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50th AIAA Aerospace Science Meeting              Nashville, Tennessee      January 10th, 2012


                                    Acknowledgements
                             Texas Advanced Computing Center




      Large Eddy Simulation based Studies of
     Reacting and Non-reacting Transverse Jets
              in Supersonic Crossflow

                  Shaun Kim a,b       Pratik Donde a Venkat Raman a
                         Kuo-Cheng Lin c      Campbell Carter d

                Department of Aerospace Engineering and Engineering Mechanics
                               The University of Texas at Austin




 a                           b                            c                     d
data have shown that this is not a reali
                                                                   free-stream, plume overexpansion do
     Motivation                                 354
                                                                   Subsequently, Champigny and Lacau
                                                                   supersonic cross-flow. TheirS. K. stru
                                                                                 S. Kawai and flow Lel




Crossflow
                Jet


      • Combustion inside hypersonic engine requiresetmixing of an und
                                     Figure 1. Schematics of the transverse injection
                                              crossflow (Ben-Yakar al. 2006; Gruber, Nejad,
        optimization due to short residence time                                      Figure 1
                                                turing flows with complex shocks and contact surfaces a
                                                eddying motions present in high Reynolds number flowf
                                                                        The Champigny–Lacau model has
      • Jet in supersonic crossflow exhibits complex flow             upstream separation zone created fro
                                                   In the present study, an under-expanded sonic jet inj
                                                is numerically simulated by using layer interaction also g
                                                                    shock/boundary a high-order low dis
        features; shock-turbulence interactions, 3D vortical
                                                difference scheme (Lele the crossflow, but turns downstre
                                                                    into 1992) and spatial filtering (Gait
        structures                              capture the physicsreferred to as the barrel shock. The ba
                                                                     of the supersonic turbulent mixing. R
                                                capturing schemes the high-wavenumber biased artificia
                                                                     of plume moves downstream. A se
                                                                    vortices moving downstream along th
                                                2005) and diffusivity (Fiorina & Lele 2007) are simpli
                                                and stretched grid originating from the& Lele 2007) to se
                                                                    framework (Kawai boundary layer p
      • Supersonic combustion modeling is crucial to predict        examines this near field mean flow stru
                                                objective of this paper is to develop further insights into
        chemical reaction characteristics       the supersonic jet mixing. Comparisons between the L
                                                data (Santiago & Dutton 1997) are also performed for v
Outline


• Jet in supersonic crossflow (JISC)

• Numerical methodology

  -   Compressible flow solver

  -   Direct quadrature method of moments (DQMOM)

• Result and discussions

  -   Non-reacting jet in supersonic crossflow

  -   Reacting jet in supersonic crossflow
flowfield that makes it difficult to quantify its effect on forces and moments. In the past, some res
                   suggested that the jet can be properly represented by a solid cylinder of given transverse length in in
   Jet in Supersonic Crossflow
                   data have shown that this is not a realistic representation. Such a model does not include plume exp
                   free-stream, plume overexpansion downstream or the horseshoe vortex surrounding the jet arou
                   Subsequently, Champigny and Lacau5 gave a detailed explanation of the flow phenomena pres
354                supersonic cross-flow. TheirS. K. structure model is shown in Fig. 1.
                                 S. Kawai and flow Lele




