Combustor assembly for a turbo machine
AssigneeGeneral Electric Company
InventorMackenzie Christopher Hock
Life of this patent
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Abstract
A turbo machine including an annular liner assembly defining a reverse flow combustion chamber is generally provided. The liner assembly includes a first piece defining an inner diameter (ID) combustor inlet portion, an outer diameter (OD) combustor outlet portion, and an outer diameter turbine shroud portion, in which the first piece defines a substantially solid volume between the inner diameter combustor inlet portion and the outer diameter combustor outlet portion.
Claims20
A turbo machine, the turbo machine defining a radial direction, the turbo machine comprising:
- an annular liner assembly defining a reverse flow combustion chamber therewithin, the liner assembly comprising a first piece and a second piece, the first piece defining an inner diameter (ID) combustor inlet portion, an outer diameter (OD) combustor outlet portion, and an outer diameter (OD) turbine shroud portion, wherein the first piece defines a substantially solid volume between the ID combustor inlet portion and the OD combustor outlet portion, the annular liner assembly further comprising a dome assembly and a deflector wall of the dome assembly, the deflector wall positioned at an inlet of the dome assembly of the annular liner assembly, the deflector wall extending along the radial direction between the first piece and the second piece, and the deflector wall aligned along the radial direction with at least a portion of a first turbine blade.
A gas generator for a gas turbine engine defining a radial direction, the gas generator comprising:
- an annular liner assembly defining a reverse flow combustion chamber therewithin, the annular liner assembly comprising a first piece and a second piece, the first piece defining an inner diameter (ID) combustor inlet portion, an outer diameter (OD) combustor outlet portion, and an outer diameter (OD) turbine shroud portion together formed integrally, wherein the first piece is approximately 95% or greater of a solid volume of a ceramic matrix composite material between the ID combustor inlet portion and the OD combustor outlet portion, the annular liner assembly further comprising a dome assembly and a deflector wall of the dome assembly, the deflector wall positioned at an inlet of the dome assembly of the annular liner assembly, the defector wall extending along the radial direction between the first piece and the second piece, and the deflector wall aligned along the radial direction with at least a portion of a first turbine blade.
Dependencies are inferred from the claim text.