Thermomechanical Analysis and Optimization of Cryogenic Liquid Rocket Engines

Kuhl, Detlef; Riccius, Jörg; Haidn, Oskar

doi:10.2514/2.6007

Cited by 30 publications

(18 citation statements)

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“…For comparison reasons, we also perform simulations based on a fully coupled iterative staggered partitioned TSI algorithm based on an isothermal split. This partitioned TSI algorithm has been predominantly used in the literature for such problems so far; see for example [1,[7][8][9][10][11]. Furthermore, relaxation in form of an Aitken 2 method, as proposed in [26,27], can be considered for the partitioned TSI algorithm.…”

Section: Numerical Examplesmentioning

confidence: 99%

“…Elevated temperatures (combustion temperature up to 3600 K) with high temperature gradients (coolant fluid inlet temperature approximately 73 K), high wall heat fluxes (of about 120 MW/m 2 ), very thin structures, high Mach and Reynolds numbers, and complex shockboundary-layer interactions have to be considered in the target system of such a rocket nozzle (see e.g. [1,2]). Further challenges are the consequences of flow separation in rocket nozzles that can result in so-called side loads.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Numerical Examplesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A monolithic computational approach to thermo‐structure interaction

Danowski

Gravemeier

Yoshihara

et al. 2013

Numerical Meth Engineering

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“…The interaction with the hot gas side is neglected, whereas the experimental data of [12] serve as boundary condition. This simplified model is extended by a thermomechanical coupling strategy in [13]. Riccius argues in [7] about the relevance of a correct transient load cycle, whereas a 1D fluid model for the hot gas and cooling side is deployed for quasistatic and transient thermal analyses.…”

Section: Introductionmentioning

confidence: 99%

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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“…To determine these heat fluxes from the chamber through the wall into the cooling fluid of up to 85 MW/m 2 in Ariane 5's Vulcain main engine nozzle [1] numerical tools are necessary. Therefore a code is required which does not only simulate the flow regime with its physical problems but solves the heat conduction in the wall and the heat transfer into the cooling fluid.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Heat Loads in a Cryogenic H₂/O₂ Rocket Combustion Chamber

Haarmann

Koschel

2003

Proc Appl Math and Mech

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A Finite Element solver for a coupled simulation of fluid and structure in an axisymmetric domain is presented. The method employs an explicit solution of the flow and structure variables. The computational domain of the fluid is discretised by unstructured triangles and rectangles while the sturcture domain is discretised by unstructured triangles only. For the purpose of code validation the solution of in total three test cases are shown. One test case deals with the structure only while the other two simulate heat transfer problems with a defined temperature distribution along a boundary wall and coupled conditions. Finally the code is used to simulate the heat load in a cryogenic H2/O2 rocket combustion chamber.

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Thermomechanical Analysis and Optimization of Cryogenic Liquid Rocket Engines

Cited by 30 publications

References 3 publications

A monolithic computational approach to thermo‐structure interaction

A monolithic computational approach to thermo‐structure interaction

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

Numerical Simulation of Heat Loads in a Cryogenic H₂/O₂ Rocket Combustion Chamber

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Thermomechanical Analysis and Optimization of Cryogenic Liquid Rocket Engines

Cited by 30 publications

References 3 publications

A monolithic computational approach to thermo‐structure interaction

A monolithic computational approach to thermo‐structure interaction

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

Numerical Simulation of Heat Loads in a Cryogenic H2/O2 Rocket Combustion Chamber

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Numerical Simulation of Heat Loads in a Cryogenic H₂/O₂ Rocket Combustion Chamber