Topic
Afterburner
About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.
Papers published on a yearly basis
Papers
More filters
01 Mar 2002
TL;DR: In this paper, jet engine exhaust particulate samples collected from four military aircraft engines were analyzed for particle morphology and polycyclic aromatic hydrocarbons (PAHs) in four modes: approach, idle, military, and intermediate.
Abstract: : In this study, jet engine exhaust particulate samples collected from four military aircraft engines were analyzed for particle morphology. Particulate emissions from three of the engines were also analyzed for polycyclic aromatic hydrocarbons (PAHs). The F118, F404, T58, and T64 engines were tested in four modes: approach, idle, military, and intermediate. The F404 engine was also tested in afterburner mode. Conclusions and recommendations are made based on the test results.
Patent•
12 Apr 2021
TL;DR: In this article, a two-engine aircraft power plant and a method of controlling said aircraft was presented, which includes two combined engines, each of which comprises three-circuit turbojet engine with afterburner cavity and straight-flow air-jet engine.
Abstract: FIELD: aviation.SUBSTANCE: invention relates to a two-engine aircraft power plant and a method of controlling said aircraft. Power plant includes two combined engines, each of which comprises three-circuit turbojet engine with afterburner cavity and straight-flow air-jet engine, and has two independent air channels, one of which is connected to inlet of turbojet engine, and the second one is connected to inlet of straight-flow air-jet engine. Air intakes have two controlled flaps connected to inputs of turbojet engines. Outputs of the third circuits are connected to the direct-current motors inputs. Direct-flow motors have annular continuously-detonation combustion chambers arranged around the afterburner cavities outer surfaces, each of which contains permeable matrix nozzles in the form of semi-rings. Semi-rings in one engine are located in horizontal plane, and in other—in vertical plane, at that vertical and horizontal axes of symmetry between semi-rings are mutually perpendicular. Method of power plant control uses traditional control of turbojet engines with Mach speeds M≤3. When the flight speed M>3 is reached, the turbojet engines are switched off and the direct-flow air-jet engines are switched on, which increase the flight speed of the aircraft to M>5. To control the thrust vector in one half-ring of the permeable matrix atomiser, increasing the fuel mass flow rate, and in the other semi-ring reducing, difference of thrust values at the outlet is used to form the moment providing the aircraft turning.EFFECT: power plant combines capabilities and advantages of various types of air-jet engines and method of control to provide optimum weight and efficiency at small weights and overall dimensions in a wide range of flight speeds and altitudes.6 cl, 6 dwg
TL;DR: In this paper, the authors used diesel fuel in a gas turbine engine to assess the effects of fuel enrichment and residence time of the products in a precombustion chamber on combustion processes within the engine such as flame ignition time and stability.
Abstract: The authors use a diesel fuel in a gas turbine engine to assess the effects of fuel enrichment and residence time of the products in a precombustion chamber on combustion processes within the engine such as flame ignition time and stability. They also perform gas chromatography on the combustion products at the prechamber exit and the afterburner in order to determine the effect of their residence time on their composition.
Patent•
25 Jan 2018
TL;DR: In this article, a spray nozzles with a micro-swirl is used to reduce the length of the afterburner combustion and reduce emissions of harmful substances into the atmosphere.
Abstract: FIELD: engines and pumps.SUBSTANCE: afterburner combustion chamber of turbojet engine contains chassis, connected to the turbine, nozzle, fuel, or fuel-air collectors, injectors are connected with the jets. The spray nozzles are equipped with micro-swirlers. Each of the micro-swirlers is a cone-shaped nozzle casing with roundings of a small radius R at the base of the cone located near the atomizer. Nozzles with a micro-swirl are connected behind the manifolds by the flow of air so that the injected fuel or fuel-air mixture coincides in the direction of travel with the flow of air and combustion products behind the turbine in the afterburner combustion chamber. At the base of the cone of the nozzle body is a cylindrical spray nozzle.EFFECT: invention allows to reduce emissions of harmful substances into the atmosphere and decrease the length of the afterburner combustion.2 cl, 3 dwg
Patent•
09 Mar 2017
TL;DR: In this paper, the main and after-burner combustion chambers are combined into a single combustion chamber, where the main area is permanent, the afterburner is for chamber working at the augmented rating.
Abstract: FIELD: power industry.SUBSTANCE: aircraft gas turbine engine combustion chamber, where the combination of the main combustion chamber and afterburner into a single chamber is realized. The combustion chamber has two combustion areas: the main and the afterburner. The main area is permanent, the afterburner is for chamber working at the augmented rating. The positive result is due to the fact, that the combustion conditions in the main combustion chamber afterburner area of at the same values of the total air excess ratio is objectively better, than in the afterburners of similar gas turbine engines.EFFECT: invention allows to expand the operating modes range of the main combustion chambers according to the total air excess ratio.6 cl, 3 dwg