          crossflow (Ben-Yakar et al. 2006; Gruber, Nejad, ChenChampigny-Lacau
 Figure 1. Schematics of the transverse injection of an under-expanded jet into a supersonic
                                                                 & Dutton 1995).
                                                   Figure 1. Champigny and Lacau flow structure model.5
      • Jet/crossflow interaction creates complex 3D vortical
turing flows with complex shocks and contact surfaces and the 3-D broadband turbulent
                        The Champigny–Lacau model has found widespread acceptance currently. Amongst the flow fea
eddying motions present in high Reynolds number flows.
        structures
   In the present study, an under-expanded sonic jet injected bow a supersonic crossflow the approaching bounda
                    upstream separation zone created from a into shock interaction with
is numerically simulated by using layer interaction also generatesand dissipative compactshock. As the jet exits, it i
                    shock/boundary a high-order low dispersive a shock, or separation
difference scheme (Lele the crossflow, but turns downstream because of 2000) to properly a shock forms around th
                    into 1992) and spatial filtering (Gaitonde & Visbal this interaction and
      • Shock-turbulence interaction
capture the physicsreferred to as the barrel shock. The barrel shock is terminated with a Mach disk and wake vortices a
                     of the supersonic turbulent mixing. Recently developed discontinuity-
capturing schemes the high-wavenumber biased artificial viscosity (Cook formed aft2004, jet plume with the so-c
                     of plume moves downstream. A secondary shock is & Cabot of the
2005) and diffusivity (Fiorina & Lele 2007) are simplified and extended to curvilinear model describes the hors
                    vortices moving downstream along the surface. The Champigny–Lacau
and stretched grid originating from the& Lele 2007) to separation upstream of the jet main
                    framework (Kawai boundary layer perform the simulation. The between the -shock region. Th
      • Highly unsteady flow field
objective of this paper is to develop further insights into the 3-D complex flow physics and moments.
                    examines this near field mean flow structure and their effects on forces of
the supersonic jet mixing. Comparisons between the LES results and the experimental
UTCOMP :         Compressible Flow Solver




• Large-eddy simulation (LES) captures unsteady flow
  motion in turbulence with large length scale

• Flow in subfilter scale needs closure

 -   Dynamic Smagorinsky model is used for closing convective
     terms

• High numerical scheme : 5th order WENO

• MPI based parallelization
ied. The rate of mixing depends on the coefficient
       Direct quadrature method of moments
C / that appears in the definition of the mixing time
scale (Eq. (5)). Figure 5 shows the time-averaged
                                                                                           (DQMOM)
absolute difference between the abscissas normal-
ized by the mean scalar values. When the mixing
coefficient is doubled in value, the peaks are pulled
          • Joint PDF of thermochemical composition variables is
towards the mean, which is reflected in the lower
normalized value. This plot also shows that there
is significant evolved using DQMOM method
               variation in the abscissas with the
maximum OH variation being around four times
the mean value. Since these fluctuations occur in
the shear• Developed forany given time, combustion by Koo et al.
           layer, it is likely that at supersonic
the weight associated with the Combustion Institutes, 2011)
              (Proceedings ofpeaks. of the peaks is
                                 one
much higher than the other            This will reduce Fig. 7. Instantaneous snapshots of OH mass fraction for
the impact of the temperature difference between        (top) high inlet temperature and (bottom) low inlet
                                                          temperature cases.

             Supersonic reacting jet                          Supersonic cavity-stabilized flame
Results and Discussion




• Non-reacting Jet in Supersonic Crossflow

• Reacting Jet in Supersonic Crossflow
Non-reacting Jet in Supersonic Crossflow


• Sonic jet in Mach 2 crossflow

• Momentum ratio = 1.52

• Compared with the experiment from Air Force Research
  Laboratory (AFRL) by Lin et al. (Journal of Propulsion and Power,
  2010)




                                      Crossflow               Jet
                                      Air                    C2H4
                                      M = 2.0                M = 1.0
                                      ρ = 0.65 kg/m3         ρ = 2.504 kg/m3
                                      T = 167 K              T = 287.5 K
                                      p = 31 kPa             p = 213.8 kPa
                                      δ = 6.4 mm             d = 4.8 mm
Computational details
                                                        24d
• 17 million grid cells over
  31d x 8d x 24d                                               8d

  computational domain

 -   15y+ x 1.5y+ x 15y+ near wall                       31d




• Spatial discretization

 -   Flow : 5th order WENO | Scalar : 3rd order QUICK

• Crossflow simulated separated as boundary layer

• Periodic boundary condition in spanwise direction

• Computed with 480 processors for 36 hours
Flow Evolution of Non-reacting JISC


          C2H4




Density gradient magnitude




           Ma
Flow Evolution of Non-reacting JISC


          C2H4




Density gradient magnitude




           Ma
Comparison with the Experiment

                                                 LES                                Experiment




C2H4 on symmetric plane
                                                                         x/d                                        x/d
                                   x/d=5                  x/d=25                 x/d=5               x/d=25
                             y/d                 y/d                       y/d                 y/d




