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