Combustors and combustion systems for gas turbine engines

Details Combustors and combustion systems for gas turbine engines Combustors and combustion systems for gas turbine engines

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/06 (2006.01) F23R 3/38 (2006.01) F23R 3/50 (2006.01)

Patent

CA 2626952

A combustion system includes a combustor having a forward annular liner having a first plurality of effusion holes, and an aft annular liner having a second plurality of effusion holes and forming a combustion chamber with the forward annular liner. The first plurality of effusion holes and the second plurality of effusion holes are adapted to receive compressed air from a compressor and contribute to a single toroidal recirculation air flow pattern in the combustion chamber. The combustion system further includes a rotary fuel slinger further adapted to receive a flow of fuel from a fuel source and to centrifuge the received fuel into the combustion chamber; and an igniter extending at least partially into the combustion chamber to ignite the fuel and compressed air in the combustion chamber, to thereby generate combusted gas.

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