Stationary and Transient Thermal Analyses of Cryogenic Liquid Rocket Combustion Chamber Walls

Riccius, Jörg; Zametaev, Evgeny B.

doi:10.2514/6.2002-3694

Cited by 11 publications

(15 citation statements)

References 2 publications

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“…The hot gas temperature is T hg = 3435 K and the maximum calculated hot gas wall temperature is about 950 K. In order to avoid damage concentration at the outer cooling channels additional water cooling is applied. The applied material parameters for the material model were identified based on [1,6]. The damage distribution of the testing sample after 20 cycles (cf.…”

Section: Numerical Resultsmentioning

confidence: 99%

Lifetime prediction of a rocket combustion chamber wall by a viscoplastic damage model

Fassin

Tini

Vladimirov

et al. 2014

Proc Appl Math and Mech

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Regeneratively cooled nozzle structures of Reusable Launch Vehicles (RLV) belong to the most critical components of a space shuttle main engine. The so-called doghouse effect is a failure mode in the rocket combustion chamber wall, which has been observed experimentally. Within the Collaborative Research Centre SFB-TR 40 of the German Research Foundation (DFG), new technologies for the future space-transport-systems are being developed. By using a new continuum mechanical approach, motivated by a rheological model, we are able to reproduce the doghouse effect. Moreover we intend to give reliable lifetime predictions for rocket combustion chamber structures so that in future components can be tested virtually instead of conducting real experiments.

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Section: Numerical Resultsmentioning

confidence: 99%

Lifetime prediction of a rocket combustion chamber wall by a viscoplastic damage model

Fassin

Tini

Vladimirov

et al. 2014

Proc Appl Math and Mech

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“…The yield stress σ y and the Young's modulus of elasticity E 1 for generic copper and nickel alloys is adopted from . Suggestions for the kinematic hardening parameters E 2 and b are found in .…”

Section: Materials Modelingmentioning

confidence: 99%

“…For the thermomechanical analysis to be discussed in Section 3.4, the parameters of the material model introduced in the previous section have to be determined. The yield stress y and the Young's modulus of elasticity E 1 for generic copper and nickel alloys is adopted from [6]. Suggestions for the kinematic hardening parameters E 2 and b are found in [10].…”

Section: Materials Parametersmentioning

confidence: 99%

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3D fluid–structure interaction analysis of a typical liquid rocket engine cycle based on a novel viscoplastic damage model

Kowollik

Tini

Reese

et al. 2013

Numerical Meth Engineering

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SUMMARYIn many space missions, expandable or reusable launch systems are used. In this context, the reliable design of liquid rocket engines (LREs) is a key issue. In the present paper, we present a novel combination of numerical schemes. It is applied to model the extreme physical phenomena a typical LRE undergoes during its loading cycles. The numerical scheme includes a partitioned fluid–structure interaction (FSI) algorithm in combination with a unified viscoplastic damage model. This allows the complex description of the material response under cyclic thermomechanical loading taking place in LREs. In this regard, we focus on the response of the cooling channel wall that is made from copper alloys. For the coupled FSI analysis, the individual domains of the rocket thrust chamber are modeled by a 3D parametrized approach. The well‐established single field solver codes, DLR TAU for the hot gas and ABAQUS FE software for the structural domain, are coupled via the inhouse developed simulation environment ifls. Ifls provides the necessary algorithms for a partitioned coupling approach such as individual code steering, data interpolation, time integration and iteration control. Finally, the results of an FSI analysis of a complete engine cycle are presented. They show the potential of the new numerical scheme for the lifetime prediction of LREs.Copyright © 2013 John Wiley & Sons, Ltd.

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“…However, few studies have been published on the transient variations and the distribution in the nozzle segment of the heat flux. More precise life prediction of the thrust chamber can be achieved with the transient heat flux (Riccius and Zametaev, 2002). Furthermore, because the maximum heat flux locates in the region close to the nozzle throat, obtaining the heat loads in the nozzle section is crucial for the design of thermal protection systems.…”

Section: Introductionmentioning

confidence: 99%

Wall heat flux measurements in a GO<sub>2</sub>/GH<sub>2</sub> heat-sink combustion chamber

Wang

Sun

Xiang

et al. 2018

JTST

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In order to understand heat transfer mechanisms in the combustion chamber with multi-elements injector and provide benchmark data of wall heat fluxes for the CFD code validation, experiments were carried out in a GH2/GO2 heat-sink combustion chamber. To obtain the transient heat flux in the experiments, the LevenbergMarquardt method was modified and applied to the rocket combustion chamber based on the temperature measured by single coaxial thermocouple (Named "single-point method"). The comparison between the singlepoint method and the two-point method with temperatures measured in two points shows that the single-point method could be used as heat flux measurements of the heat-sink combustion chamber in engineering. Heat flux distribution was obtained in experimental conditions of different work time and chamber pressure by the modified method, feasibly and efficiently. For the transient variations of the heat flux, an inverse variation trend of heat flux to time in the cylindrical segment and the nozzle segment was observed. A typical variation of the averaged heat flux was obtained under the conditions with different chamber pressure and work time. The results of wall heat flux scaled with pressure to the power 0.8 can be uniformized for all pressure levels. The heat fluxes obtained in the cylindrical chamber and nozzle section may be applied for the life cycle prediction of rocket engines.

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Stationary and Transient Thermal Analyses of Cryogenic Liquid Rocket Combustion Chamber Walls

Cited by 11 publications

References 2 publications

Lifetime prediction of a rocket combustion chamber wall by a viscoplastic damage model

Lifetime prediction of a rocket combustion chamber wall by a viscoplastic damage model

3D fluid–structure interaction analysis of a typical liquid rocket engine cycle based on a novel viscoplastic damage model

Wall heat flux measurements in a GO<sub>2</sub>/GH<sub>2</sub> heat-sink combustion chamber

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