Patent ID: 11959643
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 0:
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.