Swirler arrangement for combustor of gas turbine engine
Patent
·
OSTI ID:6948177
This patent describes a combustion apparatus for a gas turbine engine comprising; (a) an annular combustor structure including a plurality of annularly displaced combustion zones; (b) a fuel nozzle extending into each of the combustion zones for supplying fuel to the combustion zones; (c) a swirler supported on each fuel nozzle, each of the swirlers including a plurality of angularly-directed passages for directing combustion air to provide effective mixing of the air with the fuel, the air flowing through the passages tending to rotate each of the swirlers in the same rotational direction; (d) the swirlers being arranged in adjacent pairs; and (e) means on each of the swirlers for engaging the means on the adjacent swirler to limit rotation of the swirlers.
- Assignee:
- General Electric Co., Cincinnati, OH
- Patent Number(s):
- US 4763482
- OSTI ID:
- 6948177
- Country of Publication:
- United States
- Language:
- English
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