Abstract: A gas turbine engine is described in which a compressor, combustor and turbine are arranged in series flow relationship. The compressor discharge is outwardly angled. This pressurized air is then introduced into a toroidal combustion chamber of the combustor to create an annular vortex within which the combustion process is maintained. The hot gas stream generated is discharged from the combustion chamber to a centripital turbine which drives the compressor rotor. A portion of the pressurized air is introduced into the combustion chamber adjacent the hot gas stream discharge exit and in general flow opposition thereto, to dilute the hot gas stream and confine the combustion process within the combustion chamber, thereby minimizing the possibility of overtemperaturing the turbine. The combustor housing also defines the outer bounds of the hot gas stream flowing through the turbine. A power turbine converts a major portion of the energy of the hot gas stream to a motive shaft power output.

Abstract: A miniature flat spray nozzle is disclosed which delivers a fan-shaped mist of fuel to a gas turbine combustor from a narrow slot. The slot is formed by making a transverse cut in a fuel-carrying conduit at a location near its end. A specially formed part is inserted into the end of the conduit which, in addition to capping off the conduit, divides the space adjacent thereto into three small chambers. One chamber is immediately below the transverse slot. Four orifices in the bottom wall of this first chamber connect it with the other two chambers. Each of the lower chambers opens into the conduit at its upstream end. Fuel delivered down the conduit divides in two parts, passes through the orifices between the lower and upper chambers, undergoes turbulent mixing in the chamber adjacent the transverse slot, and issues forth from the slot as an atomized mist.