Blade structure in a gas turbine
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United States of America Patent
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Jun 12, 2007
Grant Date -
Jan 20, 2005
app pub date -
Aug 9, 2004
filing date -
Jan 12, 2001
priority date (Note) -
In Force
status (Latency Note)
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Abstract
In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.
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