CPC F23R 3/60 (2013.01) [F23R 3/06 (2013.01); B33Y 80/00 (2014.12); F23R 2900/00012 (2013.01); F23R 2900/00017 (2013.01); F23R 2900/00018 (2013.01)] | 17 Claims |
1. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising:
a forward liner segment;
an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward liner segment and the aft liner segment at least partially defining a combustion chamber; and
an intermediate member disposed at least partially between the forward liner segment and the aft liner segment and extending in the circumferential direction, the intermediate member comprising:
a feature configured to interface with a radially outer surface, with respect to the longitudinal centerline, of the forward liner segment or the aft liner segment; and
a fence extending into the combustion chamber in the radial direction, with respect to the longitudinal centerline, and continuously in the circumferential direction.
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