| 摘要 |
<p>The present invention relates to a radial turbomachine, comprising: a fixed casing (6); at least one rotor disc (2,2') installed in the casing (6) and rotatable in the casing (6) around a respective rotation axis (X-X); a plurality of annular rotor elements (3,22,23,24; 22,23) coaxial with the rotation axis (X-X), axially projecting from a front face (4,4') of the rotor disc (2,2') and/or from a rear face (9,9') of the rotor disc (2,2'); a plurality of annular fixed elements (13,25,27; 34) coaxial with the rotation axis (X-X), axially projecting from the casing (6) and each positioned in a radially external position with respect to a respective annular rotor element (3,22,23,24; 22,23); a plurality of sealing devices (28,29; 29,31; 32,33) radially interposed between at least some of said annular rotor elements (3,22,23,24; 22,23) and the respective annular fixed elements (13,25,27; 34). The annular rotor elements (3,22,23,24; 22,23) are radially movable between a first radially contracted configuration, when the turbomachine (1) is in a non-operative condition, wherein, at the sealing devices (28,29; 29,31; 32,33), the annular rotor elements (3,22,23,24; 22,23) are radially spaced from the respective annular fixed elements (13,25,27; 34), and a second radially expanded configuration under the action of the centrifugal force and/or of the heat, when the turbomachine (1) is operating, wherein, at the sealing devices (28,29; 29,31; 32,33), the annular rotor elements (3,22,23,24; 22,23) are close to the respective annular fixed elements (13,25,27; 34). In the second configuration the sealing devices (28,29; 29,31; 32,33) substantially prevent the passage of a working fluid between the annular rotor elements (3,22,23,24; 22,23) and the annular fixed elements (13,25,27; 34).</p> |
