Progress in Combustion and Heat Transfer Modelling in Rocket Thrust Chamber Applied Engineering

Knab, O.; Frey, Manuel; Görgen, J.; Maeding, C.; Quering, Katharina; Wiedmann, D.

doi:10.2514/6.2009-5477

Cited by 28 publications

(27 citation statements)

References 4 publications

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“…Replacing equations (9) and (10) in equation (8) finally leads to equation (11). (11) Pr is the Prandtl number, is viscosity, P C is specific heat at constant volume and A is cross section of flow( R is a constant parameter of gas combustion products, is an isentropic exponent, g M is molecular weight and 0 T is combustion temperature (T-core).…”

Section: Rapid Heat Transfer Modelingmentioning

confidence: 99%

“…Coolant is injected through orifices near the injector or near the throat with special slots. This method has been widely used, in particular, for high heat fluxes [8]- [10].Sample engines were film cooling is applied are the SSME, Vulcain2, RD-171and RD-180.Combinations of mentioned methods are nowadays used [11] to increase the thermal performances. Combination of regenerative and film cooling is more interesting because of good performance without activity limitation.…”

Section: Introductionmentioning

confidence: 99%

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

Adami¹,

Mortazavi²,

Nosratollahi³

2015

JFFHMT

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Section: Rapid Heat Transfer Modelingmentioning

confidence: 99%

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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“…takes place due the use of shared parameters in diff erent disciplines (Adami 2015;Darabi et al 2015). Analytical and computational tools were developed for over-cooled walls (Knab et al 2009) but known computational and analytical methods are usually involved in CFD and longtime consumption. Such accuracy and time consumption are not needed for conceptual and preliminary design phase.…”

Section: Heat Transfer Disciplinesmentioning

confidence: 99%

A New Approach to Multidisciplinary Design Optimization of Solid Propulsion System Including Heat Transfer and Ablative Cooling

Adami

Mortazavi

Nosratollahi

2017

J.Aerosp. Technol. Manag.

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AbstrAct:The optimum design of a solid propulsion system consists of optimization of various disciplines including structure, aerothermodynamics, heat transfer, and grain geometry. In this paper, an efficient model of every discipline has been developed, and a suitable framework is introduced for these hard-coupled disciplines. Hybrid optimization algorithm is used to find the global optimum point including genetic algorithm and sequential quadratic programing. To show the performance of the proposed algorithm, the required correction factor values have been carefully derived using comparison between more than 10 real solid propulsion systems and the proposed algorithm results. According to the results, the derived correction factors are close to 1, with scattering level better than 0.97. In addition, it is shown that the proposed algorithm (errors < 8%) is more accurate in comparison with the conventional approach (errors < 17%). Then, for a case study, multidisciplinary analysis has been done based on 3 general objectives including dry mass, total mass, and specific impulse. It means that the optimum specific impulse is not the maximum value and the optimum dry mass is not the minimum value. Finally, the proposed algorithm can be used to directly derive the optimum configuration for every mission requirement.

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“…The cooling channel §ow is included by a one-dimensional (1D) approach. Current simulation strategies were presented by Knab et al in [5], where a coupled heat transfer simulation was performed between the hot gas side and the coolant §ow. The hot gas side is modeled by an axisymmetric multiphase NavierStokes solver, whereas the cooling channel §ow and the structure are analyzed by a 3D conjugate heat transfer model.…”

Section: Introductionmentioning

confidence: 99%

Fluid-structure interaction analysis applied to thermal barrier coated cooled rocket thrust chambers with subsequent local investigation of delamination phenomena

Kowollik

Horst

Haupt

2013

Progress in Propulsion Physics

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The aim of this work is to investigate numerically thermal barrier coating (TBC) systems applied to realistic rocket thrust chamber conditions. A global full parametric three-dimensional (3D) modeling approach for cooled rocket thrust chambers is presented to be able to simulate the §uidstructure interaction (FSI) phenomena involved. In a subsequent analysis step, realistic mechanical and thermal boundary conditions are extracted from critical design regions of the global model and applied to a local ¦nite element model (FEM) to analyze possible TBC delaminations by means of a Fracture Mechanics (FM) approach.

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Progress in Combustion and Heat Transfer Modelling in Rocket Thrust Chamber Applied Engineering

Cited by 28 publications

References 4 publications

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

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

A New Approach to Multidisciplinary Design Optimization of Solid Propulsion System Including Heat Transfer and Ablative Cooling

Fluid-structure interaction analysis applied to thermal barrier coated cooled rocket thrust chambers with subsequent local investigation of delamination phenomena

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