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A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. Th

A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. The annular space communicates with ducts, arranged in the disk, for feeding the cooling air into the blades. A diverter unit is provided inside the annular space or so as to delimit the annular space on one side, so cooling air emerging from the nozzle units, before entering the ducts, is diverted on one side and foreign particles are centrifugally thrown into a radially outer part of the annular space and separated therefrom with a barrier-air fraction. The diverter unit has a surface region on which the stream impinges so it can be diverted radially outward through an angle greater than 90째.

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What is claimed is: 1. A device for separating foreign particles out of cooling air to be fed to rotor blades of a turbine, the device comprising: stationary nozzle units for feeding the cooling air to an annular space formed between wall parts of a turbine stator and a rotating wheel disk, the noz

What is claimed is: 1. A device for separating foreign particles out of cooling air to be fed to rotor blades of a turbine, the device comprising: stationary nozzle units for feeding the cooling air to an annular space formed between wall parts of a turbine stator and a rotating wheel disk, the nozzle units configured for directing the cooling air in a stream flowing in a circumferential direction inside the annular space; ducts communicating with the annular space for feeding the cooling air into the rotor blades, the ducts being arranged in the wheel disk; a diverter unit associated with the annular space and comprising a surface region; wherein the diverter unit is configured such that before the cooling air enters the ducts, foreign particles in the cooling air emerging from the nozzle units are centrifugally moved into a radially outer part of the annular space and are separated out of the annular space together with a barrier-air fraction of the cooling air; and wherein the surface region of the diverter unit is configured such that when the stream of cooling air passes through the nozzle units and impinges the surface region, the stream of cooling air is diverted by the surface region in a radially outward direction through an angle greater than 90째. 2. The device of claim 1, wherein the nozzle units feed the cooling air directly to the annular space. 3. The device of claim 1, wherein the nozzle units feed the cooling air indirectly to the annular space. 4. The device of claim 1, wherein the annular space is delimited on the radially outer part and an inner side by sections of axially protruding webs of the turbine stator and of the wheel disk, the webs having a circumferentially overlapping arrangement and forming locking seals with respect to spaces in the turbine in which the pressure is lower than in the annular space, and wherein the locking seals include a radially outer locking seal disposed such that the barrier-air fraction together with the foreign particles enters the turbine duct therethrough. 5. The device of claim 4, wherein the radially outer locking seal is formed as a labyrinth seal for spatially demarcating the annular space from a radially outer turbine duct. 6. The device of claim 4, wherein the diverter unit has a contour that ends freely in the annular space, serves as a flow detachment contour for the stream of cooling air diverted radially outward, and permits further flow to propagate without obstacle in a direction of the radially outer locking seal with respect to the barrier-air fraction mixed with foreign particles. 7. The device of claim 6, wherein the flow detachment contour is followed, as seen in the direction of flow of the barrier-air fraction, by an open flow region unobstructed by flow obstacles. 8. The device of claim 6, wherein a through-opening is provided adjacent to the freely ending contour on the radially outer part for permit cooling air to be fed into the ducts. 9. The device of claim 8, wherein the through-opening is delimited by the freely ending contour of the diverter unit and a web of the wheel disk, and the web is set back from the flow of cooling air over the freely ending contour. 10. The device of claim 1, wherein the diverter unit is fixedly connected to the turbine stator, and the surface region is spaced from the nozzle units. 11. The device of claim 1, wherein the nozzle units each comprise a nozzle duct with a duct longitudinal axis, the axis defining a direction of flow of the stream of cooling air and being oriented perpendicular to a radial direction of the wheel disk that rotates about another axis, and wherein the surface region is configured so that the duct longitudinal axis includes a radially outwardly open angle of greater than 90째 with the surface region. 12. The device of claim 11, wherein each duct longitudinal axis is inclined radially and the surface region is oriented so that each duct longitudinal axis includes a radially outwardly open angle of greater than 90째 with the surface region. 13. The device of claim 12, wherein the surface region is oriented parallel to the radial direction. 14. The device of claim 12, wherein the surface region is oriented at an inclination to the radial direction. 15. The device of claim 1, wherein the diverter unit is configured as an annular component and further comprises a cross-section with an angled profile, a connecting web for fixedly joining the diverter unit to the turbine stator, and a section that includes the surface region and projects beyond the nozzle unit at a distance therefrom with the freely ending contour oriented radially outward. 16. The device of claim 15, further comprising a transition contour provided between the connecting web and the section that includes the surface region. 