Abstract: An igniter for the main burner of a gas turbine engine has an air chamber with a discharge passage and the fuel nozzle or tip is positioned within and in spaced relation to the walls of the passage. The tube has a helical member around the portion of the tube within the passage in order to impart a swirl to the air and the member itself is spaced from the passage walls to produce less swirl at the periphery of the air flow through the passage. The size of the device is such that it may operate continuously utilizing fuel from the main burner supply and air from the engine compressor.

Abstract: A gas burner is provided with a rich combustion chamber contiguous with a second combustion chamber through which combustion air enters in predetermined flow patterns to enable the burner to be self-stabilizing in a highly efficient manner. The rich combustion chamber receives air through a first port arrangement which, among other things, establishes underpressure zones at the center of the rich combustion chamber and air layer zones thereabout. Combustion air is supplied to the second chamber by a second port arrangement which, among other things, assures thorough combustion therein independent of the burner firing rate.

Abstract: A burner for burning crude or contaminated oil comprises a body defining a bore open at both ends, at one of which the oil is burnt, air being drawn into the flame through the bore, and an annular oil inlet in the bore wall such that air flowing through the bore to the flame will draw oil from the inlet in atomised form, will mix with it and will carry it into the flame. The burner is surrounded by an annular water ring provided with nozzles for spraying water into the flame.

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: An injector formed of an outer Coanda nozzle, consisting of three bodies, is located inside a flame stabilization cylinder, also introduced into a supplementary ejection nozzle. The front body is endowed with a baffle followed by an adjustable slot and continued by a Coanda profile having a recess with several orifices. The injector is simultaneously fed with air and fuel, which mix due to the depression created by the Coanda effect.

Abstract: Combustion chamber apparatus and process for use in gas turbine engines including a premix chamber bounded by porous ceramic material and a combustion chamber immediately adjacent a porous ceramic diaphragm which bounds the premix chamber. In this premix chamber, partial vaporization of the fuel, without combustion, takes place so as to improve combustion efficiency and shorten the length of the flame tube or combustion chamber needed for complete efficient combustion of the fuel. Primary air is introduced into the premix chamber, which passes with the fuel into the flame tube or combustion chamber, for futher mixture with secondary and tertiary air.

Abstract: A combustion liner for a gas turbine combustion apparatus has a wall of ceramic material. To minimize destructive thermal gradients in the ceramic material due to local cooling by air entering the liner through ports for combustion or dilution air, the walls of these ports are isolated from the entering air by metal bushings inserted through each port, these bushings being retained by a band encircling the liner and connected to the bushings.