摘要 |
PROBLEM TO BE SOLVED: To provide a rotor blade cooling structure of a gas turbine increasing the peripheral speed of secondary air flowing in a front seal without energy loss and thereby considerably reducing energy loss. SOLUTION: The rotor blade cooling structure includes a pre-swirl duct 12 converting the secondary air 6 to a swirl flow 7 and injecting it to a front seal side, and an acceleration duct 14 stationarily lying between the pre-swirl duct 12 and the front seal 3 and injecting the swirl flow 7 to the front seal side while reducing a swirl radius of the same, and increases the circumferential speed of the swirl flow 7 corresponding to a reduction of the swirl radius without energy loss by the law of conservation of angular momentum. COPYRIGHT: (C)2011,JPO&INPIT
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