Abstract: A low cost, low fuel consumption, twin-spool turbine engine with external power take-off essentially exclusively from the high pressure (H.P.) spool uses a radial in-flow turbine and a centrifugal compressor in the H.P. spool and a flow-optimized L.P. spool to achieve pressure ratios above 12/1 for simple cycle engines. Intercooled and recuperated versions are included. The turbine engine according to this invention is ideally suited for applications up to about 1000 KW and will provide some 20% less fuel consumption in this power range compared with conventional designs.

Abstract: A combustor for a gas turbine engine includes divergent mixing cones disposed within the combustion chamber proper to provide a flow restriction which separates the combustion chamber into primary and secondary combustion zones. Placement of the mixing cones within the chamber enhances vaporization of the fuel and permits combustion to take place in the primary zone at flame temperature below the stoichiometric temperature thereby reducing formation of nitrous oxides.