Afterburner

About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.

Characteristics of flow and thrust variations in a jet engine with a variable area nozzle

Abstract: A numerical analysis of the internal flow field in an exhaust converging-diverging nozzle of a jet engine has been carried out. Variable area nozzle is required in a jet engine for optimal expansion and adjusting back pressure in the engine when the afterburner is operated. Steady-state and transient analyses are carried out for each condition with and without afterburner operation and as a function of the location of the nozzle flap. For a baseline power condition, mixture composition of combustion products is calculated by the chemical equilibrium analysis and the cold flow analysis is carried out based on the mixture composition. For the afterburner operating condition, additional fuel is injected from the inlet boundary and numerical analyses of reactive flow fields are carried out. With variable area nozzle adopted, combustion fields are variable in time, leading to periodically variable thrust. When nozzle flap is in a closed state, nozzle internal pressure and temperature are increased upon the afterburner operation and moment of a force at the pivot point is increased as well. These undesirable phenomena can be solved by control of a variable area nozzle. And, thrust level is also maximized by nozzle variation. During nozzle variation, unsteadiness effect is observed because of response lag of internal flow to nozzle variation. Both the design pressure and the optimum expansion of the nozzle can be attained by adopting the independent operation of a variable area nozzle.

Evaluation of hydrogen fuel in a full-scale afterburner

Abstract: Report presenting a performance investigation using hydrogen fuel in a full-scale afterburner with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, some concentric ring and some radial bar, were investigated at a specified burner inlet velocity over a range of burner-inlet total pressures.

Compact afterburners for gas turbine engines

Abstract: An afterburner apparatus (10) that utilizes a novel swirl generator (30) for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator (30) converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator (30) effects a toroidal outer recirculation zone (640) and a central recirculation zone (610), which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length. Inherent with this swirl afterburner concept are design compactness, light weight, lower cost, smooth and efficient combustion, high thrust output, wide flammability limits, continuous operation at stoichiometric fuel/oxidizer mixture ratios, no combustion instabilities, and relatively low pressure losses.

Installation for cleaning ventilation wastes

Abstract: The installation includes a housing (1) containing a furnace (2) with a burner (3). A nozzle (4) is located above the furnace (2). An afterburner chamber (5) is located behind the furnace (2), and behind it a heat exchanger (11). Catalytic elements (6, 7) are positioned in the afterburner chamber (5), having the shape of two parallelogram prisms whose upper edges touch. A V-shaped diffuser grid (16) is provided between the heat exchanger (11) and the afterburner chamber (5), with its peak facing the afterburner chamber (5). The nozzle (4) is positioned so that it is possible for its axis (8) to intersect the axis (9) of the burner (3).