Supersonic jet and crossflow interaction: Computational modeling

Hassan, Ez A.; Boles, John A.; Aono, Hikaru; Davis, Douglas; Shyy, Wei

doi:10.1016/j.paerosci.2012.06.002

Cited by 74 publications

(14 citation statements)

References 83 publications

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“…Overall, the experiments conducted by Gruber et al commonly showed superior performance of elliptic injection in terms of mixing, total pressure saving, and lateral spreading, as compared to circular injection with the same effective diameter, at the cost of somewhat (20%) less penetration in the transverse direction [15,21,22]. Other extensive computational efforts using various models for turbulence closure are well reviewed and summarized in [25] for jet and crossflow interactions in the supersonic regime.…”

Section: Introductionmentioning

confidence: 99%

Physical Insight into Fuel-Air Mixing for Upstream-Fuel-Injected Scramjets via Multi-Objective Design Optimization

Ogawa

2015

Journal of Propulsion and Power

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Fuel injection and mixing into air play a crucial role in the operation of hypersonic airbreathing propulsion systems, particularly scramjet engines featuring upstream fuel injection. This study applies an advanced design methodology combining computational fluid dynamics and evolutionary algorithms assisted by surrogate modeling to a multi-objective optimization for fuel injection in a Mach 5.7 crossflow after the initial compression in a scramjet intake operating at Mach 7.6. Optimization is performed for elliptical injector configurations defined by four design parameters (i.e., the injection angle, spanwise spacing, aspect ratio, and radius of the injector), simultaneously aiming to maximize three objectives, that is, fuel/air mixing, total pressure saving, and fuel penetration into the crossflow. Statistical methods based on global sensitivity analysis are employed to assess the optimization results in conjunction with surrogate models to identify key design factors with respect to the three design objectives and additional performance measures. Major effects of the injection angle and aspect ratio have been observed on all considered design criteria. The spanwise spacing has been found to have considerable influence on the total pressure recovery, fuel penetration, and lateral spread when the injection pressure is adjusted to maintain a constant fuel/air equivalence ratio. Low-angle fuel injection through a highly elliptic orifice with wide spanwise spacing demonstrated the most comprehensive advantages in overall aspects. NomenclatureA j = injector area on floor, m 2 A n j = injector area normal to jet, m 2 AR = injector aspect ratio a j = semimajor axis of injector, m c = mass fraction c s = stoichiometric mass fraction c H 2 = hydrogen mass fraction c O 2 = oxygen mass fraction D = effective injector diameter, m f = vector of objective functions H = vertical height of computational domain, m h f = fuel penetration height (normalized) J = jet-to-freestream momentum flux ratio L = streamwise length of computational domain, m k = number of clustering L 0 = distance to upstream end of injector, m _ m = mass flow rate, kg∕s N = size of population pool p = static pressure, Pa p eb = effective backpressure (normalized) p j = jet static pressure (normalized) p 02 = pitot pressure behind normal shock, Pa p 0 = total pressure, Pa r j = effective injector radius, m S i = first-order sensitivity index S T i = total-effect sensitivity index U = freestream velocity, m∕s u = velocity, m∕s W = injector spacing (spanwise domain width), m w f = fuel lateral spread (normalized) X i = input vector for decision variable x i X = input matrices comprising vectors X i x = streamwise coordinate, m x = vector of decision variables Y = input vector for output parameter y y = spanwise coordinate, m z = vertical coordinate, m α j = injection angle, deg Γ= streamwise circulation (normalized) Δp 0 = total pressure loss (normalized) Δt = time step, s Δx = spatial step, m Δμ χ = mesh sensitivity error of parameter χ η m = mixing efficie...

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Section: Introductionmentioning

confidence: 99%

Physical Insight into Fuel-Air Mixing for Upstream-Fuel-Injected Scramjets via Multi-Objective Design Optimization

Ogawa

2015

Journal of Propulsion and Power

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“…It is well known that accurate prediction of flow separation is still challenging for many RANS turbulence models. Previous investigations [18,29] found that there are large gaps between the simulation results and experimental data for the case with high injection pressures when the traditional incompressible RANS turbulence models are used. In the present study, the k À ε turbulence model with compressibility modification is applied and briefly discussed.…”

Section: The Governing Equationsmentioning

confidence: 99%

Effects of self-throttling on combustion enhancement in supersonic flow with transverse injection

Han

Chen

2015

International Journal of Hydrogen Energy

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“…Введение. Исследование поперечного вдува струи в сверхзвуковой поток представляет интерес при проектировании систем смешения топлива и окислителя в прямоточных воздушно-реактивных двигателях, в которых используется сверхзвуковое горение [1]. Вдув струи в сверхзвуковой поток применяется также в системах управления вектором тяги ракетных твердотопливных двигателей [2].…”

Section: Doi: 1015372/pmtf20150505unclassified

“…Обзор различных подходов к моделированию турбулентности, таких как моделирование крупных вихрей (large eddy simulation (LES)), моделирование свободных вихрей (detached eddy simulation (DES)) и комбинированные подходы (LES/RANS), приведен в работе [1]. Результаты физических экспериментов, проведенных в широких диапазонах значений чисел Маха и Рейнольдса (M ∞ = 2 ÷ 13, Re = 7,5 • 10 6 ÷ 5,5 • 10 8 ), а также значений отношения давлений в струе вдуваемого газа и основном сверхзвуковом потоке, представлены в работах [18,19].…”

Section: Doi: 1015372/pmtf20150505unclassified

Numerical Simulation of the Interaction of a Transverse Jet With Supersonic Flow Using Different Turbulence Models

2015

PMTF

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Supersonic jet and crossflow interaction: Computational modeling

Cited by 74 publications

References 83 publications

Physical Insight into Fuel-Air Mixing for Upstream-Fuel-Injected Scramjets via Multi-Objective Design Optimization

Physical Insight into Fuel-Air Mixing for Upstream-Fuel-Injected Scramjets via Multi-Objective Design Optimization

Effects of self-throttling on combustion enhancement in supersonic flow with transverse injection

Numerical Simulation of the Interaction of a Transverse Jet With Supersonic Flow Using Different Turbulence Models

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