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Journal ArticleDOI

Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines

01 Mar 2015-Journal of Thermal Science and Engineering Applications (American Society of Mechanical Engineers)-Vol. 7, Iss: 1, pp 011012
About: This article is published in Journal of Thermal Science and Engineering Applications.The article was published on 2015-03-01. It has received 8 citations till now. The article focuses on the topics: Regenerative cooling (rocket) & Internal combustion engine cooling.
Citations
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Journal ArticleDOI
TL;DR: In this article, the regenerative cooling channels designed in a variety of non-uniform patterns are proposed and the conjugated flow and heat transfer behaviors of coolant and solid combustion chamber are numerically investigated.

31 citations

01 Jan 2016

6 citations


Additional excerpts

  • ...Rajagopal [59] analyzed the effects of radiation...

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Journal ArticleDOI
07 Jun 2022-Energies
TL;DR: In this article , the authors discuss the results concerning the cooling jacket equipping the liquid-oxygen/liquid-methane demonstrator, designed and manufactured within the scope of HYPROB-NEW Italian Project.
Abstract: The successful design of a liquid rocket engine is strictly linked to the development of efficient cooling systems, able to dissipate huge thermal loads coming from the combustion in the thrust chamber. Generally, cooling architectures are based on regenerative strategies, adopting fuels as coolants; and on cooling jackets, including several narrow axial channels allocated around the thrust chambers. Moreover, since cryogenic fuels are used, as in the case of oxygen/methane-based liquid rocket engines, the refrigerant is injected in liquid phase at supercritical pressure conditions and heated by the thermal load coming from the combustion chamber, which tends to experience transcritical conditions until behaving as a supercritical vapor before exiting the cooling jacket. The comprehension of fluid behavior inside the cooling jackets of liquid-oxygen/methane rocket engines as a function of different operative conditions represents not only a current topic but a critical issue for the development of future propulsion systems. Hence, the current manuscript discusses the results concerning the cooling jacket equipping the liquid-oxygen/liquid-methane demonstrator, designed and manufactured within the scope of HYPROB-NEW Italian Project. In particular, numerical results considering the nominal operating conditions and the influence of variables, such as the inlet temperature and pressure values of refrigerant as well as mass-flow rate, are shown to discuss the fluid transcritical behavior inside the cooling channels and give indications on the numerical methodologies, supporting the design of liquid-oxygen/liquid-methane rocket-engine cooling systems. Validation has been accomplished by means of experimental results obtained through a specific test article, provided with a cooling channel, characterized by dimensions representative of HYPROB DEMO-0A regenerative combustion chamber.

5 citations

Journal ArticleDOI
TL;DR: In this paper, the authors manage the HYPROB (HYdrocarbon PROpulsion test Bench) program, supported by the Italian Ministry of University and Research, with the aim of improving...
Abstract: CIRA, the Italian Aerospace Research Center, manages the HYPROB (HYdrocarbon PROpulsion test Bench) Program, supported by the Italian Ministry of University and Research, with the aim of improving ...

3 citations


Cites background from "Numerical Modeling of Regenerative ..."

  • ...such as the coolant (LCH4) enters the cooling system as a liquid and moves in the counter-flow direction with respect to the combustion gases [30], as pointed out by Figure 22....

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References
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Book
01 Jan 1992
TL;DR: From the component design, to the subsystem design to the engine systems design, engine development and flight-vehicle application, this how-to text bridges the gap between basic physical and design principles and actual rocket-engine design as it's done in industry as mentioned in this paper.
Abstract: From the component design, to the subsystem design, to the engine systems design, engine development and flight-vehicle application, this how-to text bridges the gap between basic physical and design principles and actual rocket-engine design as it's done in industry. More than 470 illustrations and tables should make this book a must-read for advanced students and engineers active in all phases of engine systems design, development and application in industry and in government agencies.

450 citations

Journal ArticleDOI
TL;DR: In this paper, the erosion behavior of graphite nozzles in hybrid engines at different operating conditions and compare results with those obtained for solid motors was studied. But the main distinctive feature of hybrid engine operating conditions is a greater concentration of oxygen-containing combustion products than solid motors.
Abstract: Ablative materials are commonly used to protect the nozzle metallic housing and to provide the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because of interaction with hot gas, these materials are chemically eroded during rocket firing, with a resulting nominal performance reduction. The objective of the present work is to study the erosion behavior of graphite nozzles in hybrid engines at different operating conditions and compare results with those obtained for solid motors. A main distinctive feature of hybrid engine operating conditions is, in fact, a greater concentration of oxygen-containing combustion products than solid motors. The adopted approach relies on a validated full Navier–Stokes flow solver coupled with a thermochemical ablation model that takes into account heterogeneous chemical reactions at the nozzle surface, rate of diffusion of the species through the boundary layer, ablation species injection in the boundary layer, heat conduction inside the nozzl...

91 citations

Journal ArticleDOI
TL;DR: In this article, the authors compared available Nusselt number correlations with an extensive data set of local heat transfer coefficients to determine the domains of validity for each correlation and found that particular correlations perform better than others for certain regimes of fluid properties, with the accuracy of heat transfer coefficient predictions ranging from 23 to over 100%.
Abstract: Understanding the cooling efficiency of supercritical hydrogen is crucial to the development of high-pressure thrust chambers forregeneratively cooledliquid-oxygen/liquid-hydrogen rocket engines. Available Nusselt number correlations are compared with an extensive data set of local heat transfer coefficients to determine the domains of validity for each correlation. The data set was compiled from previous heated straight-tube experiments with supercritical hydrogen. Results indicate that particular correlations perform better than others for certain regimes of fluid properties, with the accuracy of heat transfer coefficient predictions ranging from 23 to over 100%. Correlation uncertainty due to inherent uncertainties in the equation-of-state and transport properties of supercriticalhydrogenisalsoevaluated.Thepropertydependentuncertaintywasfoundtorangefrom2to10%,and therefore is not the main contributor to the larger errors in the correlation predictions. A number of published correlations for nonhydrogen supercritical fluids are shown to achieve comparable performance with hydrogen.

60 citations

Journal ArticleDOI
TL;DR: In this article, a one-dimensional mathematical model is presented for flows in a rocket engine that has a regenerative cooling system, where the problem involves the flow of a gas in a converging-diverging nozzle, flow of the coolant in channels distributed around the engine, and the heat conduction through a wall between the gas and the cooling fluid.
Abstract: A one-dimensional mathematical model is presented for flows in a rocket engine that has a regenerative cooling system. The problem involves the flow of a gas in a convergingdiverging nozzle, the flow of a coolant in channels distributed around the engine, and the heat conduction through a wall between the gas and the coolant. The numerical model adopted is based on the finite-volume method with a second-order scheme. It was noted that it is important to use variable properties in order to predict the maximum wall temperature in the rocket engine and the drop in pressure of the coolant as it moves along the channels, whereas the thrust of the engine can be calculated with constant properties.

42 citations