GB686754A - Preheater and vapourizer for gas turbine engines - Google Patents

Abstract

686,754. Liquid fuel burners. WHITELAW, W. B., and ROE CANADA, Ltd., A. V. June 21, 1950 [June 28, 1949], No. 17056/49. Class 75(i) [Also in Group XII] In a vaporizing type of combustion chamber for a gas turbine engine, liquid fuel is passed through a preheating element 21 having a wall exposed to the flame zone 19, and is then sprayed forcibly against an impingement member 28 situated in the opening for admission, of air to the flame tube. Fuel enters the preheating element 21 through the conduit 20 and flows downstream to the rear distributing ring 22 from which the heated fuel flows upstream through superheating tubes 23 to the forward distributing ring 24 and from which it is discharged downstream through the nozzles 25 on to the impingement member 28. An air deflector 26 of frusto-conical shape is disposed at the entrance of the flame tube and has a baffle plate 27 within, one or more holes 27b being provided in the baffle plate. The impingement member 28 is of frusto-conical form and lies between the air deflector 26 and the preheating element 21. The superheating tubes may be omitted, the fuel entering the rear distributing ring and flowing to a forward ring from which it is discharged through nozzles as before. The invention is also applicable to the annular type of combustion chamber, the preheating element being disposed either on the inner or outer walls of the annular flame tube. In the tubular type of combustion chamber shown in Figs. 2 and 3, the exposed wall of the preheating element may be a separate wall 21b as shown, or may be the wall of the flame tube itself, in which case the outer wall of the preheating element is remote from the flame zone.