Showing papers on "Afterburner published in 1994"

Method and afterburner apparatus for control of highly variable flows

Abstract: Methods and apparatus are provided for destruction of volatile organic compounds ("VOC's") from process fumes having variable amounts of such VOC's wherein a nominal amount of the fumes are passed through an oxidizer for destruction of the VOC's and the hot products from the oxidizer are fed to an afterburner that is principally made up of a matrix bed of heat resistant material. The heat from the oxidized gases heats the matrix bed. Fume flows exceeding the nominal flow are bypassed directly to an inlet port of the afterburner where they are passed through the matrix bed of the afterburner, which has been heated by the oxidized gases from the oxidizer, and are combusted into additional gaseous products in a combustion wave. The system allows for utilization of the heat produced from the oxidation of the nominal flow for destructing fume flows that exceed the nominal flow.

Energy efficient afterburner

Abstract: A small energy efficient afterburner for oxidizing the byproducts of incomplete combustion is disclosed. Gases are forced into a firebox, where a heating element maintains a temperature above the flash point for the more common and undesirable pollutants. Typical temperatures are 500° C. to 800° C. for burning hydrocarbons coming from internal combustion engines or wood stoves. After gases pass through the firebox, they are forced into a chamber adjacent to the firebox intake, so that heat energy may be transferred to the incoming gases, thereby greatly increasing the thermal efficiency of the device. Greater efficiencies are achieved by putting a catalytic surface in the firebox, and by insulating the afterburner exterior.

Apparatus for thermal destruction of waste

Abstract: An apparatus for the thermal destruction of waste which includes an afterburner assembly for removing pollutants from industrial waste streams by high temperature thermal destruction using a mixture of gas and gaseous hydrocarbons which is injected into the combustion chamber (14) of the assembly using a ring injector assembly (66).

Aerodynamic flow investigations in an isothermal model of an afterburner

Abstract: Experimental and numerical investigations of the three-dimensional flowfields in an isothermal model of an afterburner are presented Five-hole pilot probe measurements along the entire length of the model in three different azimuthal planes, allow the determination of three mean velocity components which provide comprehensive information to aid understanding of such complex flows The numerical calculations are performed using a SIMPLE based algorithm with staggered grid arrangement The standardk-ɛ model is used for physical modeling The numerical results agree quite satisfactorily with the time-mean velocity measurements The predicted turbulence kinetic energy contours have also been presented

Augmentor light-off improvement

Abstract: The disclosure describes a fuel scheduling system that controls the fuel into the pilot burner of an afterburner by making fuel flow directly proportional to compressor discharge pressure at low compressor pressures, but to limit fuel flow to a fixed value at high A/B pressures. This is accomplished by used of a fixed orifice trim in combination with a variable orifice inserted in the fuel tube for the afterburner.

Fire-tube boiler with fuel supply to each individual tube

Abstract: The space (7) to be heated is traversed by a number of tubes (2) each leading from a combustor (11) and afterburner (8) to a corrosion-resistant inlet (10) of the common smokebox.The pollutant content in the combustion prods. is measured by a sensor (6) and signalled to a computer (5) which provides optimal control of the individual fuel delivery devices (3) and blower (4). The number of burners in operation and the speed of the blower are adjusted for min. emission.

Afterburner for various furnaces

Abstract: The invention relates to an afterburner for various incinerators, said afterburner (3) including a housing portion provided with a smoke delivering pipe (2) for carrying the smokes coming from an incinerator firing chamber (1) into the afterburner chamber. The chamber (3) is provided with a burner (7), for example an oil burner or a gas burner. The chamber (3) is further fitted with a smoke dispensing box (9), whereby the particles not yet incinerated are recycled back into the fling chamber (1) and the flue gases are delivered into a flue gas scrubber (12). Between the afterburner (3) and the smoke dispensing box (9) is a wall (16) including a perforated section. The afterburner (3) comprises a preferably circularly cylindrical housing portion, having its ends sealed with end plates for creating a substantially sealed chamber, the burner (7) being mounted on one of the end plates for directing the burner flame substantially lengthwise of the afterburner and, thus, when in operation, the afterburner (3) is substantially filled with flames for an intensified combustion of particles thereby.

Turbojet afterburn unit

Abstract: A turbojet engine is provided with an afterburn unit having non-deformable flame catcher arms 10, in which each flame catcher arm 10 has a streamlined cross-section which is sharp at its upstream end 22 and convexly curved at its downstream end 23, and the final stage of vanes 7 of the turbine blading each has an upstream part 24 which is fixed relative to the engine structure and a downstream part 25 which is pivotable between a first configuration, in which it extends substantially in a radial plane 28 containing the engine axis, and a second configuration, in which it is oriented in a direction K which is oblique to the said radial plane 28. The arrangement provides for turbulence production to facilitate mixing of gases during afterburner operation, and a low-drag configuration when afterburner operation is not required.

Gas turbine device

Abstract: PURPOSE: To enhance heat efficiency of a gas turbine plant in which an energy exchanger and a combustion chamber are connected to a gas turbine by providing a water supply conduit for cooling an outlet channel of the energy exchanger and reusing the steam generated by the cooling. CONSTITUTION: Compressed air is supplied to a complex supercharger (pressure wave supercharger) which is an energy exchanger C through an outlet conduit 2 by the operation of a compressor A operatively coupled to a turbine B. The pressurized air from the supercharger C is supplied to a combustor E. High pressure gas produced by combusting fuel in the combustor is supplied to a high pressure turbine F and an afterburner D. The gas from the afterburner D is expanded in the energy exchanger C and then joins the gas from the high pressure turbine F to be supplied to the turbine B for working. An outlet port 13 of the energy exchanger C is cooled by water or steam supplied from a supercharger conduit 12. The steam thus generated is directed by a conduit 14 to the afterburner D for reuse.

Afterburning process and afterburner with energy recovery

Abstract: An afterburning process for a stream of dust (11) containing production residues. Combustion gas is taken through a heat exchanger (14, 16). A charged stream of air (20) is heated in another heat exchanger (15) before being taken into the spin reaction chamber.

Aerodynamic flow investigations

Abstract: Experimental and numerical investigations of the three-dimensional flowfields in an isothermal model of an afterburner are presented. Five-hole pitot probe measurements along the entire length of the model in three different azimuthal planes, allow the determination of three mean velocity components which provide comprehensive information to aid understanding of such complex flows. The numerical calculations are performed using a SIMPLE based algorithm with staggered grid arrangement. The standard k-~ model is used for physical modeling. The numerical results agree quite satis- factorily with the time-mean velocity measurements. The predicted turbulence kinetic energy contours have also been presented. 1 Introduction increased popularity of turbofan engines along with afterburners in various air-crafts, which consist of complicated shapes of flame stabilizers, necessitates an innovative and efficient design approach. The separated recirculating flow which is established in the lee of bluff bodies can be used to stabilize flames in high velocity reacting streams. The flame stability characteristics and the accurate fuel flow control behind the complex flame stabilizer are the main source of various low-frequency combustion instabilities (Edwards 1955; Cullom and )ohnsen 1979; Sotheran 1988). They are mainly governed by the aerodynamics of the flow around the body. Thus, the understanding of the aerodynamics of the flow in the region near the flame stabilizer is essential for the failure-free design of the afterburner.