Abstract: A combustion chamber for a gas turbine engine which has staged combustion in two toroidal vortices of opposite hand arranged one upstream of the other. A burner delivers air/fuel mixture in a radial direction to support the vortices and the burner has a convergent outlet for the air/fuel mixture.

Abstract: A combustion chamber device includes a combustion chamber and a rotatable cup-shaped fuel spreader arranged centrally therein. Liquid fuel is supplied to within said cup for being distributed therein and discharged therefrom and intermixed with an air stream supplied to said combustion chamber to form an air-fuel mixture which then is ignited. The spreader cup is located adjacent a combustion zone in the combustion chamber and provided with an enclosing insulation in the form of a layer of axially flowing air. According to the invention, the fuel spreader cup has a substantially straight and cylindrical inner surface with a circumferential shoulder or threshold adjacent the open end, said shoulder having a radial thickness sufficient for maintaining inside said spreader cup a fuel layer of required depth for obtaining a predetermined fuel supply volume in the cup.

Abstract: A system for burning fuel particles in which the particles are suspended in a stream of air and projected into the firebox of a heat exchanger. In order to spread the fuel-air mixture, air is directed transversely, and preferably outwardly of the flowing mixture. The fuel is preferably powdered coal.