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1983•21st Aerospace Sciences MeetingRequires access

Investigation of a dual inlet side dump combustor using liquid fuel injection

F. D. Stull, R. R. Craig, G. D. Streby

Open publisher page 6 citations

Abstract

The characteristics of a dual-inlet side-dump combustor configuration suitable for ducted rocket missiles was investigated by injecting a liquid fuel (JP-4) into the two rectangular inlet ducts upstream of the dump plane. Cold flow water tunnel simulations were obtained by injecting small air bubbles into the inlet arms of a plexiglas model and illuminating these by a high intensity slit light source. Combustor performance was obtained by testing a similar stainless steel model on a combustor thrust rig. Combustion efficiency, combustor total pressure loss, lean blow-out limits, combustor pressure oscillations, and surface heating patterns were obtained. A threedimensional computer code using the k-e turbulence model was used to predict the corresponding cold flowfields with good agreement.

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What this paper is about

The characteristics of a dual-inlet side-dump combustor configuration suitable for ducted rocket missiles was investigated by injecting a liquid fuel (JP-4) into the two rectangular inlet ducts upstream of the dump plane. Cold flow water tunnel simulations were obtained by injecting small air bubbles into the inlet arms of a plexiglas model and illuminating these by a high intensity slit light source. Combustor performance was obtained by testing a similar stainless steel model on a combustor thrust rig. Combustion efficiency, combustor total pressure loss, lean blow-out limits, combustor pressure oscillations, and surface heating patterns were obtained. A threedimensional computer code using the k-e turbulence model was used to predict the corresponding cold flowfields with good agreement.

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OpenAlex reports 6 citations for this work. Citation counts describe recorded attention and do not establish research quality.

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Available abstract

The characteristics of a dual-inlet side-dump combustor configuration suitable for ducted rocket missiles was investigated by injecting a liquid fuel (JP-4) into the two rectangular inlet ducts upstream of the dump plane. Cold flow water tunnel simulations were obtained by injecting small air bubbles into the inlet arms of a plexiglas model and illuminating these by a high intensity slit light source. Combustor performance was obtained by testing a similar stainless steel model on a combustor thrust rig. Combustion efficiency, combustor total pressure loss, lean blow-out limits, combustor pressure oscillations, and surface heating patterns were obtained. A threedimensional computer code using the k-e turbulence model was used to predict the corresponding cold flowfields with good agreement.

Key concepts: Combustor, Inlet, Dual (grammatical number), Environmental science, Petroleum engineering, Fuel injection, Liquid fuel, Materials science

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