Abstract: Combustion apparatus for a gas turbine engine for directing combustion air to enter the combustor adjacent the fuel oil nozzle in a vigorous swirling pattern to thoroughly mix with the atomized fuel to eliminate fuel rich, smoke producing pockets from the combustion zone. The apparatus includes air inlet ports directing one portion of the combustion air in an axially directed swirling motion, another portion of the air in a tangentially directed swirling motion with other portions of the air directed to cool and clean the nozzle and cool the wall of the combustor.

Abstract: A fuel nozzle assembly having a nozzle tip disposed in one end of a fuel delivery tube supported in a mounting flange. An air delivery tube, also secured to said support flange, encloses the fuel delivery tube to define an annular air chamber therebetween. The air delivery tube and the fuel delivery tube define interengaging tab portions providing a breech-lock engagement therebetween, with the tab members disposed closely adjacent the nozzle tip and effecting a sealing engagement between the nozzle tip and an aperture in the end of the air delivery tube through which the tip protrudes. To accommodate unequal axial expansion of the two tubes, the air delivery tube is mounted to the support flange with a flexible diaphragm.

Abstract: A combustion chamber either an annular or can-annular type, which substantially eliminates the production of smoke while maintaining all other performance parameters of the combustion chamber. The combustion chamber is provided with a front end configuration which substantially eliminates local fuel rich regions and which provides a means for mixing the incoming fuel and air.