Combustor assemblies for use in turbine engines and methods of assembling same
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United States of America Patent
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Jun 23, 2020
Grant Date -
Jan 11, 2018
app pub date -
Jul 6, 2016
filing date -
Jul 6, 2016
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Abstract
A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces. The combustor assembly also includes a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve. The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface.
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