C2H4 at x/d=5 and x/d=25
                                           z/d                     z/d                   z/d                  z/d




                                                       Wall                                           PSP


Wall pressure distribution
                                                               x/d                                                   x/d
Comparison with the Experiment

                                            LES                                 Experiment

                             y/d                                 y/d




C2H4 on symmetric plane
                                   x/d=5                         x/d   x/d=5                       x/d



                                                         z/d                             z/d


                             y/d                                 y/d
C2H4 at x/d=5 and x/d=25



                                                  Wall                                       PSP
                                                  Wall                                       PSP
                                   x/d=25                              x/d=25

Wall pressure distribution                                     x/d                                  x/d
                                                         z/d   x/d                           z/d    x/d
Comparison with the Experiment

                                                 LES                                Experiment




C2H4 on symmetric plane
                                                                         x/d                                        x/d
                                   x/d=5                  x/d=25                 x/d=5               x/d=25
                             y/d                 y/d                       y/d                 y/d




C2H4 at x/d=5 and x/d=25
                                           z/d                     z/d                   z/d                  z/d




                                                       Wall                                           PSP


Wall pressure distribution
                                                               x/d                                                   x/d
Shock Structures in JISC




                                                         Bow shock
                                                                                Reflected shock




                                               λ-shock
                                                                Barrel shock




Recirculation zones                                        Expansion fan       Mach disk




              • Most of jet fluid passes through windward side of
                barrel shock and Mach disk
suggested that the jet can be properly represented by a solid cylinder of given tra
      Shock Structures in JISC
                   data have shown that this is not a realistic representation. Such a model does no
                   free-stream, plume overexpansion downstream or the horseshoe vortex surrou
                   Subsequently, Champigny and Lacau5 gave a detailed explanation of the flo
354                supersonic cross-flow. TheirS. K. structure model is shown in Fig. 1.
                                 S. Kawai and flow Lele




                                                                    Bow shock
                                                                                          Reflected shock




                                                          λ-shock
                                                                           Barrel shock




          crossflow (Ben-Yakar et al. 2006; Gruber, Nejad, ChenChampigny-Lacau
 Figure 1. Schematics of the transverse injection of an under-expanded jet intoMach disk
                                                                  Expansion fan a supersonic
                                                                 & Dutton 1995).
                                                   Figure 1. Champigny and Lacau flow structure mo
turing flowsUnderexpandedand contact surfaces and the 3-D barrel shock
        • with complex shocks jet in crossflow creates broadband turbulent
                        The Champigny–Lacau model has found widespread acceptance currently. A
eddying motions present in high Reynolds number flows.
            and Mach disk
   In the present study, an under-expanded sonic jet injected bow a supersonic crossflow the a
                    upstream separation zone created from a into shock interaction with
is numerically simulated by using layer interaction also generatesand dissipative compactshock.
                    shock/boundary a high-order low dispersive a shock, or separation
difference scheme (Lele the crossflow, but turns downstream becausethethis interaction and a sho
        • Common1992) and structures are visible Visbal 2000) to properly
                    into shock spatial filtering (Gaitonde & in of result
capture the physicsreferred to as the barrel shock. The barrel shock is terminated with a Mach disk
                     of the supersonic turbulent mixing. Recently developed discontinuity-
Vortical Structures in JISC
Vortical Structures in JISC

                   agn itude
                  m
             ient
        grad
Density
Vortical Structures in JISC
Vortical Structures in JISC


                                  C2H4 = 0.8




                              Q-criterion vorticity
                              with contour of C2H4
Vortical Structures in JISC
Vortical Structures in JISC




                   C2H4 = 0.8                            Vortical structure


• Boundary layer thickening is seen in the shock-boundary
  layer interaction

• Jet/crossflow interaction creates vortical structures

• Interaction of vortical structures is closely related to efficient
  mixing in the near field
Vortical Structures in JISC
Vortical Structures in JISC
Vortical Structures in JISC



