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US 9,429,074 B2Granted
Aerodynamic swept vanes for fuel injectors
AssigneeROLLS-ROYCE plc
InventorsBrandon Phillip Williams, Kevin Eugene Thompson
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Abstract
A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.
Claims12
A fuel nozzle for a gas turbine engine comprising:
- a) a nozzle body having a longitudinal axis;
- b) an annular air passage defined within the nozzle body;
- and
- c) a plurality of circumferentially spaced apart axially extending aerodynamic swirl vanes disposed within the annular air passage, each of the swirl vane having an axially swept cross-sectional profile along the radial extent thereof,
- wherein the cross-sectional profile of each of the swirl vane has proportions that vary along the radial extent of the swirl vane.
2 more elements
Dependencies are inferred from the claim text.