Gas flow path for a gas turbine engine
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United States of America Patent
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Mar 14, 2017
Grant Date -
Aug 20, 2015
app pub date -
Feb 20, 2014
filing date -
Feb 20, 2014
priority date (Note) -
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Abstract
A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.
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