein the at least one of the blade tip and annulus surfaces are provided in the form of at least one of surfaces on a hub and casing contours of the annulus, with firm connection to the blade, between a trailing edge plane HK and a plane which is located 25 percent of a meridional blade chord length Cm before a leading edge plane VK, the means for removal of the fluid including at least one aperture positioned within a blade passage between adjacent blades and being more centered towards a suction side than a pressure side of the adjacent blades, the aperture having a maximum width that does not exceed 15% of an exit spacing of the adjacent blades. 36. A turbomachine in accordance with claim 35, comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before or within a bladed space of the same blade areas of the rotor/stator. 37. A turbomachine comprising: at least one rotor, with the rotor comprising several rotor blades attached to a rotating shaft, a casing which is passed by a fluid flowing through the rotor, at least one stator equipped with stationary stator blades which is passed by the fluid, means for removal of the fluid provided at at least one blade of at least one of the rotor and the stator on aerodynamically critical locations on at least one of a blade tip and annulus surfaces, and further comprising, simultaneously with the means for removal of the fluid, means for fluid supply positioned at least one of before and within a bladed space of the same blade areas of the rotor/stator.