Output stage for an axial-flow turbine
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United States of America Patent
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Aug 8, 2000
Grant Date -
N/A
app pub date -
Nov 12, 1998
filing date -
Nov 17, 1997
priority date (Note) -
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status (Latency Note)
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Abstract
An output stage of an axial-turbine having a high channel divergence has a row of curved vanes and a row of narrowed twisted blades. The curved vanes include, in an axial direction, a positive sweep at their rotor-side end, head and a negative sweep at their stator-side end, with respect to a run of the rotor-side channel boundary. In an area of a stator-side channel boundary a negative sweepback predominates, so that between the curved vanes and the twisted blades an axial diffuser that steadily widens toward the stator-side channel boundary is formed. As a result, an increasing delay of an axial component of a flow agent can occur. The negative sweep at the stator-side end is formed such that at least one of a vane trailing edge and a vane leading edge is directed substantially perpendicularly to the stator-side channel boundary.
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