          Long streak of
       streamwise vorticity
Vortical Structures in JISC

                                         x/d = 5
                                         x/d = 0


          Long streak of
       streamwise vorticity
                                         x/d = 3




                                         x/d = 5
                                               0




                              LES   Experiment
Results and Discussion




• Non-reacting Jet in Supersonic Crossflow

• Reacting Jet in Supersonic Crossflow
Reacting Jet in Supersonic Crossflow



• Sonic jet in Mach 3.38 crossflow

• Momentum ratio = 1.4

• Compared with the experiment by Ben-Yakar et al.
  (Physics of Fluids, 2006)



                                    Crossflow           Jet
                                    Air                C2H4
                                    M = 3.38           M = 1.0
                                    ρ = 0.0846 kg/m3   ρ = 7.02 kg/m3
                                    T = 1290 K         T = 263 K
                                    p = 32.4 kPa       p = 550 kPa
                                    δ = 0.75 mm        d = 2 mm
Computational details
                                              24d
• 15 million grid cells over
  21d x 10d x 24d                                    10d

  computational domain

 -   60y+ x 2y+ x 60y+ near wall               21d




• Periodic boundary in spanwise direction

• LES-DQMOM methodology for combustion modeling

 -   Reduced 13 species C2H4-air mechanism

• Computed with 820 processors for 72 hours
026101-9   Transverse jets in supersonic crossflows
       Shock Structures Comparison
                                    LES                                   Experiment




                                                   026101-6      Ben-Yakar, Mungal, and Hanson
Instantaneous




Time-averaged



        • Shock structure is highly unsteady dueschlieren imagefeatures coherent structures
                                      FIG. 5. An example to flapping s exposure time for
                                      injection case. While the unsteady
                                                                         with 3

          motion at the windward sideaged tothe some of the weak shocks such as upstream separat
                                        of zero, barrel shock
                                                   wave and downstream recompression wave are emphasized.
Flow Evolution of Reacting JISC




        Mixture Fraction




        Temperature (K)
Flow Evolution of Reacting JISC




        Mixture Fraction




        Temperature (K)
Flow Evolution of Reacting JISC

                   t1            0.5 flow
                                              t2
                             residence time




Mixture Fraction




Temperature (K)




      OH
Flow Evolution of Reacting JISC



                       0.5 flow
                   residence time
Flow Evolution of Reacting JISC



                          0.5 flow
                      residence time




• Mixing depends on much larger coherent motions

• Low Reynolds number in crossflow cause the mixing
  process to be “tearing up” rather than effective
  turbulent mixing
Flow Configuration

• Difference in flow configuration between non-reacting
  and reacting jet

• Reacting case had thinner boundary layer thickness
  (shock tunnel)


                Non-reacting       Reacting
         J          1.52           1.4 ± 0.1
       Rejet      ~420,000         ~480,000
        Reδ       ~190,000          ~3,000
         δ         1.33 D           0.375 D
        Ujet      325 m/s          315 m/s
Time-averaged Mixing Properties




• Entrainment heavily depends on large coherent motion

• Inefficient mixing quality in the near field (mixture
  fraction RMS ~ 0.5)

• Flow residence time much smaller than ignition time
  delay
Conclusions


• LES captures unsteady motion of jet in supersonic
  crossflow accurately

• Flow structures in JISC were studied

• LES-DQMOM methodology was used to study
  supersonic combustion with multivariate ethylene-air
  reaction mechanism

• Reacting case did not have enough near field mixing

• No flame stabilization was found in the reacting case
Questions

     Large Eddy Simulation based Studies of
    Reacting and Non-reacting Transverse Jets
             in Supersonic Crossflow
           Shaun Kim a,b   Pratik Donde a Venkat Raman a
                Kuo-Cheng Lin c   Campbell Carter d



a                  b                      c                d

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LES-DQMOM based Studies on Reacting and Non-reacting Jets in Supersonic Crossflow

