Abstract: Combustion equipment for a gas turbine engine operating on the pre-mix lean combustion bases comprises a flame tube having a plurality of alternately arranged main and pilot air ducts each having a respective fuel injector and receiving axially directed air from downstream of part span outlet guide vanes. The fuel and air in each duct are substantially pre-mixed before entry into the flame tube and the outlets of the pilot ducts direct the fuel and air mixture into the recirculation zone in a single vortex. At engine idle the air fuel ratio (AFR) is substantially stoichiometric to prevent the formation of unburnt hydrocarbons (UHC) and carbon monoxide (CO). As the engine accelerates the fuel flow to the pilot air ducts remains near constant so that the AFR in the re-circulation zone progressively weakens, and fuel is introduced into the main air ducts, the outlets of which direct the air fuel mixture into the flame tube with a substantial downstream component.

Abstract: A combustor for a gas turbine is provided, the combustor including a reverse flow type combustion chamber defined by an inner cylindrical wall and an outer wall concentric with the inner wall and connected at one end by an annular dome. The outer wall has three successive sections with the first section being cylindrical and of a predetermined diameter, the second outer wall section being of frusto-conical shape, and the third wall section being of cylindrical shape but of reduced diameter compared to the first section. Injectors are provided in the angled wall of the second outer wall section, and openings are provided annular with the injectors to allow compressor delivered air to enter directly into the combustion chamber surrounding the injector, the injector being directed towards the primary zone.

Abstract: An exhaust purification apparatus includes a regenerative burner for repetitively regenerating a trap element located in the exhaust system of an internal combustion engine. The regenerative burner has a combustion chamber adapted to permit flow of exhaust gases from the engine exhaust conduit to the trap element. A cup-shaped member is disposed within the combustion chamber to define therein an evaporation chamber which has an adequate supply of air-fuel mixture. The cup-shaped member has a peripheral wall formed with cutouts to permit air-fuel mixture from said evaporation chamber into said combustion chamber and also with a hole to permit fuel droplets to fall onto a glow plug located below the cup-shaped member within the combustion chamber. A protective cover is provided to cover the path of dropping of fuel droplets onto the glow plug to prevent air from flowing to cool down the glow plug and deviate the fuel droplets away from the glow plug.

Abstract: A swirler for use in combustion chambers in which the vanes of the swirler are partially unshrouded to improve the mixing of fuel and air.

Abstract: An atomizer nozzle for continuous fuel injection is provided. The nozzle can serve as a main injection nozzle or as an igniter for combustion chambers, and is provided with a single-hole fuel nozzle, and an annular gap for possible additional air supply located coaxially therebefore. The chamber or space between the nozzle opening and the annular gap is connected by pressure equalization openings with the combustion chamber behind or after the annular gap. The pressure equalization openings are represented and defined by individual spacers between the fuel nozzle body and the air nozzle ring.

Abstract: A burner construction for low emission burners in which the primary fuel is injected with air in an annulus into the upstream end of the burners so as to cause a significant recirculation of the fuel and air mixture adjacent to the end cap, the secondary fuel is injected into the burner in a small angle spray at a point substantially spaced from the end cap and large combustion and/or dilution holes in the burner wall a small distance upstream of the secondary nozzle are sized to produce an additional recirculation in the primary fuel and air around the secondary nozzle with this additional recirculation in the direction opposite to the first recirculation.

Abstract: A combustor in which fuel is premixed with rather large amounts of primary air in order to obtain a high temperature, rich mixture of volatized fuel and air prior to ignition is designed as a tubular vaporizer provided with a swirl inlet opening in a preheat air chamber and a substantially rotation symmetrical outlet in a combustion chamber the outlet being directed towards inlets for secondary air to the combustion chamber.

