| 摘要 |
<p>A gas turbine nozzle arrangement comprises an outer carrier ring (37), an inner carrier ring (39), and nozzle segments each having an outer platform (25) forming an outer wall segment of a flow channel for the hot combustion gas, an inner platform (27) forming an inner wall segment of a flow channel for the hot combustion gas, and at least one guide vane (17) extending between the outer platform (25) and the inner platform (27). The outer platform (25) has an axially facing outer platform surface (43) located in axial opposition and at a distance to the axially facing outer carrier ring surface (49) and/or the inner platform (27) has an axially facing inner platform surface located in axial opposition and at a distance to the axially facing inner carrier ring surface. An outer seal strip (53) is inserted into an outer notch (51), the outer seal strip (53) being dimensioned such that it projects over the outer notch (51) and contacts the outer carrier ring surface (49), and/or an inner seal strip is inserted into an inner notch, the inner seal strip being dimensioned such that it projects over the inner notch and contacts the inner carrier ring surface.</p> |
