Cooling Channel Analysis of a LOX/LCH4 Rocket Engine Demonstrator

Pizzarelli, Marco; Betti, B.; Nasuti, Francesco; Ricci, Daniele; Roncioni, Pietro; Battista, Francesco; Salvatore, Vito

doi:10.2514/6.2014-4004

Cited by 6 publications

(4 citation statements)

References 28 publications

(25 reference statements)

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“…Additionally, an input heat flux obtained through reactive CFD analysis was defined on the hot gas side of the engine wall. The cooling channel dimensions, thrust chamber profile, and calculated results were obtained by digitizing the plots in the reference study [42]. The same case was then analyzed using ODREC.…”

Section: Resultsmentioning

confidence: 99%

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Kose,

Celik

2023

Applied Sciences

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Due to the extreme temperatures inside the combustion chambers of liquid propellant rocket engines, the walls of the combustion chamber and the nozzle are cooled by either the fuel or the oxidizer in what is known as regenerative cooling. This study presents an indigenous computational tool developed for the analysis of heat transfer in regenerative cooling of such rocket engines. The developed tool incorporates a one-dimensional (1-D) combustion analysis to calculate the thermophysical properties of the combustion gas. Basic engine properties were calculated and used to generate a thrust chamber profile based on a bell-shaped nozzle. The hot gas side was analyzed using 1-D isentropic flow assumptions, along with heat transfer correlations. The coolant side was evaluated using the hydraulic analysis in the axial direction and the heat transfer analysis in the radial direction. Thermophysical properties and the phase of the coolant were determined using the given property tables and the instantaneous state of the coolant. This flexible and computationally less demanding tool was used to analyze two small-scale engines utilizing liquid hydrocarbon fuels, which are used in modern rocket propulsion. The wall cooling analyses of a liquid oxygen (LOX)/liquid methane (LCH4) engine and a liquid oxygen (LOX)/liquid propane (LC3H8) engine are presented. Fuel and oxidizer were used separately as coolants for both engines, and both of them experienced phase change. Results reveal the advantage of the high mass flow rate of the oxidizer in cooling performance. In addition, the results of this study show that the cooling of the LOX/LC3H8 engine is somewhat more challenging compared to the LOX/LCH4 engine.

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Section: Resultsmentioning

confidence: 99%

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Kose,

Celik

2023

Applied Sciences

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“…The estimated l owski beam model is 67 cycles. Tao Chen [21] used the creep-modified P model to estimate the life of a reusable liquid engine thrust chamber in the The life prediction results offered a reference for the design of reusable thr Marco Pizzarelli [22,23] developed an algebraic model for structural and l regeneratively cooled thrust chambers. The life of instability is calculated by beam model.…”

Section: Basic Equations and Procedures Of The Porowski Beam Modelmentioning

confidence: 99%

“…The life prediction results offered a reference for the design of reusable thrust chambers. Marco Pizzarelli [22,23] developed an algebraic model for structural and life analysis of regeneratively cooled thrust chambers. The life of instability is calculated by the Porowski beam model.…”

Section: Introductionmentioning

confidence: 99%

Life Analysis of Reusable Liquid Rocket Engine Thrust Chamber

Cheng

Zhang

2022

Aerospace

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The thrust chamber’s inner wall suffers high temperature and pressure differences from the coolant channel, which limits the life of the rocket engine. Life prediction of the thrust chamber really plays an important role in reusable launch vehicle propulsion systems. The Porowski beam model is widely used in the life prediction of reusable liquid rocket engine thrust chambers, which calculates the life caused by fatigue, creep, and thinning after each firing cycle. In order to analyze the life of the thrust chamber, a LOX/Kerosene rocket engine is investigated in this paper. The life analysis consists of pressure and temperature differences and structural parameters. Two kinds of inner wall materials were chosen for comparison in this research: OFHC copper and Narloy-Z alloy. The results are presented to offer a reference for the design and manufacture of reusable rocket engine thrust chambers in the future.

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“…Traditionally, Reynolds Averaged Navier-Stokes (RANS) solvers have been extensively used in industry due to their low computational cost. In methane thrust chambers, multiple researchers have used this methodology for both the combustion chamber [10][11][12] and the cooling system [13][14][15][16][17]. The most relevant handicap of this approach is the suppression of transient behavior, which excessively restricts the degrees of freedom of the turbulent flow dynamics.…”

Section: Introductionmentioning

confidence: 99%

Subgrid Turbulent Flux Models for Large Eddy Simulations of Diffusion Flames in Space Propulsion

Martinez-Sanchis,

Sternin,

Banik

et al. 2024

Fluids

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Subgrid scale models for unresolved turbulent fluxes are investigated, with a focus on combustion for space propulsion applications. An extension to the gradient model is proposed, introducing a dependency on the local burning regimen. The dynamic behaviors of the model’s coefficients are investigated, and scaling laws are studied. The discussed models are validated using a DNS database of a high-pressure, turbulent, fuel-rich methane–oxygen diffusion flame. The operating point and turbulence characteristics are selected to resemble those of modern combustors for space propulsion applications to support the future usage of the devised model in this context.

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Cooling Channel Analysis of a LOX/LCH4 Rocket Engine Demonstrator

Cited by 6 publications

References 28 publications

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Life Analysis of Reusable Liquid Rocket Engine Thrust Chamber

Subgrid Turbulent Flux Models for Large Eddy Simulations of Diffusion Flames in Space Propulsion

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