Combustor Assembly
AssigneeGeneral Electric Company
InventorsDavid Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
Life of this patent
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Abstract
A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.
Claims20
A combustor assembly for a gas turbine engine defining a circumferential direction, the combustor assembly comprising:
- a liner;
- and
- a combustor dome, the combustor dome and the liner together at least in part defining a combustion chamber, the combustor dome comprising a transition potion and a forward wall, the transition portion defining an angle greater than 90 degrees and less than 180 relative to the forward wall and extending from the forward wall towards the liner.
A combustor assembly for a gas turbine engine defining a circumferential direction, the combustor assembly comprising:
- a liner;
- and
- a combustor dome, the combustor dome and the liner together at least in part defining a combustion chamber, the combustor dome comprising a transition potion and a forward wall, the forward wall defining a length, the transition portion comprising a flat extending from the forward wall towards the liner and defining a radius of curvature between the forward wall and the flat of the transition portion between about two percent and about twenty percent of the length of the forward wall.
Dependencies are inferred from the claim text.