Gas turbine engine combustor with lobed, three dimensional contouring
AssigneeGeneral Electric Company
InventorsDonald Mark Bailey, Jonathan Dwight Berry, Luis Manuel Flamand, Kwanwoo Kim, Patrick Benedict Melton, Robert Joseph Rohrssen, John Drake Vanselow
Life of this patent
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Abstract
A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
Claims14
A gas turbine engine combustor, comprising:
- an array of fuel nozzles including a central fuel nozzle and outer fuel nozzles spaced about the central fuel nozzle;
- a combustion casing assembly disposed about the array of fuel nozzles;
- and
- an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles,
- the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring relating to each of the outer fuel nozzles and extending radially inwardly between adjacent outer fuel nozzles to a perimeter of the central fuel nozzle.
A gas turbine engine combustor, comprising:
- a central fuel nozzle;
- a plurality of outer fuel nozzles arrayed substantially uniformly about the central fuel nozzle;
- a combustion casing assembly disposed about the array of outer fuel nozzles;
- and
- an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles,
- the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring relating to each of the plurality of outer fuel nozzles.
A gas turbine engine combustor with a single component lobed insert, the gas turbine engine combustor comprising:
- a central fuel nozzle;
- an array of fuel nozzles arrayed substantially uniformly about the central fuel nozzle;
- an end cover;
- a combustion casing assembly connected to the end cover and disposed about the array of fuel nozzles;
- an end cap assembly disposed within the combustion casing assembly to define an axis-symmetric annulus through which fluid travels into each of the fuel nozzles;
- and
- an insert connected to an aft face of the end cover within the combustion casing assembly,
- the insert including a medallion shaped body having an aft face formed with lobed, three-dimensional contouring comprising scallop sections relating to each of the fuel nozzles and extending radially inwardly between adjacent outer fuel nozzles to a perimeter of the central fuel nozzle.
Dependencies are inferred from the claim text.