Abstract: A gas turbine engine comprises an annular combustion chamber (13) intended for low nitrogen oxide emission. The chamber has a pre-mixing section (20) in which an air-fuel mixture is brought to a significant degree of vaporization before issuing through a grill (22) at the end of the pre-mixing section into a main section (21) of the chamber. Pilot sections (18,19) at opposite sides of the pre-mixing section have outlets (28,29) through which burning mixture from the pilot sections is discharged into main section (21). The grill (22) defines openings (35) through which the fresh mixture from the pre-mixing section (20) is discharged across the outlets (28,29) of the pilot sections (18,19) to mix with and become ignited by the burning mixture.The pre-mixing section (20) is an annular duct (33) having walls (15,16) which extend in the direction of the axis of the chamber and are straight in that direction though slightly convergent. The arrangement favors vaporization in the duct without auto-ignition.

Abstract: A gas turbine engine combustion chamber includes an inlet through which primary air can flow and which is capable of receiving a fuel injector. A cylindrical collar extends from this inlet into the interior of the combustion chamber and the collar may be parallel walled or slightly divergent and one or more rows of equi-spaced apertures can be provided in the collar wall. The presence of the collar has the effect of reducing the rate of carbon deposition on the combustion chamber head and of reducing the levels of emitted smoke.

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: This invention relates to improvements in the art of liquid fuel combustion and, more particularly, concerns a method and apparatus for the controlled gassification of liquid fuels, the thorough premixing of the then gassified fuel with air and the subsequent gas-phase combustion of the mixture to produce a flame substantially free of soot, carbon monoxide, nitric oxide and unburned fuel.

Abstract: A gas turbine engine comprises an annular combustion chamber (13) intended for low nitrogen oxide emission. The chamber has a pre-mixing section (20) in which an air-fuel mixture is brought to a significant degree of vaporization before issuing through a grill (22) at the end of the pre-mixing section into a main section (21) of the chamber. Pilot sections (18,19) at opposite sides of the pre-mixing section have outlets (28,29) through which burning mixture from the pilot sections is discharged into main section (21). The grill (22) defines openings (35) through which the fresh mixture from the pre-mixing section (20) is discharged across the outlets (28,29) of the pilot sections (18,19) to mix with and become ignited by the burning mixture.The pre-mixing section (20) is an annular duct (33) having walls (15,16) which extend in the direction of the axis of the chamber and are straight in that direction though slightly convergent. The arrangement favors vaporization in the duct without auto-ignition.

Abstract: A dual phase fuel vaporizing combustor, and method for burning, in an annular vaporizing combustor, high viscosity, high carbon/hydrogen ratio hydrocarbon fuels, including such as residual fuels, low grade synfuels and coal-oil slurries. A dual phase vaporizer tube receives alternating introductions of a fuel air mixture of high fuel content, and then a hot air or low fuel content mixture, to alternately initially discharge from the tube a vapor stream of combined air and partially vaporized fuel, the initial vapor stream impinging onto a hot surface where more volatile portions of fuel will vaporize and burn, while less volatile heavier fuel components will form a hot carbon deposit on the surface; and alternately and sequentially discharge from the tube a hot, highly oxidizing stream with little or no fuel and impinge the sequential stream onto the carbon deposit on the hot surface and thereby promote substantial burning of the carbon.

Abstract: The disclosure is of a combustion chamber having prevaporizing pipes for the injection of fuel and shield cups intended to play the role of thermal barriers, upon which the hot jets issuing from the injectors are broken up. The shield cups have ribs toward which high velocity jets of air are directed, the jets of air issuing from small orifices. Other small orifices may addtionally open on a ridge of the ribs, so as to form supplementary jets of air convergent with the first set of jets of air.

Abstract: Combustion equipment designed to reduce smoke levels and the production of nitrogen oxides has a fuel burner mounted in the upstream wall of a combustion chamber, the fuel burner comprising a central duct partially surrounded by an annular duct, each of the ducts having an array of swirl vanes at their upstream ends and fuel inlet apertures downstream of the respective arrays of swirl vanes. The fuel supply to each of the ducts can be controlled to apportion the fuel flow between the two ducts in dependence of an engine parameter, such as speed, so that at low speeds a majority of the fuel is injected into the annular duct while at higher engine speeds, a majority of the fuel is injected into the central duct.