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Theoretical Performance Evaluation of a Marine Solid Propellant Water-Breathing Ramjet Propulsor

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Theoretical Performance Evaluation of a Marine Solid Propellant Water-Breathing Ramjet Propulsor Journal of Marine Science and Engineering Article Theoretical Performance Evaluation of a Marine Solid Propellant Water-Breathing Ramjet Propulsor Nachum E. Eisen * and Alon Gany Faculty of Aerospace Engineering, Technion—Israel institute of Technology, Haifa 3200003, Israel; [email protected] * Correspondence: [email protected] Received: 24 November 2019; Accepted: 18 December 2019; Published: 20 December 2019 Abstract: This work analyzes and presents theoretical performance of a marine water-breathing ramjet propulsor. A conceptual scheme of the motor is shown, the equation of thrust is presented, and the dependence on cruise velocity and depth are discussed. Different propellant compositions, representing a wide variety of formulations suitable for propelling a water-breathing ramjet, are investigated. The theoretical results reveal that the specific impulse of a water-breathing ramjet can increase by as much as 30% compared to a standard rocket, when using a conventional hydroxyl terminated polybutadiene (HTPB)-ammonium perchlorate (AP) propellant, which does not react chemically with the water. When employing a water-reactive propellant containing metal particles such as magnesium or aluminum, the specific impulse may be more than doubled. The thrust coefficient of the propulsor was computed at different cruise velocities and depths and was found to be greater than the predictable drag even at significant depth. Keywords: underwater propulsion; water-breathing ramjet; marine ramjet; water ducted rocket 1. Introduction The search for underwater high-speed cruising reveals certain high-thrust marine propulsion concepts which are parallel in principle to their aeronautical counterparts [1]. Rocket engines can propel high-speed underwater vehicles just like aeronautical vehicles. Independent of speed and ambience medium, rocket engines provide very high thrust and do not need air for their operation, hence, they can suite underwater vehicles. However, their specific fuel (propellant) consumption is very high and, thus, they enable only a limited range. Therefore, propulsion principles utilizing the surrounding water as a working fluid as well as a chemical reactant (usually oxidizer), have been considered [2–8]. One of the interesting concepts for propelling high-speed underwater vehicles is the solid propellant water-breathing ramjet [4–8]. It is a powerful propulsion means, independent of atmospheric air, hence, it can operate fully and deeply underwater. The basic principle of the marine water-breathing ramjet is to utilize the high dynamic (ram) pressure, resulting from the high-speed motion, in order to ingest water into the combustion chamber of the motor, thus increasing the thrust and energetic performance of the propulsor. This work focuses on theoretical prediction of the performance of a water-breathing underwater solid propellant ramjet motor. The design of an underwater solid propellant water-breathing ramjet is similar to the design of an aeronautical ducted rocket. Water enters the motor through an inlet located in the front of the vehicle and is sprayed through a porous wall into the combustion chamber. Due to the high temperature in the combustion chamber, the incoming water boils and then mixes with the combustion products, forming a high-speed exhaust jet that provides the thrust necessary to propel the vehicle. A conceptual illustration of a solid propellant water-breathing ramjet is presented in Figure1. J. Mar. Sci. Eng. 2020, 8, 8; doi:10.3390/jmse8010008 www.mdpi.com/journal/jmse J. Mar. Sci. Eng. 2020, 8, 8 2 of 11 theJ. Mar. vehicle. Sci. Eng. A2020 conceptual, 8, 8 illustration of a solid propellant water-breathing ramjet is presented2 of in 11 Figure 1. FigureFigure 1. 1. ConceptualConceptual illustration illustration of of a a marine marine solid solid propellant propellant water-breathing water-breathing ramjet. ramjet. SimilarlySimilarly to solidsolid rocket rocket motors motors (SRMs), (SRMs), the the solid solid propellant propellant grain grain can provide can provide high thrust high without thrust withoutthe addition the addition of water, of aswater, well. as Nevertheless, well. Nevertheless, the mere the additionmere addition of water, of water, entering entering through through an inlet an inletdue due to the to vehiclethe vehicle motion, motion, and and its furtherits further conversion conversion into into steam steam because because of theof the high high heat heat release release of ofthe the burning burning solid solid propellant, propellant, increases increases the the thrust thrust andand thethe specificspecific impulse,impulse, even with no no