  • 1. 50th AIAA Aerospace Science Meeting Nashville, Tennessee January 10th, 2012 Acknowledgements Texas Advanced Computing Center Large Eddy Simulation based Studies of Reacting and Non-reacting Transverse Jets in Supersonic Crossflow Shaun Kim a,b Pratik Donde a Venkat Raman a Kuo-Cheng Lin c Campbell Carter d Department of Aerospace Engineering and Engineering Mechanics The University of Texas at Austin a b c d
  • 2. data have shown that this is not a reali free-stream, plume overexpansion do Motivation 354 Subsequently, Champigny and Lacau supersonic cross-flow. TheirS. K. stru S. Kawai and flow Lel Crossflow Jet • Combustion inside hypersonic engine requiresetmixing of an und Figure 1. Schematics of the transverse injection crossflow (Ben-Yakar al. 2006; Gruber, Nejad, optimization due to short residence time Figure 1 turing flows with complex shocks and contact surfaces a eddying motions present in high Reynolds number flowf The Champigny–Lacau model has • Jet in supersonic crossflow exhibits complex flow upstream separation zone created fro In the present study, an under-expanded sonic jet inj is numerically simulated by using layer interaction also g shock/boundary a high-order low dis features; shock-turbulence interactions, 3D vortical difference scheme (Lele the crossflow, but turns downstre into 1992) and spatial filtering (Gait structures capture the physicsreferred to as the barrel shock. The ba of the supersonic turbulent mixing. R capturing schemes the high-wavenumber biased artificia of plume moves downstream. A se vortices moving downstream along th 2005) and diffusivity (Fiorina & Lele 2007) are simpli and stretched grid originating from the& Lele 2007) to se framework (Kawai boundary layer p • Supersonic combustion modeling is crucial to predict examines this near field mean flow stru objective of this paper is to develop further insights into chemical reaction characteristics the supersonic jet mixing. Comparisons between the L data (Santiago & Dutton 1997) are also performed for v
  • 3. Outline • Jet in supersonic crossflow (JISC) • Numerical methodology - Compressible flow solver - Direct quadrature method of moments (DQMOM) • Result and discussions - Non-reacting jet in supersonic crossflow - Reacting jet in supersonic crossflow
  • 4. flowfield that makes it difficult to quantify its effect on forces and moments. In the past, some res suggested that the jet can be properly represented by a solid cylinder of given transverse length in in Jet in Supersonic Crossflow data have shown that this is not a realistic representation. Such a model does not include plume exp free-stream, plume overexpansion downstream or the horseshoe vortex surrounding the jet arou Subsequently, Champigny and Lacau5 gave a detailed explanation of the flow phenomena pres 354 supersonic cross-flow. TheirS. K. structure model is shown in Fig. 1. S. Kawai and flow Lele crossflow (Ben-Yakar et al. 2006; Gruber, Nejad, ChenChampigny-Lacau Figure 1. Schematics of the transverse injection of an under-expanded jet into a supersonic & Dutton 1995). Figure 1. Champigny and Lacau flow structure model.5 • Jet/crossflow interaction creates complex 3D vortical turing flows with complex shocks and contact surfaces and the 3-D broadband turbulent The Champigny–Lacau model has found widespread acceptance currently. Amongst the flow fea eddying motions present in high Reynolds number flows. structures In the present study, an under-expanded sonic jet injected bow a supersonic crossflow the approaching bounda upstream separation zone created from a into shock interaction with is numerically simulated by using layer interaction also generatesand dissipative compactshock. As the jet exits, it i shock/boundary a high-order low dispersive a shock, or separation difference scheme (Lele the crossflow, but turns downstream because of 2000) to properly a shock forms around th into 1992) and spatial filtering (Gaitonde & Visbal this interaction and • Shock-turbulence interaction capture the physicsreferred to as the barrel shock. The barrel shock is terminated with a Mach