One- and Three-Dimensional Wall Heat Flux Calculations in a O2/H2 System

Vaidyanathan, Aravind; Gustavsson, Jonas; Segal, Corin

doi:10.2514/1.44640

Cited by 7 publications

(2 citation statements)

References 9 publications

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“…Inverse heat transfer methods have been successfully applied for the heat flux estimation in capacitively cooled engines where the temperature field is not stationary during the test operation and hence a transient inverse heat conduction method is needed [4,19,27]. The main concept behind an inverse method for heat conduction problems lies in trying to estimate the boundary conditions (causes) which best fit the measured temperature values (effects) while keeping the physics of the problem intact.…”

Section: Inverse Heat Transfer Methodsmentioning

confidence: 99%

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Perakis

Haidn

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The experimental investigation of sub-scale rocket engines gives significant information about the combustion dynamics and wall heat transfer phenomena occurring in full-scale hardware. At the same time, the performed experiments serve as validation test cases for numerical CFD models and for that reason it is vital to obtain accurate experimental data. In the present work, an inverse method is developed able to accurately predict the axial and circumferential heat flux distribution in CH$$_4$$/O$$_2$$ rocket combustors. The obtained profiles are used to deduce information about the injector-injector and injector-flame interactions. Using a 3D CFD simulation of the combustion and heat transfer within a multi-element thrust chamber, the physical phenomena behind the measured heat flux profiles can be inferred. A very good qualitative and quantitative agreement between the experimental measurements and the numerical simulations is achieved.

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Section: Inverse Heat Transfer Methodsmentioning

confidence: 99%

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Perakis

Haidn

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…Among this research, many advanced techniques, such as the optical measurement and the large eddy simulation (LES), are widely used. [5][6][7][8][9][10][11][12] In order to explore the approach to the optimal design of the injector, Shyy et al [13] used different optimization methods to study the gas-gas injector. In their work, the propellant mixture ratio, the velocity ratio of fuel to oxidizer, and the combustor length (the length from the injector to the throat) were selected as the design parameters; the optimal energy release efficiency, and the heat flux were selected as the objectives.…”

Section: Introductionmentioning

confidence: 99%

Numerical and experimental study on shear coaxial injectors with hot hydrogen-rich gas/oxygen-rich gas and GH₂/GO₂

Jin¹,

Li²,

Cai³

2013

Chinese Phys. B

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The influences of the shear coaxial injector parameters on the combustion performance and the heat load of a combustor are studied numerically and experimentally. The injector parameters, including the ratio of the oxidizer pressure drop to the combustor pressure (DP), the velocity ratio of fuel to oxidizer (RV), the thickness (WO), and the recess (HO) of the oxidizer injector post tip, the temperature of the hydrogen-rich gas (TH) and the oxygen-rich gas (TO), are integrated by the orthogonal experimental design method to investigate the performance of the shear coaxial injector. The gaseous hydrogen/oxygen at ambient temperature (GH2/GO2), and the hot hydrogen-rich gas/oxygen-rich gas are used here. The length of the combustion (LC), the average temperatures of the combustor wall (TW), and the faceplate (TF) are selected as the indicators. The tendencies of the influences of injector parameters on the combustion performance and the heat load of the combustor for the GH2/GO2 case are similar to those in the hot propellants case. However, the combustion performance in the hot propellant case is better than that in the GH2/GO2 case, and the heat load of the combustor is also larger than that in the latter case.

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Inverse heat transfer method applied to capacitively cooled rocket thrust chambers

Perakis

Haidn

2019

International Journal of Heat and Mass Transfer

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One- and Three-Dimensional Wall Heat Flux Calculations in a O2/H2 System

Cited by 7 publications

References 9 publications

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Numerical and experimental study on shear coaxial injectors with hot hydrogen-rich gas/oxygen-rich gas and GH₂/GO₂

Inverse heat transfer method applied to capacitively cooled rocket thrust chambers

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One- and Three-Dimensional Wall Heat Flux Calculations in a O2/H2 System

Cited by 7 publications

References 9 publications

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Numerical and experimental study on shear coaxial injectors with hot hydrogen-rich gas/oxygen-rich gas and GH2/GO2

Inverse heat transfer method applied to capacitively cooled rocket thrust chambers

Contact Info

Product

Resources

About

Numerical and experimental study on shear coaxial injectors with hot hydrogen-rich gas/oxygen-rich gas and GH₂/GO₂