Showing papers on "Afterburner published in 1977"

Swirling Flow Combustion

Abstract: Tests in a combustion centrifuge demonstrated that the normal progression from laminar flamespeeds of about 0.3 m/s (in hydrocarbon-air mixtures) to turbulent flamespeeds of up to 6.1 m/s can be advanced to a third stage, where flamespeeds in excess of 19 m/s were measured. A theory explaining how centrifugal-force-enhanced buoyancy produces the increased flamespeeds was developed. This theory was applied to the results of a combustion centrifuge experiment, the design of a 38-cm-dia afterburner research rig, and eventually to the design of a full-scale afterburner, which was tested on a modern turbofan engine. The experimental results confirmed the theory and indicate a potential 2 percent reduction in specific fuel consumption. 16 figures.

Process and apparatus for afterburning of combustible pollutants from an internal combustion engine

Abstract: In a process for the afterburning of the combustible pollutants from an internal combustion engine, in order to automatically reduce the secondary induction rate when power increases without using a controlling valve actuated by the carburettor venturi depression, there is provided a volumetric efficiency of the secondary air pump linked to and activated by the engine and a volumetric efficiency which decreases when the ratio between its back pressure and suction pressure increases, this reduction being achieved through the proper selection of the pump volumetric comression ratio r: between 0.6 c and 1.3 c when a steeply decreasing trend is required, and above 1.3 c if a slower and slower decreasing trend is required. To perform this process an afterburner apparatus has a nitrogen oxide reducing catalyst placed inside the afterburner reactor on the gas stream immediately at the outlet of a torus, in which the gases are homogenized and their reaction with preinjection air is terminated.

Afterburner flow mixing means in turbofan jet engine

Abstract: A short length afterburner assembly for a jet propulsion engine having a fan bypass includes cold and hot air cross-over passages and a plurality of flame stabilization swirler vanes associated with a balanced load controller for positioning the vanes parallel to hot gas stream flow from a jet engine core when the afterburner is off and in an inclined position to such gas stream flow when fuel is injected therein during afterburner operation thereby to produce flame spread within the afterburner core by a combination of translatory and swirling motions; and wherein atomized fuel for afterburner combustion is injected into hot gases ducted through hot air cross-over passages from the jet engine core to produce premix and prevaporization of fuel upstream of fixed flameholders and wherein cold fan bypass air cross-over passages have movable turbulator grids positioned during afterburner operation for mixing cold air flow with the bypassed hot core gas at the fixed flameholders during afterburner operation and wherein the turbulator grids are positioned parallel to gas flow when the afterburner is not in operation by means of the balanced load controller to produce a balanced variable geometry mechanical load to that on the flame stabilization swirler vanes.

General purpose incinerator/combustor

Abstract: An incinerator/combustor, comprising an elongated combustion chamber surrounded by an afterburner which is in turn surrounded by a housing, the afterburner and housing being coaxial with, and cooperating to provide redundant heating for, the combustion chamber, is disclosed. The combustion chamber is generally cylindrical with a horizontal axis, one end being adapted to receive materials to be burned. An ash chamber is spaced from the other end of the combustion chamber to define a circumferential opening which serves as an exhaust outlet. The two chambers are relatively movable to permit the flow of exhaust gases to be controlled. Air under controlled pressure is introduced to the combustion chamber to produce a cyclonic flow to enhance burning. A fuel supply may be provided to initiate combustion, but the system is designed to require no fuel other than the material being incinerated during normal continuous operation. The afterburner extends over both the exhaust outlet and a major portion of the combustion chamber. Air under pressure directed across the exhaust outlet produces a Venturi effect to draw exhaust gases out of the combustion chamber and direct them into the afterburner. The outer housing receives exhaust gases from the afterburner and directs them back over the outside surface of the afterburner in a second redundant flow, carrying them to an outlet stack.

Combustible compositions for air-augmented rocket engines

Abstract: A solid combustible composition for use in solid fuel air-augmented rocket engines which very substantially increases the temperature efficiency of afterburner fuel combustion with ram air, thereby greatly increasing engine performance. The improvement comprises dispersing in a matrix comprising the solid, fuel-rich organic compositions conventionally utilized in air-augmented rockets, particles containing solid oxidizable element and fluorine oxidizer compound which reacts with the element to produce gaseous subfluoride compound.

Engine with premixing and afterburning units - has fuel controller for constant air to fuel ratio, varying air proportion to burner

Abstract: The IC engine with pre-mixing and afterburning units has an airflow meter (8), butterfly throttle (9) and fuel injector (10) for the premixer (7). The afterburner may be thermal or catalytic. It receives its air via a branch (11) from the inlet pipe between airflow meter and throttle. A metering pump (14) in this branch is controlled by a unit (15) which also controls a magnetic valve (17) regulating fuel flow. A part from the usual control parameters this unit receives the airflow meter reading. It is set to keep the total air fuel ratio between 1.05 and 1, 15 times the stoichiometric value. The proportion deflected to the afterburner varies with load conditions.

Altitude test of several afterburner configurations on a turbofan engine with a hydrogen heater to simulate an elevated turbine discharge temperature

Abstract: A performance test of several experimental afterburner configurations was conducted with a mixed-flow turbofan engine in an altitude facility. The simulated flight conditions were for Mach 1.4 at two altitudes, 12,190 and 14,630 meters. Turbine discharge temperatures of 889 and 1056 K were used. A production afterburner was tested for comparison. The research afterburners included partial forced mixers with V-gutter flameholders, a carburetted V-gutter flameholder, and a triple ring V-gutter flameholder with four swirl-can fuel mixers. Fuel injection variations were included. Performance data shown include augmented thrust ratio, thrust specific fuel consumption, combustion efficiency, and total pressure drop across the afterburner.

Afterburner recoilless rifle

Abstract: Rearwardly exhausted powder gases from a recoilless rifle are combined withir and combusted in an afterburner that is attached to the rifle. Thrust produced by the combustion is utilized to assist in counter-recoil.

Exhaust gas cleaning system for internal combustion engine

Abstract: PURPOSE:With regard to an internal combustion engine equipped with an afterburner in the exhaust line, to make the after burner operate effectively in a transient phase of operation by means of an air fuel ratio controller which offers richer air fuel ratio of mixture than usual in the transient phase.

White smoke prevention device

Abstract: PURPOSE:Pure air of high temperature is mixed with the exhaust gas with saturated steam in an exhaust apparatus which possesses a wet purifier so that white smoke is prevented and an afterburner is dispensed without.

Gas turbine engine

Abstract: PURPOSE:To perform the afterburning of an engine in a stable manner even when turbine inlet temperature is high and oxygen contained in a combustion gas is little, by installing a device which leads the oxygen for combustion of fuel in an afterburner of the gas-turbine engine. CONSTITUTION:A gas turbine engine 1 is provided with an air intake 2, a compressor 4 installed in front of a rotor 3, a combustor 5, a turbine 6 installed in the rear of the rotor 3, an afterburner 7 and a jet nozzle 8. In the case aforesaid, a flow passage 9 to lead pressure oxygen into the afterburner 7 is additionally installed therein and its one end 9b is set up in a combustion gas flow passage 13 of the afterburner 7. And, a tank 12 storing oxygen under specified pressure is installed in this flow passage 9 with the hlep of a pump 10, an on-off valve 11 and another end part 9a of the flow passage 9 interconnected through. With this constitution, in the case where turbine inlet temperature is high and a quantity of oxygen contained in a combustion gas is small, the oxygen is fed out of the flow passage 9 so that afterburning takes place in a stable manner.