Doklady Physics · 2020 · 18 citations · 5 references
EngineeringAerospace EngineeringMechanical EngineeringCombustionHeat TransferInternal Combustion EnginesCombustion FundamentalsCombustion In EnginesCombustion ProcessesFuel CharacteristicsIgnitionTurbojet EnginesAfterburnersCombustion In Jet EnginesDetonationDetonation CombustionDetonation WavesFuel ConsumptionSpecific Fuel ConsumptionThrust Generation
Abstract For the first time, a detonation afterburner (DA) for continuous detonation combustion of TS-1 aviation kerosene was developed, manufactured, and tested. Test fires of the DA in combination with a TJ100S-125 small-sized single-circuit turbojet engine were carried out on a ground test bench. In the test fires, stable modes of continuous detonation combustion of aviation kerosene were registered: a near-limit mode of longitudinally pulsating detonation (LPD) and a spin detonation (SD) mode with one detonation wave. Compared to a conventional afterburner, at the same in-chamber pressure, the specific fuel consumption in the DA was 30% lower and the specific thrust and thrust boosting coefficient were 30% higher. It is shown that, when operating in the LPD mode, the average heat flux to the DA walls is about 0.5 MW/m2 and, in the SD mode, 0.86 MW/m2. These values indicate the high potentiality of the DA when used in advanced jet engines.
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