Showing papers on "Afterburner published in 1971"

Incineration systems and methods

Abstract: Apparatus and control techniques for coupling afterburner-centrifugal separator devices to existing incinerators. By means of exercising control over incinerator exhaust stack draft and afterburner temperature, complete oxidation and particulate separation can be achieved in an afterburner unit which may be coupled to an existing incinerator. The invention further encompasses automatic safety features including provision of a bypass for incinerator effluents in the case of any failures in the afterburner system.

Afterburner for internal combustion engine

Abstract: An afterburning system for minimizing hydrocarbon and carbon monoxide, content left unburned in engine exhaust gases of an internal combustion engine. In the afterburning system, an improved afterburning stabilizer is provided including a porous enclosure for uniformly admixing an additional air-fuel mixture, which is burned to form a premixed flame therearound for anchoring the main combustion of the contaminated exhaust gases. A number of projections are mounted upon the porous enclosure for producing small disturbances in the flow of the exhaust gases and for acting as a stable heat source for the main combustion when the premixed flame is formed close to the tips thereof.

Pollution control system

Abstract: A POLLUTION CONTROL SYSTEM FOR CONNECTION TO THE EXHAUST OF AN AUTOMOBILE OR HEATING PLANT CONSUMING FOSSIL FUELS CONSISTING OF AN AFTERBURNER COMPARTMENT INCLUDING A GLOW HEAD DISPOSED WITHIN THE AFTERBURNER COMPARTMENT FOR IGNITING UNBURNED EXHAUST GASES. THE AFTERBURNER COMPARTMENT ALSO INCLUDES AN AIR INLET TO PERMIT OXYGEN TO MIX WITH THE UNBURNED EXHAUST GASES TO AID IN THEIR IGNITION. AT THE OUTPUT OF THE AFTERBURNER COMPARTMENT IS INCLUDED A COOLING AND MIXING CHAMBER SO THAT THE EXHAUST GASES CAN BE FED INTO A PNEUMATIC PUMP WHERE THEY WILL BE APPLIED TO A FILTERING SYSTEM PREFERABLY CONSISTING OF CHARCOAL BEFORE THE GAS ENTERS INTO THE ATMOSPHERE.

Exhaust gas purifying device

Abstract: An exhaust gas purifying device comprises an improved control system for controlling a device for regulating the flow of a supplementary air to the afterburner, disposed in an exhaust system of an internal combustion engine, or a device for controlling the spark-plug ignition timing, in response to the difference between the temperature of the internal combustion engine and the ambient temperature around the engine for the purpose of reducing to an inappreciable value the amount of noxious unburned compounds present in an exhaust gas emerging from the exhaust system of the engine The difference of temperature therebetween can be detected by a combined pair of thermal sensitive elements such as thermistors or the like An essential advantage of the present invention is that the ambient temperature is taken into consideration for efficiently and advantageously operating the exhaust gas purifying device

Apparatus for filling and, if desired, emptying inert gas poor in oxygen into or from holds in ships, respectively

Abstract: Exhaust gases from an emergency or auxilliary gas turbine/generator set are passed to an afterburner in which the rather high oxygen content of said exhaust gases is reduced to an acceptable level for use of the resulting gas as an inert explosion-proof gas for empty oil tanks. Before the gas is supplied to the tanks it is cooled by water supplied by a pump driven by the electric current produced by the generator. No blowers are required, since the turbine may operate against the pressure required for feeding the gas through the afterburner and the cooler and into the tanks. For displacing the inert gas from the tanks when desired, compressed air from the compressor unit of the turbine/generator set is tapped off and passed through an injector in which additional air from the atmosphere is entrained. The combined air is passed through the cooler and fed to the tanks through a suitable distribution system.

