Three-Dimensional Hybrid RANS/LES Simulations of a Supercritical Liquid Nitrogen Jet

Hosangadi, Ashvin; Lee, Chun P.; Kannepalli, Chandrasekhar; Arunajatesan, Srinivasan

doi:10.2514/6.2008-5227

Cited by 23 publications

(8 citation statements)

References 17 publications

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“…The solver has been used and validated in a wide variety of aerospace applications. [14][15][16][17] In JAXA, the solver has been used for various applications of liquid rocket engines and extensively validated over the last three years. [18][19][20][21][22][23] In this study, conjugated fluid and heat transfer simulations were performed by considering coolant flows in cooling channels and the surrounding chamber wall.…”

Section: A Numerical Methods For Fluid Flow and Heat Transfermentioning

confidence: 99%

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Negishi¹,

Daimon²,

Kawashima³

et al. 2012

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

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In recent years, methane has attracted attention as a propellant for liquid rocket engines because of its various advantages compared to typical propellants such as hydrogen. When methane is used as a coolant for a regenerative cooling system, its near-critical thermodynamic and transport properties experience large variations because its critical pressure is higher than that of typical propellants; this significantly influences the flowfield and heat transfer characteristics. Therefore, adequate understanding of the flowfield and heat transfer characteristics of methane in regenerative cooling channels is a prerequisite for future engine development. In this study, conjugated coolant and heat transfer simulations were performed to investigate the flowfield and heat transfer characteristics of transcritical methane flows in a sub-scale methane-cooled thrust chamber. The computed results were validated against experimental data measured in hot firing tests. They compared well with the measured pressures and temperatures in cooling channels, and wall temperatures were within the permitted levels. Detailed flow analysis revealed peculiar flow structures in the cooling channel: a strong secondary flow induced in the concave-heated part in the channel throat section and the coexistence of two different gas phases-ideal and real-in a single cross-section in the cylindrical region. A high wall temperature appeared in the cylindrical region of the thrust chamber under the considered conditions; this was due to the heat transfer deterioration induced by an M-shaped velocity profile and a turbulentheat flux reduction. Nomenclature a, b,  = coefficients in cubic-type equation of state C p = constant pressure heat capacity G = mass flow rate H = channel height h = heat transfer coefficient Pr = Prandtl number p = pressure q = heat flux R = gas constant Re = Reynolds number R u = universal gas constant s = normal distance T = temperature u = streamwise velocity W = molecular weight x, y, z = coordinate system Z = compressibility factor y + = normalized wall distance 2  = thermal conductivity  = viscosity  = density Subscripts b = bulk c = coolant cr = critical cw = coolant-side wall gw = hot-gas-side wall in = inlet out = outlet t = turbulent throat = throat pcr = pseudo-critical w = wall

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Section: A Numerical Methods For Fluid Flow and Heat Transfermentioning

confidence: 99%

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Negishi¹,

Daimon²,

Kawashima³

et al. 2012

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

View full text Add to dashboard Cite

show abstract

“…g., see the range of 100 to 200 K). Therefore, as also stated in [11], small temperature §uctuations lead to large density §uctuations and vice versa owing to the strong variation in thermodynamics in this §ow regime. On the other hand, quite large temperature §uctuations occur in Case 2 at the shear layer between the outer H 2 jet at 52 K and the chamber N 2 §uid at 810 K. This may be simply due to the large temperature di¨erence of -T ≈ 750 K between the two §uids, which is quite di¨erent from -T ≈ 45 K between the inner and outer jets or those of Case 1.…”

Section: Fluctuation Flow Characteristicsmentioning

confidence: 52%

“…2a). No perturbations are introduced; since strong unsteady §ow ¦elds are generated owing to the shear layers between the two jets, considerable in §uence of such perturbation or §uctuation on jet dynamics would not be expected [11]. A slip wall boundary is imposed at the boundaries in the y-and z-directions.…”

Section: Progress In Propulsion Physicsmentioning

confidence: 99%

Numerical simulations of mixing under supercritical pressures of a shear coaxial injector using a high-order method: effect of outer jet temperature

Terashima

Koshi

2016

Progress in Propulsion Physics

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A three-dimensional (3D) simulation of N 2 /H 2 mixing for a coaxial injector under a supercritical pressure of 10 MPa is conducted using a highorder numerical method. Two outer H 2 jets with injection temperatures of approximately 52 and 462 K are applied while an inner N 2 jet with an injection temperature of approximately 97 K is applied. The mean and §uctuation properties and instantaneous §ow ¦elds are discussed in order to characterize the detailed mixing features for the two injection conditions. A clear dependence of dense-core length on the momentum §ux ratio is also demonstrated.

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“…a two-dimensional cut completely describes the problem. However, numerical investigations of Hosangadi et al 7 show a helical instability for a cryogenic nitrogen injection with co-flow, hence this assumption might not be valid. Clearly, in presence of three-dimensional instabilities, the flow is not steady.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Effect of Injector Wall Heat Flux on Cryogenic Injection

Banuti¹,

Hannemann²

2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This paper reports on numerical investigation and discussion of a cryogenic injection test case. This is a first step towards a numerical model for high pressure liquid rocket engine injection. Experiments with nitrogen injection at supercritical pressures are an accepted way of studying flow phenomena relevant for high pressure liquid rocket engines without introducing the complexities of mixing and combustion. CFD simulations of these cryogenic injection cases are found to typically agree on predicting a region of constant high density, extending some 10 injector diameters downstream into the chamber. This is in agreement with the traditional interpretation of liquid injection where instabilities on the phase boundary grow until the jet disintegrates. However, many experiments do not show this behavior: exceeding the critical pressure of the injected fluid, phase interfaces seize to exist, the jet tends to behave more like a dense gas jet with a rapid drop off of density starting at the injector exit. It is thus unclear whether the concept of a liquid core length is still true for thermodynamic states at temperatures near the critical point and supercritical pressures. To study this, experimental and numerical boundary conditions have been analyzed. Computations have been carried out using the DLR TAU code extended by a treatment for real gas thermodynamics. It has been found that the absence of a dense core, as found in experiments, can be reproduced numerically if numerical boundary conditions are chosen appropriately: taking into account heat transfer inside the injector leads to a preheating of the cryogenic stream and the development of a distinct radial density profile. This preheated jet then shows the more realistic immediate reduction of density instead of a dense core.

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Three-Dimensional Hybrid RANS/LES Simulations of a Supercritical Liquid Nitrogen Jet

Cited by 23 publications

References 17 publications

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Numerical simulations of mixing under supercritical pressures of a shear coaxial injector using a high-order method: effect of outer jet temperature

Effect of Injector Wall Heat Flux on Cryogenic Injection

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