SEALED CONICAL-FLAT DOME FOR FLIGHT ENGINE COMBUSTORS

摘要

A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

主权项

1. A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising:
a liner at least partially defining a combustion chamber; an annular dome defining a first cavity and having a plurality of impingement holes; and a deflector plate defining a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate, wherein the annular dome and the deflector plate are positioned together to define a second cavity, the second cavity being in fluid communication with the first cavity through the plurality of impingement holes, and the second cavity being in fluid communication with the combustion chamber through the plurality of cooling holes.