Viscoplastic analysis of an experimental cylindrical thrust chamber liner

Arya, Vinod K.; Arnold, Steven M.

doi:10.2514/3.10985

Cited by 34 publications

(18 citation statements)

References 2 publications

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“…It was concluded that qualitative agreement with [6] could be reached; a quantitative assessment was, however, not presented. If the predicted deformations of [1,12] are compared with micrographs of failed channels given in [5,6] it becomes apparent that the models significantly underestimate the amount of cumulative deformation of the hot wall ligament, so a quantitative agreement cannot be ascertained.…”

Section: Introductionmentioning

confidence: 97%

“…The initially square-shaped cooling channels of the combustion liner, see Fig. 1, distort to a roof like geometry, commonly referred to as doghouse [1] and the creep-fatigued material starts to fail by crack formation in the hot wall ligament.…”

Section: Introductionmentioning

confidence: 99%

“…As reference, a main stage thrust chamber is chosen that underwent a series of firing tests and was available for destructive metallographic analyses. The simulation methodology applied here is adapted from the work of Armstrong [9] and carried further on in the following aspects: (1) In all aforementioned theoretical works on this topic [1,9,12] and also in more recent contributions [13,14] the choice of the material model was not justified by phenomenological investigations of the behaviour of the applied alloy. In the present work a series of dedicated experiments on specimen level are performed to conclude which material behaviour phenomena are required to be taken into account.…”

Section: Introductionmentioning

confidence: 99%

“…In the present work a series of dedicated experiments on specimen level are performed to conclude which material behaviour phenomena are required to be taken into account. (2) Due to the high time consumption, 2D finite elements were applied in [1,9,12]. In [13,14] the hot wall was modelled by a sandwich-beam.…”

Section: Introductionmentioning

confidence: 99%

“…Improved material models, taking into account creep-plasticity interaction and cyclic hardening mechanisms, became available after the works of [10,11]. These were subsequently applied by Arya and co-workers [1,12] to assess the inelastic deformation of an experimental thrust chamber from [6]. The simulation method was adapted from Armstrong [9].…”

Section: Introductionmentioning

confidence: 99%

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Life prediction of thermally highly loaded components: modelling the damage process of a rocket combustion chamber hot wall

Schwarz¹,

Schwub

Quering³

et al. 2011

CEAS Space J

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During their operational life-time, actively cooled liners of cryogenic combustion chambers are known to exhibit a characteristic so-called doghouse deformation, pursued by formation of axial cracks. The present work aims at developing a model that quantitatively accounts for this failure mechanism. High-temperature material behaviour is characterised in a test programme and it is shown that stress relaxation, strain rate dependence, isotropic and kinematic hardening as well as material ageing have to be taken into account in the model formulation. From fracture surface analyses of a thrust chamber it is concluded that the failure mode of the hot wall ligament at the tip of the doghouse is related to ductile rupture. A material model is proposed that captures all stated effects. Basing on the concept of continuum damage mechanics, the model is further extended to incorporate softening effects due to material degradation. The model is assessed on experimental data and quantitative agreement is established for all tests available. A 3D finite element thermo-mechanical analysis is performed on a representative thrust chamber applying the developed material-damage model. The simulation successfully captures the observed accrued thinning of the hot wall and quantitatively reproduces the doghouse deformation.

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Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Life prediction of thermally highly loaded components: modelling the damage process of a rocket combustion chamber hot wall

Schwarz¹,

Schwub

Quering³

et al. 2011

CEAS Space J

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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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A monolithic computational approach to thermo‐structure interaction

Danowski

Gravemeier

Yoshihara

et al. 2013

Numerical Meth Engineering

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In the present work, a monolithic solution approach for thermo-structure interaction problems motivated by the challenging application of the behaviour of rocket nozzles is proposed. Structural and thermal fields are independently discretised via finite elements. The resulting system of equations is solved via a monolithic thermo-structure interaction scheme, which is constructed by a block Gauss-Seidel preconditioner in combination with algebraic multigrid methods. The proposed method is tested for four numerical examples, the second Danilovskaya problem, a simplified rocket nozzle configuration, an internally loaded hollow sphere, and a fully three-dimensional nozzle configuration of a subscale thrust chamber. Good agreement of the numerical results with results from the literature is observed. Furthermore, it is shown that the monolithic solution algorithm can handle the complete range of the parameter spectrum, whereas partitioned algorithms are limited to a certain parameter range only. Moreover, the monolithic algorithm exhibits improved efficiency and robustness compared to partitioned algorithms. describing equilibrium of the forces of inertia, internal and external forces in the structural domain . In this context, , d and R d denote the density, the unknown displacements and accelerations, respectively. O b represents an arbitrary body load. The internal forces are expressed in terms of the stress tensor . For an isotropic thermoelastic solid, the strain-energy function described in the

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Viscoplastic analysis of an experimental cylindrical thrust chamber liner

Cited by 34 publications

References 2 publications

Life prediction of thermally highly loaded components: modelling the damage process of a rocket combustion chamber hot wall

Life prediction of thermally highly loaded components: modelling the damage process of a rocket combustion chamber hot wall

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

A monolithic computational approach to thermo‐structure interaction

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