Gas turbine airfoil leading edge cooling
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United States of America Patent
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Nov 21, 2006
Issued Date -
N/A
app pub date -
May 27, 2004
filing date -
May 27, 2004
priority date (Note) -
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Abstract
A gas turbine airfoil (34) includes sequentially connected, radially displaced chambers (e.g., 46, 58) within the airfoil. A cooling fluid supply chamber (46) is disposed within a first section (48) of a leading edge portion (36) of the airfoil and receives a cooling fluid flow (50). The cooling fluid supply chamber is in fluid communication with a first leading edge impingement chamber (52) disposed against a backside (44) of the leading edge portion. A discharge chamber (58) in serial fluid communication with the first impingement chamber is disposed radially outward of the first impingement chamber and within a second section (60) of the leading edge portion. A second leading edge impingement chamber (62) in fluid communication with the discharge chamber is disposed against a backside (64) of the leading edge portion in the second section. The chambers may be arranged to limit centrifugal force-induced pressure buildup in the respective chambers.
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