Abstract: A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combusting a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle assembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane and the combustion products are isolated from the fuel and air in the mixing zone at all operating conditions of the engine.

Abstract: A liner for a gas turbine engine combustor is disclosed having a non-linear cavity section, wherein air and fuel injected therein form a trapped vortex for igniting and stabilizing a flame in the combustor. The cavity section, which is substantially rectangular in shape, has an aft wall, a forward wall, and an intermediate wall connected at one end to the aft wall and at the other end to the forward wall. A plurality of passages are provided in the aft wall for injecting fuel therethrough and a plurality of air passages are provided in the aft wall surrounding each fuel passage for injecting air therethrough. Cooling holes are also provided in the aft wall, the forward wall, and the intermediate wall for reinforcing the fuel/air vortex flow in the cavity section.

Abstract: A combustor for a gas turbine engine is disclosed which is able to operate efficiently at inlet air flows having a high subsonic Mach Number. The combustor has an outer liner and an inner liner spaced therefrom, wherein a combustion chamber is defined therebetween. A dome inlet module is provided which is in flow communication with compressed air flow from a compressor upstream thereof. The dome inlet module has an outer member fixed to the outer liner and an inner member fixed to the inner liner, wherein a flow passage is defined by the outer and inner members for the compressed air flow to flow freely from a compressor to the combustion chamber. Fuel atomizers are then utilized to inject fuel into the flow passage so that the fuel is mixed with the compressed air stream to form a fuel/air mixture which enters the combustion chamber.

Abstract: In the combustion chamber of a gas turbine, at least one premixing burner (110) is arranged in a dome (51) communicating with a plenum (50). Said premixing burner (110) is fastened on the outlet side to a front plate (52) limiting the combustion space (58) of the combustion chamber. The premixing burner procures the combustion air from the dome. The fuel injected via nozzles is intensively intermixed with the combustion air within a premixing space of the burner prior to ignition.There is provided a jet injector (53) which opens into the dome (51) and of which the central nozzle (54) is connected to the combustion space (58) via an orifice (55) in the front plate (52) and of which the annular space (56) surrounding the central nozzle is loaded with a propellant.

Abstract: A sudden expansion combustion chamber comprising a combustion chamber, an inlet port, a backward-facing step layer provided in the combustion chamber having a predetermined thickness so as define the inlet port, and an after-mixing chamber. The sudden expansion combustion chamber is characterized in that it contains at least a slot provided in the backward-facing step layer so as to increase the recirculating flow rate and turbulence of the incoming air, and thus reduce ignition delay.

Abstract: A liquid fuel power plant (100) including an open-ended combustion chamber (102) and a first mechanism (112) for delivering a combustible fuel to the open-ended combustion chamber (102). A second mechanism (136) is included for igniting the fuel in the open-ended combustion chamber (102). A coiled tube-shaped mechanism (140) located within the combustion chamber (102) is provided for extending the length of the combustion chamber (102) to decompose the ignited fuel and to provide an exhaust gas comprised of fundamental elements. Finally, a third mechanism (160) is provided for using the exhaust gas to perform useful work. In a preferred embodiment, the liquid fuel power plant (100) includes separate fuel and air input lines (110, 120). The air input line (120) delivers compressed air which is preheated in an air passageway (130) and thereafter mixed with the combustible fuel in the open-ended combustion chamber (102).

Abstract: An annular combustor liner (30) includes louvers (52, 54, 56, 70, 72) for inducing the formation of a single toroidal vortex (68) adjacent a domed upstream portion (34) of the liner (30).

Abstract: In order to provide an expansive central recirculating gas zone (40) in a combustor (10), and in a manner wherein the combustion chamber (20) is of compact volume, a stored energy combustor (10) comprises a vessel (12) having narrow, spaced-apart inlet and outlet ends (14, 16) interconnected by a wall (18) defining a relatively wise combustion chamber (20). The combustion chamber (20) is generally annular and a wall (18) defining the combustion chamber (20) includes an upstream wall region (18a) and a downstream wall region (18c) interconnected by a generally annular side wall region (18b). The inlet end (14) and outlet end (16) are generally tubular extensions of the vessel (12) leading to and from the combustion chamber (20) and oxidant is swirled in the tubular extension (14) leading to the combustion chamber (20) and directed in a swirling annulus into the combustion chamber (20) outwardly of a fuel injector (28).

