Tunable transition duct side seals in a gas turbine engine
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United States of America Patent
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Sep 1, 2015
Grant Date -
Apr 12, 2012
app pub date -
Oct 8, 2010
filing date -
Oct 8, 2010
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Abstract
A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.
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