| 摘要 |
<p>The invention relates to a guide vane for rotary turbomachinery, in particular for a gas turbine stage. Said guide vane comprises a blade (3), an outer platform (4), which is radially connected to the blade (3) and comprises an upper face (42) that faces radially away from the blade (3). Said upper face is provided with a connection structure (5) for fixing the blade (1) to a support structure (2), the latter comprising lateral wall sections (51, 52, 53, 54) that protrude radially from said upper face (42) and delimit an inner cavity (6). At least some parts of the lateral wall sections are provided with a joint contour (7), which can be inserted into a receiving section (2') in the support structure (2), the shape of the latter being adapted to said contour. In addition, at least one sealing element (12) is provided between the connection structure (5) and the support structure (2).</p> |