chemical chemical interaction.interaction. Greater Greater performance performance improvement improvement ca cann be be obtained obtained when when employing employing water-reactive water-reactive propellantpropellant compositions, compositions, which which utilize utilize the the incoming incoming wa waterter as as an an oxidizer oxidizer to to increase increase heat heat release release in in additionaddition to to using using it it as as a a source source for for steam steam which which increases increases the the mass mass flow flow rate rate of of the the exhaust exhaust jet. jet. Certain Certain metalsmetals are knownknown toto reactreact very very exothermically exothermically with with water water and and may may be considered be considered for inclusion for inclusion as water as waterreactive reactive ingredients ingredients in propellants. in propellants. Typically, Typicall the reactiony, the reaction of metals of with metals water with generates water generates hydrogen hydrogenbesides metal besides oxides. metal Table oxides.1 presents Table 1 theoretical presents th physicaleoretical and physical thermochemical and thermochemical properties ofproperties selected ofmetals. selected While metals. the While gravimetric the gravimetric heat of reaction heat of is reaction related tois therelated mass to of the fuel mass (propellant) of fuel (propellant) carried on carriedboard, theon board, volumetric the volumetric heat of reaction heat reflectsof reaction the energyreflects perthe unitenergy volume per unit and volume is mainly and significant is mainly in significantvolume-limited in volume-limited systems. systems. TableTable 1. MaximumMaximum theoretical gravimetricgravimetric andand volumetric volumetric heat heat of of reaction reaction and and hydrogen hydrogen generation generation for forselected selected metals metals with with liquid liquid water, water, listed listed in the in order the order of their of volumetric their volumetric heat of heat reaction of reaction (data adapted (data adaptedfrom [9]). from [9]). Gravimetric Heat of Volumetric Heat of Specific VolumetricSpecific H Density Specific H Mole 2 Fuel GravimetricReaction VolumetricReaction Specific2 Mole Production [g/cm3] Production [mol/g] Volumetric Density Heat[kJ/g] of [kJHeat/cm3] of Mole [mol/cm3] Fuel Mole Be/ 1.85 Reaction 36.1 Reaction 66.7 Production 0.111 0.21 Production / / / B 2.35 18.4 43.2 0.139/ 0.34 BeAl 2.701.85 15.236.1 40.966.7 0.0550.111 0.150.21 BZr 6.492.35 5.718.4 37.243.2 0.0220.139 0.140.34 AlMg 1.742.70 13.015.2 22.640.9 0.0410.055 0.0720.15 ZrLi 0.546.49 25.55.7 13.837.2 0.0720.022 0.0390.14 MgNa 0.971.74 2.813.0 2.722.6 0.0220.041 0.0210.072 Li 0.54 25.5 13.8 0.072 0.039 NaIt is apparent0.97 from Table12.8 that beryllium reacts2.7 extremely exothermically0.022 with water0.021 both in terms of weight and volume, yet, beryllium and its products are notoriously toxic and therefore are ruledIt is apparent out. Second from to Table beryllium 1 that isberyllium boron, which reacts demonstrates extremely exothermically a promising theoreticalwith water heat both and in termsgas (i.e., of weight hydrogen) and volume, release. yet, In practice,beryllium it and is hard its products to obtain are high notoriously combustion toxic e ffiandciency therefore of boron are ruled(though out. Rosenband Second to etberyllium al. [10] haveis boron, demonstrated which demonstrates combustion a ofpromising boron in theoretical steam), and heat in additionand gas (i.e.,boron hydrogen) is a relatively release. expensive In practice, ingredient. it is hard Hence, to obtain for practical high combustion applications, efficiency aluminum of boron is commonly (though Rosenbandconsidered. et Aluminum al. [10] have reacts demonstrated with water tocombustion form aluminum of boron oxide in steam), (alumina) and or in aluminum addition boron hydroxide, is a relativelyand hydrogen, expensive while releasingingredient. asignificant Hence, for amount practical of heat, applications, as presented aluminum in Equation is (2). commonly However, considered.aluminum does Aluminum not combust reacts readily with as water a thin layerto form of aluminum aluminum oxide oxide naturally (alumina) forms onor thealuminum exposed hydroxide,surfaces of and the aluminumhydrogen, particleswhile releasing and passivates a significant the metal amount substrate of heat, to as inhibit presented oxidation in Equation progression. (2). However,Different approachesaluminum does for overcoming not combust the readily alumina as a coatingthin layer problem of aluminum are discussed oxide naturally extensively forms in theon theliterature exposed [11 surfaces–14]. Zirconium of the alumin hasum high particles volumetric and heatpassivates of reaction, the metal yet lowersubstrate than to that inhibit of aluminum.oxidation progression.In addition, itsDifferent other energetic approaches
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