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Trapped vortex combustor cavity manifold for gas turbine engine

United States Patent Application

20060107667
A1
View the Complete Application at the US Patent & Trademark Office
In accordance with one embodiment, the present technique provides a combustor assembly for use in a gas-turbine device. The combustor assembly includes a first combustion zone and a second combustion zone. The combustor assembly further includes a first premix chamber configured to receive a fuel and air to facilitate a first fuel-air mixture having a first fuel-to-air ratio, wherein the first premix chamber is fluidiclly coupled to the combustion chamber at the first combustion zone. The combustor assembly also includes a second premix chamber configured to receive a fuel and air to facilitate a second fuel-air mixture having a second fuel-to-air ratio, wherein the second premix chamber is fluidiclly coupled to the combustion chamber at the second combustion zone, wherein the second combustion zone is radially outboard of the first combustion zone.
Haynes, Joel Meier (Niskayuna, NY), Hojnacki, Benjamin Walter (Albany, NY)
10/ 994,833
November 22, 2004
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH & DEVELOPMENT [0001] This invention was made with Government support under contract number DE-FC26-01NT41020 awarded by the Department of Energy. The Government has certain rights in this invention.