Journal ArticleDOI
Influence of a Conical Axial Injector on Hybrid Rocket Performance
Carmine Carmicino,A. Russo Sorge +1 more
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In this paper, the axial-symmetric polyethylene cylindrical grains through two different injector configurations: an axial conical subsonic nozzle and a radial injector.Abstract:
This paper was aimed at analyzing the static engine firings results obtained by means of a hybrid rocket where gaseous oxygen was supplied into axial-symmetric polyethylene cylindrical grains through two different injector configurations: an axial conical subsonic nozzle and a radial injector. The axial injector is considered interesting because of its easy design and the remarkable feature that it produces no significant pressure oscillations for the stabilizing effect due to the hot gas recirculation zone established within the combustion port. To take advantage of its qualities, the assessment of the regression rate variations under the flow field generated by this configuration is required. For the investigated set of operating conditions, the instantaneous regression rates exhibit a time-and-space dependence caused by the impinging jet zone dynamics, while the average regression rates are higher and less mass flux dependent than those achieved with the radial injection motor and expected from the turbulent flow through pipes. A comparison to the data from the radial injector was further drawn in terms of combustion efficiency, fuel consumption profiles, and combustion stability. The radial injector, at the same mass flux and pressure, produces lower regression rates, high pressure oscillations and worse combustion efficiency at the same L*, but more uniform fuel consumption.read more
Citations
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Journal ArticleDOI
Numerical Analysis of Nozzle Material Thermochemical Erosion in Hybrid Rocket Engines
Daniele Bianchi,Francesco Nasuti +1 more
TL;DR: In this paper, the erosion behavior of graphite nozzles in hybrid engines at different operating conditions and compare results with those obtained for solid motors was studied. But the main distinctive feature of hybrid engine operating conditions is a greater concentration of oxygen-containing combustion products than solid motors.
Journal ArticleDOI
Acoustics, Vortex Shedding, and Low-Frequency Dynamics Interaction in an Unstable Hybrid Rocket
TL;DR: In this article, the influence of the oxidizer-injection configurations on the motor stability is thoroughly examined, and the role of vortex shedding in both the pre- and post-combustion chamber is considered as the main driving mechanism of this latter behavior.
Review of Solid-Fuel Regression Rate Behavior in Classical and Nonclassical Hybrid Rocket Motors
TL;DR: In this article, a modified blowing parameter was proposed for the Arrhenius preexponential constant, where the parameter exp(q′′ r/(Gcf /2) c ) is defined as the skin-friction coefficient of the gas isobaric specific heat.
Journal ArticleDOI
Trade-off between paraffin-based and aluminium-loaded HTPB fuels to improve performance of hybrid rocket fed with N2O
TL;DR: In this paper, a series of static tests on two hybrid rocket engines of different lab scales have been carried out by burning pure HTPB, aluminium-loaded HTPB or a paraffinic fuel with gaseous nitrous oxide.
Journal ArticleDOI
Experimental Investigation into the Effect of Solid-Fuel Additives on Hybrid Rocket Performance
Carmine Carmicino,A. Russo Sorge +1 more
TL;DR: In this article, an experimental performance evaluation, conducted with static firings of a laboratory-scaled hybrid rocket burning gaseous oxygen and several fuel combinations, aimed at raising the fuel regression rate is addressed.
References
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Journal ArticleDOI
An algorithm with guaranteed convergence for finding a zero of a function
TL;DR: An algorithm is presented for finding a zero of a function which changes sign in a given interval using linear interpolation and inverse quadratic interpolation with bisection and ALGOL 60 procedures.
Journal ArticleDOI
Turbulent boundary layer combustion in the hybrid rocket
G. Marxman,M. Gilbert +1 more
TL;DR: In this article, it has been shown that the flame height above the surface should be in the range of 10% to 20% of the boundary layer thickness, depending on operating conditions.
Journal ArticleDOI
Solid-Fuel Regression Rate Behavior of Vortex Hybrid Rocket Engines
TL;DR: In this paper, the authors investigate the behavior and properties of a vortex hybrid engine with a cylindrical fuel port, where the oxidizer is injected through a swirl injector located between the aft end of the fuel grain and the inlet to the converging portion of the exit nozzle.
Journal ArticleDOI
Turbulent Heat Transfer in the Separated, Reattached, and Redevelopment Regions of a Circular Tube
K. M. Krall,E. M. Sparrow +1 more
Journal ArticleDOI
Fuel Regression Rate in Hydroxyl-Terminated-Polybutadiene/ Gaseous-Oxygen Hybrid Rocket Motors
TL;DR: The results of a systematic experimental investigation on the methods of enhancing the regression rate in hydroxyl-terminated polybutadiene (HTPB) fuel used in an HTPB/gaseous oxygen hybrid motor are presented in this paper.