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US 2013/0255261 A1Published application
Swirler for combustion chambers
AssigneeGeneral Electric Company
InventorsBassam Sabry Mohammad Abdelnabi, Ahmed Mostafa Elkady
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Abstract
A combustion swirler is provided. The combustion swirler includes multiple vanes axially extending from an annular first body portion of the combustion swirler. The combustion swirler also includes an annular second body portion enclosing the multiple vanes for directing a flow of combustion fluid. Each of the vanes comprises an aerodynamic blade body comprising a leading edge with a plurality of first tubercles and a trailing edge with a plurality of second tubercles.
Claims17
A combustion swirler comprising:
- a plurality of vanes axially extending from an annular first body portion of the combustion swirler,
- an annular second body portion of the swirler enclosing the plurality of vanes for directing a flow of combustion fluid;
- wherein each of the vanes comprises an aerodynamic blade body comprising a leading edge with a plurality of first tubercles and a trailing edge with a plurality of second tubercles.
A gas turbine comprising:
- a combustion swirler located upstream of a combustion region of the gas turbine, the combustion swirler comprising:
- a plurality of vanes axially extending from an annular first body portion of the combustion swirler,
- an annular second body portion of the combustion swirler enclosing the plurality of vanes for directing a flow of combustion fluid;
- wherein each of the vanes comprises an aerodynamic blade body having a leading edge with a plurality of first tubercles and a trailing edge with a plurality of second tubercles.
1 more element
Dependencies are inferred from the claim text.