http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2018100433-A1

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filingDate 2016-10-07^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_42dd8f14882c697115f01cb493b290e0
publicationDate 2018-04-12^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber US-2018100433-A1
titleOfInvention Component assembly for a gas turbine engine
abstract A component assembly for a gas turbine engine having a combustor and defining a core air flowpath includes a first wall and a second wall. The first wall is configured for at least partially defining the core air flowpath at a location downstream of a combustion chamber defined by the combustor of the gas turbine engine. Additionally, the second wall is also configured for at least partially defining the core air flowpath at a location downstream of the combustion chamber, and is located opposite the core air flowpath of the first wall. The second wall includes a plurality of fins extending towards the first wall along the radial direction and spaced along the circumferential direction.
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