Turbine impeller disk with cooling air channels
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United States of America Patent
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Feb 8, 2000
Grant Date -
N/A
app pub date -
Feb 6, 1998
filing date -
Feb 13, 1997
priority date (Note) -
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Abstract
In connection with a turbine rotor disk in whose disk grooves air-cooled turbine blades have been inserted, at least two cooling air channels, respectively extending from the same disk front face, terminate in each disk groove. The outlet openings of two cooling air channels in each disk groove preferably lie essentially next to each other in a common sectional plane, which is normal to the disk axis. Because of this it is possible to supply a larger cooling air flow without drastically increasing the weakening, or respectively the stress of the disk in the groove bottom.
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