17. The device of claim 1, wherein the diverter unit is fixedly connected to the rotating wheel disk, and the surface region is disposed in spaced, opposing relation to the nozzle unit. 18. The device of claim 17, wherein the diverter unit is connected to a radially outer web of the wheel disk, and at least one through-opening is provided in a radially outer region of the diverter unit for permitting cooling air to be fed into the ducts. 19. The device of claim 18, wherein a freely ending contour projects axially beyond the through-opening and is provided directly adjacent to the through-opening on a radially inner side, the contour serving as a flow detachment contour for the stream of cooling air diverted radially outward, and permits further flow to propagate without obstacle in a direction of the radially outer locking seal with respect to the barrier-air fraction mixed with foreign particles. 20. The device of claim 19, wherein the flow detachment contour is followed, as seen in the direction of flow of the barrier-air fraction, by an open flow region unobstructed by flow obstacles. 21. The device of claim 17, wherein the diverter unit further comprises a radially inner, free end region that together with a web of the turbine stator encloses an intermediate gap for cooling air to pass in order also to be fed into the ducts. 22. The device of claim 17, wherein the diverter unit further comprises at least one fin-like element radially facing the annular space and having a surface oriented perpendicular to the direction of rotation of the wheel disk. 23. The device of claim 22, wherein a plurality of fin-like elements divide the diverter unit into sectors. 24. The device of claim 1, wherein the turbine is part of a gas turbine arrangement. 25. A device for separating foreign particles out of cooling air to be fed to rotor blades of a turbine, the device comprising: stationary nozzle units for feeding the cooling air to an annular space formed between wall parts of a turbine stator and a rotating wheel disk, the nozzle units configured for directing the cooling air in a stream flowing in a circumferential direction inside the annular space; ducts communicating with the annular space for feeding the cooling air into the rotor blades, the ducts being arranged in the wheel disk; a diverter unit associated with the annular space; wherein the diverter unit is configured such that before the cooling air enters the ducts, foreign particles in the cooling air emerging from the nozzle units are centrifugally moved into a radially outer pan of the annular space and are separated out of the annular space together with a barrier-air fraction of the cooling air; and wherein the nozzle units each comprise a nozzle duct with a duct longitudinal axis that determines a direction of flow of the stream of cooling air and is inclined radially to direct the stream of cooling air moving past the nozzle duct radially outward. 26. The device of claim 25, wherein the diverter unit is fixedly connected to the turbine stator and together with the wall parts of the turbine stator delimits an annular chamber downstream from a direction of flow through the nozzle unit, wherein the diverter unit further comprises at least two through-openings leading to the annular space, with a first through-opening arranged on a radially outer side and a second through-opening arranged on a radially inner side, and wherein the first through-opening is arranged to be aligned with the duct longitudinal axis. 27. The device of claim 26, wherein the annular chamber comprises a substantially radially oriented flow duct, which in a radially outward direction opens out into the region of the stream of cooling air that passes through the nozzle duct and is directed radially outward, and which on the radially inner side is connected to the second through-opening. 28. The device of claim 26, wherein a flow duct is provided upstream of the second though-opening, as seen in the direction of flow and the flow duct has a flow-duct longitudinal axis that is inclined radially outward by an angle γ, wherein 0째<γ≦ 35째. 29. The device of claim 25, wherein proximate the first through-opening, the diverter unit comprises a contour that narrows in a through-flow direction, with a decrease in cross-section of flow. 30. The device of claim 25, wherein the duct longitudinal axis is radially inclined at an angle β with respect to an axis of rotation of the wheel disk, wherein 10째≦β ≦60째. 31. The device of claim 25, wherein the duct longitudinal axis is radially inclined at an angle β with respect to an axis of rotation of the wheel disk, wherein 40째≦β ≦50째. 32. The device of claim 25, wherein the duct longitudinal axis of each of the nozzle units includes an angle δ with an axis of rotation of the wheel disk within a tangential plane at the location of the nozzle unit, wherein δ>0째. 33. The device of claim 25, wherein the nozzle units feed the cooling air directly to the annular space. 34. The device of claim 25, wherein the nozzle units feed the cooling air indirectly to the annular space. 35. The device of claim 25, wherein the turbine is part of a gas turbine arrangement. 36. A device for separating foreign particles out of cooling air to be fed to rotor blades of a turbine, the device comprising: stationary nozzle units for feeding the cooling air to an annular space formed between wall parts of a turbine stator and a rotating wheel disk, the nozzle units configured for directing the cooling air in a stream flowing in a circumferential direction inside the annular space; ducts communicating with the annular space for feeding the cooling air into the rotor blades, the ducts being arranged in the wheel disk; a diverter unit associated with the annular space and comprising an arcuate surface region configured to direct the cooling air when impinging thereon through a change in angular direction greater than 90째; wherein the diverter unit is configured such that before the cooling air enters the ducts, foreign particles in the cooling air emerging from the nozzle units are centrifugally moved into a radially outer part of the annular space and are separated out of the annular space together with a barrier-air fraction of the cooling air.