Gas turbine combustor, particularly for an aircraft engine
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United States of America Patent
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Nov 2, 2004
Grant Date -
Nov 7, 2002
app pub date -
Apr 9, 2002
filing date -
Apr 10, 2001
priority date (Note) -
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Abstract
A gas turbine combustor, in particular for an aircraft engine, has at least one chamber, through which combustion gas flows in use, and which is defined by a lateral wall with channeling for feeding cooling air into the chamber and cooling the lateral wall; part of the channeling is defined by at least one double wall for guiding a relative stream of cooling air into the chamber in a tangential direction with respect to the lateral wall.
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