A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.

A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.

A combustor for a gas turbine, having a pre-combustion chamber having a peripheral wall around a center axis of the pre-combustion chamber, the peripheral wall has an inner panel and an outer panel and a passage provided between the inner and the outer panels, a swirler which is connected to the pre-combustion chamber for providing pre-combustion chamber with a flow of an oxidant gas, at least a pilot fuel injector, wherein the swirler is connected to the peripheral wall in such a way that a portion of the oxidant gas from the swirler is channeled to the passage, and the pilot fuel injector is connected to the passage for injecting a flow of pilot fuel into the passage.

A mixer assembly for a turbine engine is generally provided. The mixer assembly includes a vane assembly including a plurality of vanes configured to direct a flow of oxidizer to mix with a flow of fuel. The vane assembly includes a fluid diode disposed within a vane flow path between each pair of vanes of the vane assembly.

A premixer assembly for a combustor includes: at least one ring of premixers, each premixer having a central axis, an annular peripheral wall surrounding a centerbody, and at least one swirler disposed between the centerbody and the peripheral wall, wherein the peripheral wall defines an inlet area of the premixer; and a lip extending forward along the central axis from the peripheral wall, the lip extending at an oblique angle to the axis of symmetry.

A burner arrangement (1), for a mobile heater operated with liquid fuel, is provided; having a combustion chamber (2) for converting fuel with combustion air in a flaming combustion, which combustion chamber (2) extends along a longitudinal axis (Z) in a main flow direction (H); a pre-mixing chamber (3), which is arranged fluidicly upstream of the combustion chamber (2), for generating a fuel-combustion air-mixture, which pre-mixing chamber (3) comprises a side wall (4); a fuel evaporation surface (O) arranged in the pre-mixing chamber; a fuel supply (10) for supplying liquid fuel; and a first combustion air supply (6) having a swirl body (7) for supplying a combustion air flow into the pre-mixing chamber (3) with a swirl such that the combustion air is guided along the fuel evaporation surface (O) with a tangential flow component. A neck portion (5) is formed at a transition from the pre-mixing chamber (3) to the combustion chamber (2) at which the flow cross-section abruptly widens in the main flow direction (H).

A system and method for generating microwaves for microwave enhanced combustion (MEC) input to an MEC antenna of an internal combustion engine. The system uses a microwave generator and a directional coupler, which delivers the MEC input signal to the MEC antenna and receives a reflected signal from the MEC antenna. A feedback path determines a desired frequency for the MEC input signal, based on the reflected signal, and also determines a power feedback correction value. An open loop path determines desired power and timing for the MEC input signal, based on various engine conditions. The desired power is corrected with the power feedback correction value.

A system and method for generating microwaves for microwave enhanced combustion (MEC) input to an MEC antenna of an internal combustion engine. The system uses a directional coupler to deliver the MEC input signal to the MEC antenna and to receive a reflected power signal from the MEC antenna. A feedback path determines a desired frequency, based on the reflected power and using an impedance-matching controller that matches the reflected power to a desired frequency value. Additional inputs, such as various engine conditions, can also be used to determine the desired frequency.

Device for controlling combustion process in power station furnace system, having burners (1) in combustion chamber. The combustion air is supplied via annular gap (3) surrounding burners which may influence quantity of combustion air flowing through the annular gap (3). Quantity of fuel supplied to burner (1) is recorded, and quantity of combustion air flowing through annular gap (3) is determined, for which two formed sensor rods (11, 12), arranged in the annular gap (3.1), successively and in parallel, preferably transversely to the longitudinal axis (4) of the annular gap and in the flow direction (7) of the combustion air flow, the sensor rods (11, 12) allow part of the combustion air to flow past the first sensor rod (12) in the flow direction (7) of the combustion air flow and also flows past the second sensor rod (11) in the flow direction (7) of the combustion air flow.

A combustion system for a coal fired furnace having a windbox includes a source of a mixture of pulverized coal and air, and a splitter that receives the mixture and splits it into first and second mixed streams. A first nozzle receives the first mixed stream and discharges it into the furnace. A separator receives the second mixed stream and separates it into an air stream and a coal rich stream. An air conduit connected between the separator and the source of the mixture causes at least some of the air stream to be fed back into the mixture. A second nozzle receives the coal rich stream and discharges it into the furnace. A third nozzle receives support air from the windbox and discharges it into the furnace in a combustion supporting relationship with respect to the coal rich stream.