Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
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United States of America Patent
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Nov 10, 2020
Grant Date -
Aug 23, 2018
app pub date -
Feb 23, 2017
filing date -
Feb 23, 2017
priority date (Note) -
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Abstract
A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.
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