Variable area inlet guide vanes
Patent
·
OSTI ID:5284856
The method is described of admitting air to aerating fuel nozzles of the combustor of a gas turbine engine which fuel nozzles has a primary fuel system and a secondary fuel system comprising the steps of: flowing fuel through the primary fuel system for injecting a continuous spray of fuel into the combustor during the entire gas turbine engine operating envelope, admitting air into the combustor through a primary swirler for imparting a swirl component so that the air surrounds the spray of fuel injected from the primary fuel system, flowing fuel through the secondary fuel system for injecting a continuous spray of fuel into the combustor during a higher power operating regime of the engine operating envelope in such a manner as to surround and be contiguous with the spray of fuel from the primary fuel system, admitting additional air into the combustor through a secondary swirler solely when the temperature adjacent the combustor is at a predetermined value for imparting a swirl component so that the additional air surrounds the spray of fuel from the primary fuel system, the secondary fuel system and the primary swirling air.
- Assignee:
- United Technologies Corp., Hartford, CT
- Patent Number(s):
- US 4606190
- OSTI ID:
- 5284856
- Country of Publication:
- United States
- Language:
- English
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