Combustor assembly for a gas turbine engine
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.
1. A combustor assembly in a gas turbine engine, the gas turbine engine defining a circumferential direction, the combustor assembly comprising:
an outer liner;
an inner liner; and
a combustor dome having a hot side and a cold side,
wherein the combustor dome, the outer liner, and the inner liner together define a combustion chamber, the combustor dome comprising an outer transition portion, an inner transition portion, and a forward wall, the outer transition portion defining an angle greater than 90 degrees and less than 180 degrees relative to the forward wall and extending from the forward wall towards the outer liner, the inner transition portion defining an angle greater than 90 degrees and less than 180 degrees relative to the forward wall and extending from the forward wall towards the inner liner,
wherein the outer transition portion defines a first flat extending away from the forward wall, the inner transition portion defines a second flat extending away from the forward wall, the forward wall defines a length extending from the first flat to the second flat, a first radius of curvature of the combustor dome is defined between the first flat and the forward wall, a second radius of curvature of the combustor dome is defined between the second flat and the forward wall, and the first radius of curvature is between two percent and twenty percent of the length of the forward wall and/or the second radius of curvature is between two percent and twenty percent of the length of the forward wall, and
wherein the combustor dome defines a plurality of cooling holes extending through the outer transition portion and/or the inner transition portion from the cold side to the hot side to allow for a flow of cooling air.
2. The combustor assembly of claim 1 , wherein the combustor dome defines a plurality of openings for receiving a respective plurality of fuel-air injector hardware assemblies.
3. The combustor assembly of claim 1 , wherein the combustor dome is formed integrally of a single continuous piece of material.
4. The combustor assembly of claim 1 , wherein the combustor dome extends continuously along the circumferential direction to define an annular shape.
5. The combustor assembly of claim 1 , wherein the combustor dome is formed of a ceramic matrix composite material.
6. The combustor assembly of claim 1 , wherein the combustor dome is formed integrally with the liner, the combustor dome and the liner being formed of a ceramic matrix composite material.
7. The combustor assembly of claim 6 , wherein the combustor dome and liner extend along the circumferential direction to define an annular shape.