Comprehensive modeling of a liquid rocket combustion chamber

Liang, P. Y.; Fisher, Scott; Chang, Y. M.

doi:10.2514/6.1985-232

Cited by 6 publications

(3 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Liang et al 6 sought to improve the effects of multi-phase modeling that included liquid, gas, and liquid droplets. A 2-D axisymmetric model was used along with a chemical model consisting of a 9-equation kinetic model along with 4 equilibrium equations.…”

Section: Review Of Select Cfd Modeling and Validation Studiesmentioning

confidence: 99%

“…For this reason, researchers have begun to employ CFD techniques to aid in injector design. For example, Liang et al 6 developed semi-empirical calculations to aid in the computer modeling of liquid rocket combustion chambers. Sindir and Lynch 7 simulated a single element GO 2 /GH 2 injector using an 8-species, 18 reaction chemical kinetics model with the k-ε turbulence model and compared the velocity profile to experimental measurements with good results.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow

Mack¹,

Haftka²,

Segal³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

A three-dimensional computational model of an experimental rectangular combustion chamber was developed to explore the wall heat transfer of a GO 2 /GH 2 shear coaxial single element injector. The CFD model allowed for the direct analysis of heat transfer effects due to flow dynamics-an analysis that would be very difficult using experimental studies alone. The use of a 3-D CFD model revealed heat transfer effects due to flow streamlines and eddy conductivity, and provided insight into the two-dimensional nature of the wall heat flux. A grid sensitivity study was conducted to determine the effects of grid resolution on the combustion chamber length and heat flux. The results of a grid sensitivity study were inconclusive, as a grid-independent solution could not be reached. However, it was found that the predicted heat flux was largely independent of the grid resolution, as long as the near-wall region was well resolved. Finally, a single-element injector model was constructed to explore the sensitivity of the peak heat flux and combustion chamber length to the circumferential and radial spacing of injector elements in the outer row of a multi-element injector. Many cases, including the baseline case, had a recirculation region that was oriented such that the outer shear layer was directed at the combustion chamber wall, resulting in a large peak heat flux near the injector face. It was found that by increasing the spacing between injector elements of the outer row while reducing the distance of the outer row to the wall, a relatively flat heat flux profile could be obtained.

show abstract

Section: Review Of Select Cfd Modeling and Validation Studiesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow

Mack¹,

Haftka²,

Segal³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

show abstract

“…a pump or a controller, or a phenomenon such as combustion instability. For example, general relations for simulations of the combustion chambers are given by Liang and Mason (1986), Habiballah et al (1991), Jiang and Chiu (1992), Wang (1993), Khosravi and Mazaheri (2000) and Ivancic and Mayer (2002). Analysis of LPRE turbomachinery is covered by McDaniel and Snellgrove (1992) and Chen (1995).…”

Section: Introductionmentioning

confidence: 99%

Modeling and simulation of a two combustion chambers liquid propellant engine

Karimi

Mohammadi²

2007

Aircraft Engineering and Aerospace Technology

View full text Add to dashboard Cite

PurposeThe purpose is to develop and apply a systematic simulation approach for dynamic analysis in order to study a two combustion chambers liquid propellant engine.Design/methodology/approachThe logic of the simulation method and the software is based on following the liquids. The implicit nonlinear algebraic equations are solved using a number of nested Newton‐Raphson loops, and the nonlinear and time varying differential equations are solved using a first‐order Euler technique.FindingsIt is found that the developed simulation code predicts the steady‐state values with errors under 5 percent, and this code has the capability to be used in studying the effect of various elements and subsystems parameters on the forecasting the performance and operation of the engine system.Research limitations/implicationsAt present, the research is limited to a specific liquid propellant engine. Development of a general purpose software package for simulation of liquid propellant engines, based on the developed simulation algorithm, is subject of future research.Practical implicationsThe major outcome of this research is that verifies liquid engine simulation code may be used as a suitable tool to optimize the engine.Originality/valueThis is the first paper in the area of a two combustion chambers engine simulation and dynamic analysis that is based on the application of an existing simulation algorithm.

show abstract

Upwind adaptive finite element investigations of the two‐dimensional reactive interaction of supersonic gaseous jets

Chargy

Dervieux

Larrouturou

1990

Numerical Methods in Fluids

View full text Add to dashboard Cite

SUMMARYWe describe an upwind finite element method aimed at numerically simulating the two-dimensional transonic flow of a reactive gaseous mixture. The method uses in particular a triangular finite element mesh, with an adaptive procedure based on mesh refinement by triangle division, and a n upwind non-oscillatory scheme based on a n approximate Riemann solver for the evaluation of the convective terms for all species. Results concerning the reactive interaction of two supersonic gaseous jets are presented.

show abstract

Comprehensive modeling of a liquid rocket combustion chamber

Cited by 6 publications

References 3 publications

Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow

Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow

Modeling and simulation of a two combustion chambers liquid propellant engine

Upwind adaptive finite element investigations of the two‐dimensional reactive interaction of supersonic gaseous jets

Contact Info

Product

Resources

About