Influence of curvature in regenerative cooling system of rocket engine

Torres, Yezid; Stefanini, L.; Suslov, Dmitry

doi:10.1051/eucass/200901171

Cited by 8 publications

(3 citation statements)

References 11 publications

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“…Regenerative cooling is the most widely used method of cooling a high performance combustion chamber and is accomplished by flowing high velocity coolant over the backside of the chamber hot gas wall to convectively cool the hot gas liner [5,6]. The coolant, heated up by the hot liner, is then discharged into the injector and used as a propellant.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary approach to materials selection for bipropellant thrusters using ablative and radiative cooling

Adami

Mortazavi

Nosratollahi

2016

Sadhana

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Reduction of costs is a main consideration in every space mission, and propulsion system is an important subsystem of those missions where orbital maneuvers are considered. Lighter propulsions with higher performance are necessary to reduce the mission costs. Bipropellant propulsions have been widely used in launch vehicles and upper-stages as well as deorbit modules because of better performances in comparison with other propulsion systems. Unfortunately heat transfer and thermal control limit bipropellant propulsion performance and maximum performance cannot be achieved. Well-known cooling methods such as regenerative and film cooling increase the cost using extra equipment and high temperature materials. In this paper, a new approach for cooling is presented based on combined ablative and radiative cooling. Governing equations are derived for two or three layers of thermal protection system (TPS) to optimize the TPS mass. The first layer is used as an ablative layer to control the temperature where the second and third layers are used as an insulator to control the heat fluxes. Proposed cooling method has been applied for two real bipropellant thrusters. According to the results, the presented algorithm can suitably predict the heat fluxes and satisfy the wall temperature constraint. Then, the algorithm has been used to minimize the wall temperatures as low as possible and replace high temperature materials (platinum alloy) with common materials (composite or steel). It is shown that selection of TPS materials affects the TPS mass and Isp simultaneously, but conversely. Best solution should be derived by trading off between structure temperature (cost), Isp (performance), and TPS thicknesses (geometry). Multidisciplinary approach to TPS and structure material selection of a bipropellant thruster is presented for a case study. It has been shown that mass and performance penalties of using TPS are acceptable, considering the advantages of using steel alloy instead of platinum alloy.

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Section: Introductionmentioning

confidence: 99%

Multidisciplinary approach to materials selection for bipropellant thrusters using ablative and radiative cooling

Adami

Mortazavi

Nosratollahi

2016

Sadhana

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“…It is accomplished by flowing high velocity coolant over the backside of the chamber hot gas wall to convectively cool the wall [5], [6]. The coolant, heated up by the hot liner, is then discharged into the injector and used as a propellant.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer Modeling of Bipropellant Thrusters for using in Multidisciplinary Design Optimization Algorithm

Adami¹,

Mortazavi²,

Nosratollahi³

2015

JFFHMT

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“…This is a relevant approximation, as the wall temperature is unknown a priori because it is the result of the balance among hot-gas convection, wall conduction, and coolant convection. This limitation can be overcome by adopting conjugate heat transfer models to study the coupled threedimensional coolant flow and heat conduction within the wall [13][14][15][16][17]. As for supercritical methane flow in cooling channels, numerical studies have been presented for both circular-cross-section tubes [18][19][20][21][22] and rectangular-cross-section cooling channels [23][24][25][26], but none of them has been compared with experimental data.…”

mentioning

confidence: 99%

Validation of Conjugate Heat Transfer Model for Rocket Cooling with Supercritical Methane

Pizzarelli¹,

Nasuti²,

Votta³

et al. 2016

Journal of Propulsion and Power

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A numerical solver able to describe a rocket engine cooling channel fed with supercritical methane is validated against experimental data coming from a test article conceived and tested by the Italian Aerospace Research Center. The multidimensional conjugate heat transfer model numerically solves the Reynolds-averaged Navier-Stokes equations for the coolant flow and the Fourier's law of conduction for the heat transfer within the wall. In this study, an experimental test case is reproduced in detail in order to evaluate the influence of partially unknown parameters, such as surface roughness and wall thermal conductivity, and of operative parameter uncertainty, such as the coolant mass flow rate and input heat transfer rate. The comparison made with respect to the wall temperature and coolant pressure drop of the whole set of experimental data provides complementary information that allows better understanding of experiments and infers possible deviations from the expected behavior.= mass flow rate p = pressure Q = heat transfer rate q = heat flux s w = internal wall thickness T = temperature t w = rib thickness x, y, z = axial, horizontal, and vertical coordinates Subscripts cr = critical e = exit i = inlet w = wall

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Influence of curvature in regenerative cooling system of rocket engine

Cited by 8 publications

References 11 publications

Multidisciplinary approach to materials selection for bipropellant thrusters using ablative and radiative cooling

Multidisciplinary approach to materials selection for bipropellant thrusters using ablative and radiative cooling

Heat Transfer Modeling of Bipropellant Thrusters for using in Multidisciplinary Design Optimization Algorithm

Validation of Conjugate Heat Transfer Model for Rocket Cooling with Supercritical Methane

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