GB1299696A - Gas turbine engine aerating nozzle - Google Patents

Abstract

1299696 Aerating nozzles EX-CELL-O CORP 19 April 1971 [26 June 1970] 26320/71 Heading F4T An aerating nozzle 11 for delivering fuel to a gas turbine engine combustion chamber 12 comprises primary and secondary fuel swirl chambers 25 and 39 fed from passages 18 and 19 and ejecting fuel spray cones from an orifice 26 and past a lip 41 respectively, secondary air swirl chambers 46 and 55 fed with air from a chamber 43 surrounding the nozzle and ejecting said air past lips 47 and 57 to intermix with the secondary fuel cone, and a primary air chamber 51 into which some of the swirling air from chamber 46 is diverted by a deflector 48 via a series of apertures 49 and from which it is ejected past a lip 52 to intermix with the primary fuel cone. As shown, the chambers have frusto-conical exit portions and the lips are disposed at different axial positions so as to increase the velocity of fluid flow and ensure optimum mixing, thus allowing relatively complete combustion close to the nozzle which in turn leads to an even temperature distribution in the combustion chamber and improved engine efficiency. The air chamber 55 is caused to swirl by slots 54 while the air fed to chambers 46 and 51 is passed over swirl vanes 45. The size of ports 38 through which the secondary fuel is fed is predetermined to give the desired rate of fuel flow according to the pressure. The primary fuel is passed through a screen filter 31. In a second embodiment the primary fuel and air chambers are omitted. Both embodiments incorporate heat shields.