Abstract: Combustion chambers for gas turbine engines and, more particularly, an annular combustion chamber. The combustion chamber comprises a flame tube having a back wall through which several vaporizers project into the flame tube or combustion zone. Each vaporizer has a pipe section extending within the flame tube, fuel supply and also supply ports in communication with the pipe section, and at least one outlet port for supplying a vaporous fuel-air mixture from the pipe section to the flame tube. Outlet ports of adjacent vaporizers are arranged spaced-apart from and facing one another, whereby a zone of maximum turbulence is formed between the outlet ports.

Abstract: A combustion chamber for gas turbine engines, particularly aircraft turbojet engines, which is constituted of an outer casing, at least one flame tube inserted therein, and incorporating at least one ignition device for the produced, respectively, supplied fuel-air mixture. The ignition device comprises two high-capacity ignition or spark plugs which are presently arranged in series in a single axial plane in the flame tube, and further including an ignition fuel nozzle, whose fuel injection spray cone will simultaneously encompass the ignition spark zones of both high-capacity spark plugs.

Abstract: A combustion chamber including an outer casing having a flame tube within it defining an annular space between them which receives air from the engine compressor. The flame tube has diametrically opposed pairs of air inlet ports through which air from the annular space flows substantially radially into the flame tube. A flow guide on the exterior of the flame tube is associated with each air inlet port. The upstream end of each flow guide is open to air from the compressor and the downstream end extends inwardly and downstream and partitions the upstream portion of its respective air inlet port from the annular space. A fuel tube extends into each flow guide. A curved baffle may extend radially inwardly at each air inlet port and define an arcuate louver between the baffle and the downstream edge of its respective air inlet port. Each air inlet port may have a square upstream portion merging into a circular downstream portion.

Abstract: A combustion engine for gas turbine engines, constituted of an outer housing and having at least one flame tube inserted therein which is suppliable with secondary or mixing air through the intermediary of an annular passageway formed between the outer housing and the flame tube while, on the other side, the primary zone within the flame tube has fuel-enriched combustion air conveyable thereto, and wherein there are provided at least two fuel atomizer nozzles which are controllable independently of each other.

Abstract: The useful life of a gas turbine combustion chamber and especially its flame pipe is increased by an improved cooling arrangement which branches off a small proportion of the air from the compressor upstream of the combustion chamber. The branched off air is directed into the combustion chamber and onto the flame pipe so that it flows in a cooling manner around at least the front end of the flame pipe without initially substantially participating in the combustion.

Abstract: A combustion chamber for gas turbine engines or power plants having devices for the gaseous processing of the fuel which is introduced therein, characterized by the combination of the following features:A. The fuel ejection cone of at least one fuel nozzle arranged upstream of the flame tube back wall of the combustion chamber extends exteriorly along the flame tube backwall, the latter of which is conically shaped in conformance with the ejection cone;B. The combustion chamber has an air infeed hood essentially encompassing at least partially the flame tube backwall as well as the fuel nozzle, forming an annular or ring channel narrowing in the direction of the downstream end of the flame tube backwall and which, by means of plurality of apertures located immediately behind the flame tube backwall in the side walls of the flame tube, is in communication with the interior of the flame tube.

Abstract: Apparatus for supplying air and fuel to a flame tube of a combustion chamber of a gas turbine engine which includes primary air supply ports for supplying air under high pressure toward the center of the flame tube and fuel tubes projecting into and opening at the primary supply ports for admitting fuel for entrainment by the primary air as it passes through the primary supply ports. In certain preferred embodiments, an annular member forms a supply port, as well as a mounting arrangement for fuel tube. Preferred embodiments also include deflector baffles or plates for preventing flow of fuel from the fuel tubes into portions of the air being supplied as secondary air to the combustion chamber.