Turbine cooling vane of gas turbine engine
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United States of America Patent
Stats
-
Nov 27, 2007
Grant Date -
Sep 21, 2006
app pub date -
Mar 3, 2004
filing date -
Nov 21, 2003
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a cooling passageway 12 formed inside thereof, making the cooling air flow therein. Film-cooling holes 13 penetrate from an inner wall surface 111 to an external wall surface 112 and form a cooling film. An impingement cooling member 2 has a multiple number of small holes 21 ejecting the cooling air. A gap t made by the inner wall surface 111 and the impingement cooling member 2 has a sealing portion 14 mounted thereon which divides the gap in a blade chord direction.
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