disk and wake vortices a of the supersonic turbulent mixing. Recently developed discontinuity- capturing schemes the high-wavenumber biased artificial viscosity (Cook formed aft2004, jet plume with the so-c of plume moves downstream. A secondary shock is & Cabot of the 2005) and diffusivity (Fiorina & Lele 2007) are simplified and extended to curvilinear model describes the hors vortices moving downstream along the surface. The Champigny–Lacau and stretched grid originating from the& Lele 2007) to separation upstream of the jet main framework (Kawai boundary layer perform the simulation. The between the -shock region. Th • Highly unsteady flow field objective of this paper is to develop further insights into the 3-D complex flow physics and moments. examines this near field mean flow structure and their effects on forces of the supersonic jet mixing. Comparisons between the LES results and the experimental
  • 5. UTCOMP : Compressible Flow Solver • Large-eddy simulation (LES) captures unsteady flow motion in turbulence with large length scale • Flow in subfilter scale needs closure - Dynamic Smagorinsky model is used for closing convective terms • High numerical scheme : 5th order WENO • MPI based parallelization
  • 6. ied. The rate of mixing depends on the coefficient Direct quadrature method of moments C / that appears in the definition of the mixing time scale (Eq. (5)). Figure 5 shows the time-averaged (DQMOM) absolute difference between the abscissas normal- ized by the mean scalar values. When the mixing coefficient is doubled in value, the peaks are pulled • Joint PDF of thermochemical composition variables is towards the mean, which is reflected in the lower normalized value. This plot also shows that there is significant evolved using DQMOM method variation in the abscissas with the maximum OH variation being around four times the mean value. Since these fluctuations occur in the shear• Developed forany given time, combustion by Koo et al. layer, it is likely that at supersonic the weight associated with the Combustion Institutes, 2011) (Proceedings ofpeaks. of the peaks is one much higher than the other This will reduce Fig. 7. Instantaneous snapshots of OH mass fraction for the impact of the temperature difference between (top) high inlet temperature and (bottom) low inlet temperature cases. Supersonic reacting jet Supersonic cavity-stabilized flame
  • 7. Results and Discussion • Non-reacting Jet in Supersonic Crossflow • Reacting Jet in Supersonic Crossflow
  • 8. Non-reacting Jet in Supersonic Crossflow • Sonic jet in Mach 2 crossflow • Momentum ratio = 1.52 • Compared with the experiment from Air Force Research Laboratory (AFRL) by Lin et al. (Journal of Propulsion and Power, 2010) Crossflow Jet Air C2H4 M = 2.0 M = 1.0 ρ = 0.65 kg/m3 ρ = 2.504 kg/m3 T = 167 K T = 287.5 K p = 31 kPa p = 213.8 kPa δ = 6.4 mm d = 4.8 mm
  • 9. Computational details 24d • 17 million grid cells over 31d x 8d x 24d 8d computational domain - 15y+ x 1.5y+ x 15y+ near wall 31d • Spatial discretization - Flow : 5th order WENO | Scalar : 3rd order QUICK • Crossflow simulated separated as boundary layer • Periodic boundary condition in spanwise direction • Computed with 480 processors for 36 hours
  • 10. Flow Evolution of Non-reacting JISC C2H4 Density gradient magnitude Ma
  • 11. Flow Evolution of Non-reacting JISC C2H4 Density gradient magnitude Ma
  • 12. Comparison with the Experiment LES Experiment C2H4 on symmetric plane x/d x/d x/d=5 x/d=25 x/d=5 x/d=25 y/d y/d y/d y/d C2H4 at x/d=5 and x/d=25 z/d z/d z/d z/d Wall PSP Wall pressure distribution x/d x/d
  • 13. Comparison with the Experiment LES Experiment y/d y/d C2H4 on symmetric plane x/d=5 x/d x/d=5 x/d z/d z/d y/d y/d C2H4 at x/d=5 and x/d=25 Wall PSP Wall PSP x/d=25 x/d=25 Wall pressure distribution x/d x/d z/d x/d z/d x/d
  • 14. Comparison with the Experiment LES Experiment C2H4 on symmetric plane x/d x/d x/d=5 x/d=25 x/d=5 x/d=25 y/d y/d y/d y/d C2H4 at x/d=5 and x/d=25 z/d z/d z/d z/d Wall PSP Wall pressure distribution x/d x/d
