| 摘要 |
<p>The present invention regards a radial turbomachine, comprising: a fixed case (6); at least one rotor disc (2, 2', 2") installed in the case (6) and having rotor blades (3, 3', 3") mounted on a front face (4, 4', 4") thereof; a plurality of elements (25, 35) projecting from the case (6) and terminating in proximity to the rotor disc (2, 2', 2"), wherein the projecting elements (25, 35) comprise seal elements (34) acting against the rotor disc (2, 2', 2") that are operatively active on a rear face (9, 9', 9") of the rotor disc (2, 2', 2") or stator blades (13) radially interposed between the rotor blades (3) of the rotor disc (2); at least one support plate (17, 37) bearing the projecting elements (25, 35) and installed in the case (6). The support plate (17, 37) is radially extended across from the rotor disc (2, 2', 2") and comprises a plurality of first circular portions (29) concentric with a rotation axis (X-X) of the rotor disc (2) and a plurality of second circular portions (30) radially interposed between the first circular portions (29). At least several of the first circular portions (29) bear the projecting elements (25, 35) and the second circular portions (30) are more deformable, along radial directions, than the first circular portions (29) in a manner so as to allow relative movements between the first circular portions (29) when the support plate (17, 37) is subjected to the action of thermal gradients.</p> |
