Combustion section for a turbine engine
AssigneeGeneral Electric Company
InventorsJames Shealy, Pradeep Naik, Marco Venturato, Shamil Shailesh Patel, Kevin Reed, Bernard Gustav Knolle
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Abstract
A combustion section for a turbine engine, the combustion section comprising a wall at least partially forming a combustion chamber and a fuel nozzle extending through a respective portion of the wall, the fuel nozzle having a fuel nozzle body defining a central channel and a fuel nozzle centerline, the central channel opening to the combustion chamber at a fuel nozzle outlet, a swirler provided along the fuel nozzle body and extending into the central channel, the swirler having a helical vane wrapped circumferentially about the fuel nozzle centerline.
Claims20
A combustion section for a turbine engine, the combustion section comprising:
- a wall at least partially forming a combustion chamber;
- and
- a fuel nozzle extending through a respective portion of the wall, the fuel nozzle having:
- a fuel nozzle body defining a central channel and a fuel nozzle centerline, the central channel opening to the combustion chamber at a fuel nozzle outlet;
- and
- a swirler provided along the fuel nozzle body and extending into the central channel, the swirler having a helical vane wrapped circumferentially about the fuel nozzle centerline greater than or equal to π/2 radians between a first end and a second end, axially opposing the first end.
Dependencies are inferred from the claim text.