Modelling combustor performance of a ducted rocket

Stowe, Robert; Champlain, Alain De; Mayer, Alfons

doi:10.2514/6.2000-3728

Cited by 7 publications

(5 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…7 Radial profiles of temperature at different combustor sections, with radiation (continuous line) and without radiation (dashed line) cent. These low values of the performance agree with the experimental values obtained in the tests performed at TNO [43,44] in combustors of similar length (0.453 m), simple injectors, similar operating conditions, and with fuels whose C(s) fraction was 24 per cent, although the mean size of carbon particles was about three times greater, that is 10 mm.…”

Section: Radiation Effectssupporting

confidence: 86%

“…The numerical simulation of this process is of great interest because it would produce quantitative results at a reduced cost when compared with employing experimental methods. There are several works that apply numerical simulation to the processes of mixing and combustion assuming that the primary flow does not contain particles [34][35][36][37][38][39][40][41][42][43]. Some of them show that the description of the flow without combustion, using k21 turbulence models, is satisfactory in comparison with experimental results.…”

Section: Introductionmentioning

confidence: 99%

“…Thus, for example, Ristori and Dufour [42] after carrying out a critical analysis of diverse models conclude that the model 'EBU þ Arrhenius' provides good results in comparison with experimental results, (efficiency prediction is within 7 per cent error and total pressure losses within 5 per cent). Stowe et al [43], by using a PDF model for the mixture fraction and local thermochemical equilibrium, obtained performance predictions that overestimate the TNO experimental results by up to 27 per cent. They conclude that these differences are mainly due to the high carbon particle content in the primary flow (molar fraction 30 per cent).…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical analysis of heterogeneous combustion in a ducted rocket

Salvá

Tizón

Jenaro³

et al. 2007

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

A model to analyse the heterogeneous combustion process that takes place in an axisymmetric combustor of an air ducted rocket is presented, including radiation. The fuel, injected into the combustor through a simple injector, is a mixture of gaseous products, carbon particles, and MgO inert particles that results from the combustion of a solid fuel (HTPB-AP-Mg). The turbulence model used is the realizable k—π model. The adopted reaction model is a reduced kinetic scheme composed of five reactions, three in gaseous phase and two heterogeneous. The model ‘finite rate/eddy dissipation model of Magnussen and Hjertager’ is used to calculate the production terms in the gas phase, meanwhile the mixed model of Field, Baum, and Street is used for the oxidation reaction of carbon particles. After a detailed analysis of the numerical results, obtained with a commercial code for a specific combustor geometry and one set of boundary conditions both for the gaseous and solid phases, the existence of a special combustion pattern is found. It is composed of a turbulent diffusion jet flame attached to the injector, where only the gaseous fuel is burned, followed by a reaction region that envelops the jet of carbon particles at the aft of the combustion chamber. This jet of carbon particles oxidizes at a finite rate producing CO and CO2. The emission of CO and C(s) from the combustor is the main cause of high efficiency reduction. Radiation has little effect on calculated global variables, such as efficiency, mass flowrate, and total pressure loss, but on the contrary its effects on the temperature fields became important. Chilling of the gas phase was observed together with a reduction of solid particle temperature, however wall combustor temperature increased greatly. Simulation results are interpreted in the light of experimental observations and available numerical solutions in the literature.

show abstract

Section: Radiation Effectssupporting

confidence: 86%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical analysis of heterogeneous combustion in a ducted rocket

Salvá

Tizón

Jenaro³

et al. 2007

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Using model engine with similar structure, the American NAWC and European TNO-PML [2] studied factors affecting combustion characteristic, such as patterns of fuel injection, air-fuel momentum ratio, jetting angle and dome height. Lately, Mayer and Stowe [3][4][5] cooperated on the study of solid rocket ramjet. Their work covered numerical simulation, direct-connected test and current test, and analyzed impact on combustion efficiency of air-fuel ratio, air-fuel momentum ratio, dome height, gas generator and injecting angle, etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation on Two Phase Combustion Characteristic in Solid Rocket Ramjet Afterburning Chamber

Zhang

Zeng

et al. 2013

AMR

View full text Add to dashboard Cite

Numerical simulation on two-phase combustion characteristic in afterburning chamber of solid rocket ramjet was carried out by applying particle trajectory model. It was analyzed that the nozzle number of secondary combustion chamber, inlet angle of air and particles diameter impact on efficiency of combustion. Results show that the combustion efficiency in the afterburning chamber is highest, achieving 99.6% when the angle between both air inlets is 180°, particle diameter is 15μm, and 5-hole nozzle is used. By contrary, when the angle between both air inlets is 90°, particle diameter is 5μm, and 5-hole nozzle is used, the afterburning chamber has a lowest combustion efficiency of 70.3%.

show abstract

“…Before the numerical tools are used in the design exercise, it is necessary to assess their predictive capabilities to simulate such flow field by taking appropriate validation test cases. Although, separate CFD simulations are carried out for intake 11,12 and combustor 13,14 for variable flow ducted rocket engines, a combined external and internal flow analysis are very rare in the open literature. In fact, the aerodynamic and propulsive elements for any high speed air breathing system are so tightly coupled that proper estimation of aerodynamic characteristics can only be carried out through combined external-internal flow simulations.…”

Section: Aerodynamic Characterisation Of Ramjet Missile Through Combinedmentioning

confidence: 99%

Aerodynamic Characterisation of Ramjet Missile through Combined External-internal Computational Fluid Dynamics Simulation

et al. 2016

View full text Add to dashboard Cite

Combined external-internal flow simulation is required for the estimation of aerodynamic forces and moments of high speed air-breathing vehicle design. A wingless, X-tail configuration with asymmetrically placed rectangular air intake is numerically explored for which experimental data is available for different angles of attack. The asymmetrically placed air intakes and protrusions make the flow field highly three-dimensional and existing empirical relations are inadequate for preliminary design. Three dimensional Navier Stokes equations along with SST-kω turbulence model were solved with a commercial CFD solver to analyse the combined external and internal flow field of the configuration at different angles of attack. Estimated aerodynamic coefficients match well with experimental data and estimated drag coefficient are within 8.5 per cent of experimental data. Intake performance parameters were also evaluated for different angles of attack.Keyword: Ramjet, computational fluid dynamics, CFD, drag coefficient, pressure recovery, mass capture ratio

show abstract

Modelling combustor performance of a ducted rocket

Cited by 7 publications

References 2 publications

Numerical analysis of heterogeneous combustion in a ducted rocket

Numerical analysis of heterogeneous combustion in a ducted rocket

Numerical Simulation on Two Phase Combustion Characteristic in Solid Rocket Ramjet Afterburning Chamber

Aerodynamic Characterisation of Ramjet Missile through Combined External-internal Computational Fluid Dynamics Simulation

Contact Info

Product

Resources

About