Study of Next Booster Engine LE-X in JAXA

Kurosu, Akihide; Yamanishi, Nobuhiro; Tani, Naoki; Okita, Koichi; Ogawara, Akira; Onga, Tadaoki; Atsumi, Masahiro

doi:10.2514/6.2006-4700

Cited by 15 publications

(5 citation statements)

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“…Although the expander-type cycle is mostly used in the upper stage engines because of its limitation of system pressure and driving power for turbopumps, a feasibility study of a booster engine, called "LE-X", with expander bleed cycle is underway in Japan. 1…”

Section: Introductionmentioning

confidence: 97%

Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber)

Daimon¹,

Negishi²,

Yamanishi³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Combustion flowfields in GH2/LOX sub-scale calorimeter chambers with multi-injector elements and full-scale thrust chamber are investigated using Reynolds-Averaged NavierStokes simulation, in which the finite rate chemistry with the H 2 /O 2 detailed reaction mechanism is taken into account. The computed wall heat flux distributions are compared to that of the simplified cases to reduce a computational cost. The considered simplifications are a presence of reaction and a number of injector rows. At first, these simplifications are validated in the simulation of sub-scale chambers. The reaction is essential for the prediction of heat flux because it makes change the species distribution in a thermal boundary layer on a thrust chamber wall. A heat flux using a combustion simulation with only outermost injectors shows a good agreement with that with an original configuration near a face plate. On the other hand, it overestimates the heat flux around nozzle and throat parts. It is clarified that this overestimate comes from the shortage of unburned hydrogen near a chamber wall in the simplified method. Next, the simplification of the number of injector rows are applied to the simulation of full-scale thrust chambers. The effectiveness of this simplification for the prediction of wall heat flux is revealed. The optimal solution by using of the simplification is proven to be effective for the prediction of heat flux in a full-scale thrust chamber.

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Section: Introductionmentioning

confidence: 97%

Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber)

Daimon¹,

Negishi²,

Yamanishi³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…[1][2][3] The expander bleed cycle system with cryogenic LOX/LH2 propellants, which is employed in the current upper stage engine LE-5B of the H-IIA launch vehicle, has been applied to the LE-X engine because of its simplicity and robustness. The engine cycle schematic and a three dimensional model are illustrated in Fig.…”

Section: Introductionmentioning

confidence: 99%

Flowfield and Heat Transfer Characteristics in the LE-X Expander Bleed Cycle Combustion Chamber

Negishi¹,

Daimon²,

Kawashima³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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In Japan, a feasibility study of the new "LE-X" booster engine has been underway since 2005. One of the key technologies of the LE-X engine development is a regenerative cooling design to produce enough power to drive the turbopumps. The LE-X engine employs an elongated chamber design to pick up enough heat energy in the regenerative cooling channels. In the current study, a fully conjugated combustion and heat transfer simulation was performed to investigate the flow field and heat transfer characteristics for the regeneratively cooled combustion chamber of the LE-X engine. A three-dimensional Reynolds-averaged Navier-Stokes simulation was used to consider the injection and combustion processes of propellants on the hot-gas side, heat conduction in the chamber wall, and cooling channel flows. Details on the three-dimensional flow and thermal characteristics of the combustion chamber were clarified in the hot-gas and coolant side domains. In particular, significant thermal stratification was found to form in the radial direction of the cooling channel in the elongated cylindrical part of the chamber, which degraded the heat transfer and resulted in the highest wall temperature there. NomenclatureA = surface area C = heat capacity of solid C p = constant pressure heat capacity D = mass diffusivity  = dissipation rate of turbulence kinetic energy H = cooling channel height h = heat transfer coefficient l = length k = turbulence kinetic energy  = thermal conductivity Le = Lewis number  = dynamic viscosity Pr = Prandtl number p = pressure q = heat flux r = chamber radius s = normal distance Re = Reynolds number T = temperature t = time u = velocity x, y, z = Cartesian coordinates y + = normalized wall distance 2 Subscripts ave = average b = bulk property c = coolant cw = coolant side wall gw = hot-gas side wall int = interface peri = perimeter

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“…N order to achieve high-efficiency and high-robustness, the expander-bleed cycle was chosen as an engine cycle for the next generation booster engine, called LE-X ( Fig.1) [1] [2]. The LE-X is considered to use liquidhydrogen as a fuel, and liquid-oxygen as an oxidizer.…”

Section: Introductionmentioning

confidence: 99%

“…The energy source of the driving gas for the turbo-pump is generated by the heat-exchange around the main combustion chamber in expander-bleed cycle, thus high efficiency pumps and turbines are required. [1] I Fig. 1…”

Section: Introductionmentioning

confidence: 99%

Feasibility Study of Multi Objective Shape Optimization for Rocket Engine Turbopump Blade Design

Tani¹,

Oyama²,

Okita³

et al. 2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Study of Next Booster Engine LE-X in JAXA

Cited by 15 publications

References 0 publications

Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber)

Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber)

Flowfield and Heat Transfer Characteristics in the LE-X Expander Bleed Cycle Combustion Chamber

Feasibility Study of Multi Objective Shape Optimization for Rocket Engine Turbopump Blade Design

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