A Quasi-2-D Model for the Prediction of the Wall Temperature of Rocket Engine Cooling Channels

Pizzarelli, Marco; Carapellese, S.; Nasuti, Francesco

doi:10.1080/10407782.2011.578011

Cited by 31 publications

(28 citation statements)

References 32 publications

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“…A better agreement between the two solutions could be reached by tuning of the semiempirical relations used in the quasi-2D model; in fact, despite the rectangular cross section of present channels, plain coolant skin friction and heat transfer relationships proposed for circular cross-section tubes have been used. However, as already demonstrated in [7], the overall good agreement of the quasi-2D solution with the reference 3D CFD solution in the case of HARCC does not justify further calibration of existing semiempirical models.…”

Section: Validation Of the Modelmentioning

confidence: 88%

“…For radial sections below 2 mm, the comparison must be performed with great care because the 3D CFD model describes the kinematic and thermal boundary layers while the simpli¦ed model does not. For that reason, the comparison of the two models in the near-wall region (that is, y ≃ 0) is not possible as already mentioned in [7]. The comparison between the 3D CFD and the quasi-2D results for the coolant total pressure and bulk temperature is presented in Fig.…”

Section: Validation Of the Modelmentioning

confidence: 99%

“…4b. The de¦nition of the bulk variables for the two di¨erent solutions is presented in details in [7]. Figure 4 shows that due to the incoming heat transfer rate from the hot-gas, the coolant temperature increases and that the e¨ect of the incoming heat transfer and the wall friction results in a coolant pressure loss.…”

Section: Validation Of the Modelmentioning

confidence: 99%

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Evolution of cooling-channel properties for varying aspect ratio

Pizzarelli

Nasuti

Onofri

2016

Progress in Propulsion Physics

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A trade-o¨analysis is performed on a cooling channel system representative of liquid rocket engine cooling systems. This analysis requires multiple cooling channel §ow calculations which are performed by means of a proper numerical approach, referred to as quasi-two-dimensional (2D) model. This model, which is suited to high-aspect-ratio cooling channels (HARCC), permits to have a fast prediction of both the coolant §ow evolution and the temperature distribution along the whole cooling channel structure. Before using the quasi-2D model for the trade-oä nalysis, its validation by comparison with computational §uid dynamics (CFD) results is presented and discussed. The results show that the pump power required to overcome losses in the cooling circuit can be minimized selecting a channel shaped with a suitably high aspect ratio.

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Section: Validation Of the Modelmentioning

confidence: 88%

Section: Validation Of the Modelmentioning

confidence: 99%

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Evolution of cooling-channel properties for varying aspect ratio

Pizzarelli

Nasuti

Onofri

2016

Progress in Propulsion Physics

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“…Recently, Pizzarelli et al [11] developed a quasi-2-D empirical model for regenerative cooling, which is modified based on a 2-D governing equation for coolant energy balance with 1-D conservation equations for coolant mass and momentum, to evaluate the radial thermal stratification pronounced in the HARCC (high-aspect-ratio cooling channels).…”

Section: Introductionmentioning

confidence: 99%

Effective Modeling of Conjugate Heat Transfer and Hydraulics for the Regenerative Cooling Design of Kerosene Rocket Engines

Kim

Joh

Choi

et al. 2014

Numerical Heat Transfer, Part A: Applications

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The present work is motivated to develop a unified framework to simulate multi-physical processes which are crucial for trade-off design of liquid rocket thrust chambers among propulsive performance, regenerative cooling, and pressure budget. In this paper, an effective modeling of conjugate heat transfer and hydraulics through the regenerative cooling passage has been performed to quantitatively evaluate detailed cooling designs, including spirally twisted channels and bidirectionally branched circuit, as well as to provide the wall heat flux to a compressible reacting flow solver in an interactively coupled manner. The kerosene fuel used as coolant is modeled by a three-component physical surrogate, and the fluid properties required for calculation of a Nusselt number correlation and empirical resistance coefficients are computed over the entire thermodynamic states from compressed liquid to supercritical fluid using the NIST SUPERTRAPP. The present method has been applied to an actual regeneratively cooled thrust chamber and validated against measurement of hot-firing tests in terms of temperature increase and pressure drop of the coolant through the cooling passages. Based on the numerical results, supplementary effects of peripheral fuel cooling injection and thermal barrier coating are addressed.

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“…[1][2][3][4][5][6][7] To overcome the simplification arising from one-dimensional modeling of hot-gas expansion, efforts have been made to describe the hot-gas flow-field by means of multi-dimensional CFD solvers, [8][9][10][11][12] while maintaining semi-empirical modeling for the coolant flow. Recently, coupled CFD analysis for the whole regeneratively-cooled thrust chamber has been performed.…”

Section: Introductionmentioning

confidence: 99%

Coupled Heat Transfer Analysis in Regeneratively Cooled Thrust Chambers

Betti¹,

Pizzarelli²,

Nasuti³

2012

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

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A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs in most liquid rocket engines and to provide a quick and reliable prediction of thrust-chamber wall temperature and heat flux as well as coolant-flow characteristics, like pressure drop and temperature gain in the regenerative circuit is presented and demonstrated. The coupled analysis is performed by means of an accurate CFD solver of the Reynolds-Averaged Navier-Stokes equations for the hot-gas flow and a simplified quasi-2D approach, which widely relies on semi-empirical relations, to study the problem of coolant flow and wall structure heat transfer in the cooling channels. Coupled computations of the Space Shuttle Main Engine Main Combustion Chamber are performed and compared with available literature data. Results show a reasonable agreement in terms of coolant pressure drop and temperature gain with nominal data, whereas the computed wall temperature peak is quite closer to hot-firing data than to the nominal value. © 2012 by B. Betti, M. Pizzarelli, F. Nasuti

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A Quasi-2-D Model for the Prediction of the Wall Temperature of Rocket Engine Cooling Channels

Cited by 31 publications

References 32 publications

Evolution of cooling-channel properties for varying aspect ratio

Evolution of cooling-channel properties for varying aspect ratio

Effective Modeling of Conjugate Heat Transfer and Hydraulics for the Regenerative Cooling Design of Kerosene Rocket Engines

Coupled Heat Transfer Analysis in Regeneratively Cooled Thrust Chambers

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