Abstract: The pre-combustion chamber (1), in which liquid fuel is burnt sub-stoichiometrically, is connected upstream of a secondary combustion chamber (16), in which complete combustion takes place over-stoichiometrically. The sub-stoichiometric quantity of combustion air (11) for the pre-combustion chamber (2) is injected close to the wall from the outlet duct (3) upwards into the casing (2), which has a heart-shaped axial cross-section. The injection nozzles (7) for the fuel are positioned so that the jets of fuel (8) shield the layer of combustion air close to the wall from the partially burnt combustion mixture flowing through the outlet duct (3) into the secondary combustion chamber (16). At the end of the outlet duct (3) the quantity of auxiliary air required for complete combustion in the secondary combustion chamber (16) is added to the partially burnt combustion mixture.

Abstract: A novel combustion device is installed into a gas turbine to permit operation with solid or other high ash fuels. A refractory burner block defines an annular primary combustion chamber and a number of secondary cyclonic combustion chambers positioned radially inwardly of the primary chamber. Waste wood or other solid fuels are charged into the primary combustion chamber. Pressurized combustion air flows derived from the turbine's compressor are introduced tangentially into the primary chamber thereby creating a vortex. A number of passages place the primary chamber in communication with the secondary chambers. These passages are formed in a radially inner wall of the primary chamber so that fuel particles are retained within the primary chamber by centrifugal forces until reduced to an appropriate size for combustion in the secondary chambers.

Abstract: A device for combustion of a fuel with substantially pure oxygen using partial recirculation of the combustion gases which has separate ejectors suspended between discs which are in turn connected to a resiliently suspended hub.

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 combustion device, especially for slow-to-react pulverized coal or coal dust.

Abstract: Combustors [22] which employ such features as rotary cup fuel atomizers and the latter in conjuction with CIVIC combustion to enhance flame performance, to produce efficient combustion over a wide operating range, and to eliminate the problems typically encountered in liquid fueled combustors, especially as they are scaled down in size. A porous or perforate barrier [180] can be used to keep large fuel drops from reaching the combustion zone [124] of the combustor. Also, an air buffer system can be employed to keep fuel from backing up to the bearings [32] by which the rotary cup [98] of the atomizer is rotatably supported, and a fuel supply line [56] with a strategically located orifice [176] can be provided to effect an interaction between fuel discharged therefrom and the buffer air. This keeps the film of fuel formed on the atomizer cup [98] from being disrupted and also keeps the buffer air from penetrating to an inner hot gas recirculation zone [130] in the combustor.

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: Combustion apparatus of the premix/fuel lean type which employ jet induced circulation to inhibit the formation of atmospheric pollutants.

Abstract: A device for burning fuel with air is provided with means for causing partly recirculation of the combustion gases prior to their exit via a preheater. The degree of recirculation may be governed by a parallel path having controllable flow resistance and in which no recirculation occurs.

Abstract: A gas turbine combustion chamber in which the primary air inlets in a peripheral wall of the combustion chamber are defined by open-ended tubes extending inwardly from the peripheral wall by a substantial distance into the combustion chamber and having their inner, that is their outlet, ends facing in an upstream direction within the combustion chamber, whereby each of the tubes will introduce a stream of air with at least a component of motion in the upstream direction along or parallel with the longitudinal axis of the combustion chamber, thereby to effect recirculation of fuel, air and combustion gases within the combustion chamber. Similar air inlet tubes may be provided for introducing secondary and tertiary air into the combustion chamber.

Abstract: A combustion chamber for a gas turbine is provided with a prechamber connected at the input end of the flame tube. The dimensions of the flame tube and prechamber, and the location of the air inlet openings are selected so that the flame in the flame tube flashes back and burns as a stable rich flame in the prechamber when the turbine is in a high-load condition. The result is a variation in the combustion properties of the chamber which reduces pollutant emission levels over a wide range of engine load conditions.