A turbomachine ( 1 ), in particular a turbine or compressor, includes a rotor ( 2 ) which has at least one moving blade row ( 4 ) with a plurality of moving blades ( 5 ), and a stator ( 3 ) which has at least one guide vane row ( 6 ) with a plurality of guide vanes ( 7 ), at least in one of the blade or vane rows ( 4, 6 ) all the blades or vanes ( 5, 7 ) each having a shroud plate ( 10 ). In order to simplify the maintenance of the turbo-machine ( 1 ), the shroud plates ( 10 ) are separate components with respect to the respective blade or vane ( 5, 7 ) and are mounted on the respective blade or vane ( 5, 7 ), shroud plates ( 10 ) adjacent in the circumferential direction ( 9 ) being coupled to one another for the transmission of tensile forces in the circumferential direction ( 9 ).
1. A turbomachine comprising:
a rotor having at least one moving blade row with a plurality of moving blades;
a stator having at least one guide vane row with a plurality of guide vanes;
at least in one of at least one moving blade row and at least one guide vane row, all the blades or vanes each having a shroud plate;
a securing device securing each shroud plate to an associated blade or vane axially, circumferentially, or both, against relative adjustment;
wherein the shroud plates are separate components from the respective blade or vane and are mounted on the respective blade or vane to be radially movable with respect to said blade or vane;
wherein circumferentially adjacent shroud plates are directly coupled to one another for the transmission of tensile forces in the circumferential direction; and
wherein the shroud plates are configured and arranged to form a self-supporting annularly closed ring when the turbo machine is rotating;
wherein each shroud plate is mounted on an associated blade or vane to be fixed axially, fixed circumferentially with respect to an associated blade or vane, or both;
wherein each shroud plate includes a securing orifice and each securing device has at least one securing member which is arranged radially movably on a respective blade or vane;
wherein each shroud plate contains, for each securing member, at least one desecuring orifice through which the securing member can be driven out of the securing orifice and into the associated blade or vane.
2. The turbomachine as claimed in claim 1 , wherein adjacent shroud plates, in the region of their mutual coupling, in the circumferential direction are positively or non-positively in engagement with one another, or are fastened to one another.
3. The turbomachine as claimed in claim 1 , wherein each shroud plate, on its circumferential end regions, includes a first holding contour at one end and a second holding contour at the other end; and
wherein, in a mounted state, the first holding contour of each shroud plate is in engagement with the second holding contour of each adjacent shroud plate for the transmission of tensile forces.
4. The turbomachine as claimed in claim 3 , wherein the first holding contour of each shroud plate is in engagement positively or non-positively with the second holding contour of each adjacent shroud plate for the transmission of tensile forces.
5. The turbomachine as claimed in claim 1 , wherein each shroud plate contains cooling duct structures for cooling the shroud plate when the turbomachine is in operation, which cooling duct structures, when in a mounted state of the shroud plate, communicate with cooling duct structures of an associated blade or vane.
6. The turbomachine as claimed in claim 1 , wherein each shroud plate includes, on a side facing away from an associated blade or vane, a sealing structure configured and arranged to axially seal the blade or vane row when the turbomachine is in operation.
7. The turbomachine as claimed in claim 1 , wherein the shroud plates are configured and arranged so that, in the mounted state, each of the shroud plates is coupled to adjacent shroud plates for the transmission of tensile forces in the circumferential direction.
8. The turbomachine as claimed in claim 7 , wherein said turbomachine comprises a turbine or a compressor.
9. The turbomachine as claimed in claim 1 , wherein said turbomachine comprises a turbine or a compressor.
10. The turbomachine as claimed in claim 1 , wherein each shroud plate is nondestructively, releasably mounted on an associated blade or vane.
11. The turbomachine as claimed in claim 1 , wherein each securing member, at least when the turbomachine is in operation, penetrates radially into the securing orifice.
12. The turbomachine as claimed in claim 1 , wherein each securing member includes and is prestressed by a securing spring for penetration into the securing orifice.
13. The turbomachine as claimed in claim 1 , wherein each securing member comprises a bolt.