Preliminary sector tests at 920 K /1200 F/ of three afterburner concepts applicable for higher inlet temperatures

Abstract: Preliminary sector tests at 920 K of three afterburner concepts proposed for inlet temperature of 1260 F and comparison of results with conventional V-gutter flame holder

High Temperature Turbine Design Considerations

Abstract: The effect of higher turbine inlet temperature on the performance of an aircraft gas turbine engine can be quite dramatic. It can be used to increase the exhaust velocity of a dry turbojet to provide a higher specific thrust; to increase the by-pass ratio of a turbofan engine to improve its propulsive efficiency; to optimise the thermodynamic cycle at a higher pressure ratio to improve its specific fuel consumption; to reduce the amount of afterburner fuel flow in an augmented turbojet to improve its specific fuel consumption, or to increase the work output of a turbo-shaft engine. If the thrust or power of the engine is held constant, a size, cost and/or weight reduction can result. If the size of the engine is held constant growth capability can be provided.

Device for metering ignition fuel to the ignition unit of an afterburner associated with a turbojet engine

Abstract: An installation for metering the ignition fuel to an ignition unit of an afterburner forming part of a jet engine, which utilizes a control device for regulating the injection period and/or the quantity of the ignition fuel as a function of engine parameters which vary with varying ambient conditions.

Rotary afterburner for internal combustion engines

Abstract: A ROTARY AFTERBURNER FOR INTERNAL COMBUSTION ENGINES INCLUDES A ROTARY HEAT EXCHANGER IN THE FORM OF A HONEYCOMB MATRIX LOCATED WITHIN A COMBUSTION CHAMBER INTO WHICH EXHAUST GASES FROM THE ENGINE EXHAUST MANIFOLD ARE INTRODUCED AFTER PASSING THROUGH ONE SECTION OF THE ROTATING HEAT EXCHANGER. THE EXHAUST GASES ARE BURNED IN THE COMBUSTION CHAMBER AND THENCE ARE PASSED THROUGH ANOTHER SECTION OF THE ROTATING HEAT EXCHANGER AND FINALLY EXHAUSTED TO ATMOSPHERE THROUGH AN EXHAUST PIPE.

Gas turbine engine emergency speed control system

Abstract: A control system for an aircraft gas turbine engine is shown to include emergency provisions for overriding the throttle position and discontinuing afterburner operation while setting engine speed at some preselected value. Two solenoid valves are included in the control system, one to deliver a servo signal to an "rpm lockup" device in the main fuel control and the other to interrupt a control signal to the afterburner fuel valve.

Blow-in door actuation for afterburner nozzle

Abstract: THE BLOW-IN-DOORS FOR AN EXHAUST NOZZLE ARE HELD IN OPEN POSITION BY AN AIR PISTON THAT PERMITS THE DOORS TO CLOSE WHEN A PREDETERMINED PRESSURE DIFFERENTIAL IS BUILT UP ON THE DOORS. THE AIR PRESSURE FOR ACTUATING THE PISTON MAY BE A SELECTED COMPRESSOR PRESSURE SO THAT THE PRESSURE VARIES WITH ENGINE OPERATING CONDITIONS AND THUS THE REQUIRED PRESSURE FOR CLOSING THE DOORS WILL VARY CORRESPONDINGLY.

High Temperature Turbine Design Considerations

Abstract: THE effect of higher turbine inlet temperature on the performance of an aircraft gas turbine engine can be quite dramatic. It can be used to increase the exhaust velocity of a dry turbojet to providea higher specific thrust; to increase the bypass ratio of a turbofan engine to improve its propulsive efficiency; to optimize the thermodynamic cycle at a higher pressure ratio to improve its specific fuel consumption; to reduce the amount of afterburner fuel flow in an augmented turbojet to improve its specific fuel consumption, or to increase the work output of a turboshaft engine. If the thrust or power of the engine is held constant, a size, cost and/or weight reduction can result. If the size of the engine is held constant growth capability can be provided.

Afterburner fuel manifold flow sensor and igniter control

Abstract: Apparatus for sensing the rate of fuel flow into an afterburner fuel manifold and energizing ignition apparatus for a predetermined time interval to ignite the after afterburner fuel flow when the manifold is filled to a predetermined extent as well as providing a simultaneous output signal to release the gates of a variable area exhaust nozzle downstream from the afterburner.