(57) The present disclosure relates to a combustor assembly 16 for a gas turbine engine
10, the combustor assembly 16 comprising: a combustor wall 30 defining a combustion
chamber 25 and comprising an opening periphery 33, the opening periphery 33 defining
a first opening 32; a sealing element 34 comprising an annular body 35, the annular
body 35 extending around a sealing element axis S and extending through the first
opening 32, the sealing element 34 further comprising a flange 38 extending radially
outward from the annular body 35 with respect to the axis S to a distal surface 58,
the flange 38 slidingly coupling the sealing element 34 and the combustor wall 30
and forming a seal or first partial seal between the sealing element 34 and the combustor
wall 30, the annular body comprising an outer surface 37 and an inner surface 36,
the inner surface 36 defining a second opening 49 configured to receive a fuel nozzle
40, wherein a first total clearance D1, D2 between the outer surface 37 and the opening periphery 33 in a first direction A
is greater than a second total clearance d1, d2 between the outer surface 37 and the opening periphery 33 in a second direction B
perpendicular to the first direction A such that the sealing element 34 is able to
slide relative to the combustor wall 30 by a greater extent in the first direction
A than in the second direction B.
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