  • 15. Shock Structures in JISC Bow shock Reflected shock λ-shock Barrel shock Recirculation zones Expansion fan Mach disk • Most of jet fluid passes through windward side of barrel shock and Mach disk
  • 16. suggested that the jet can be properly represented by a solid cylinder of given tra Shock Structures in JISC data have shown that this is not a realistic representation. Such a model does no free-stream, plume overexpansion downstream or the horseshoe vortex surrou Subsequently, Champigny and Lacau5 gave a detailed explanation of the flo 354 supersonic cross-flow. TheirS. K. structure model is shown in Fig. 1. S. Kawai and flow Lele Bow shock Reflected shock λ-shock Barrel shock crossflow (Ben-Yakar et al. 2006; Gruber, Nejad, ChenChampigny-Lacau Figure 1. Schematics of the transverse injection of an under-expanded jet intoMach disk Expansion fan a supersonic & Dutton 1995). Figure 1. Champigny and Lacau flow structure mo turing flowsUnderexpandedand contact surfaces and the 3-D barrel shock • with complex shocks jet in crossflow creates broadband turbulent The Champigny–Lacau model has found widespread acceptance currently. A eddying motions present in high Reynolds number flows. and Mach disk In the present study, an under-expanded sonic jet injected bow a supersonic crossflow the a upstream separation zone created from a into shock interaction with is numerically simulated by using layer interaction also generatesand dissipative compactshock. shock/boundary a high-order low dispersive a shock, or separation difference scheme (Lele the crossflow, but turns downstream becausethethis interaction and a sho • Common1992) and structures are visible Visbal 2000) to properly into shock spatial filtering (Gaitonde & in of result capture the physicsreferred to as the barrel shock. The barrel shock is terminated with a Mach disk of the supersonic turbulent mixing. Recently developed discontinuity-
  • 18. Vortical Structures in JISC agn itude m ient grad Density
  • 20. Vortical Structures in JISC C2H4 = 0.8 Q-criterion vorticity with contour of C2H4
  • 22. Vortical Structures in JISC C2H4 = 0.8 Vortical structure • Boundary layer thickening is seen in the shock-boundary layer interaction • Jet/crossflow interaction creates vortical structures • Interaction of vortical structures is closely related to efficient mixing in the near field
  • 25. Vortical Structures in JISC Long streak of streamwise vorticity
  • 26. Vortical Structures in JISC x/d = 5 x/d = 0 Long streak of streamwise vorticity x/d = 3 x/d = 5 0 LES Experiment
  • 27. Results and Discussion • Non-reacting Jet in Supersonic Crossflow • Reacting Jet in Supersonic Crossflow
  • 28. Reacting Jet in Supersonic Crossflow • Sonic jet in Mach 3.38 crossflow • Momentum ratio = 1.4 • Compared with the experiment by Ben-Yakar et al. (Physics of Fluids, 2006) Crossflow Jet Air C2H4 M = 3.38 M = 1.0 ρ = 0.0846 kg/m3 ρ = 7.02 kg/m3 T = 1290 K T = 263 K p = 32.4 kPa p = 550 kPa δ = 0.75 mm d = 2 mm
  • 29. Computational details 24d • 15 million grid cells over 21d x 10d x 24d 10d computational domain - 60y+ x 2y+ x 60y+ near wall 21d • Periodic boundary in spanwise direction • LES-DQMOM methodology for combustion modeling - Reduced 13 species C2H4-air mechanism • Computed with 820 processors for 72 hours
  • 30. 026101-9 Transverse jets in supersonic crossflows Shock Structures Comparison LES Experiment 026101-6 Ben-Yakar, Mungal, and Hanson Instantaneous Time-averaged • Shock structure is highly unsteady dueschlieren imagefeatures coherent structures FIG. 5. An example to flapping s exposure time for injection case. While the unsteady with 3 motion at the windward sideaged tothe some of the weak shocks such as upstream separat of zero, barrel shock wave and downstream recompression wave are emphasized.
  • 31. Flow Evolution of Reacting JISC Mixture Fraction Temperature (K)
  • 32. Flow Evolution of Reacting JISC Mixture Fraction Temperature (K)
  • 33. Flow Evolution of Reacting JISC t1 0.5 flow t2 residence time Mixture Fraction Temperature (K) OH
  • 34. Flow Evolution of Reacting JISC 0.5 flow residence time
  • 35. Flow Evolution of Reacting JISC 0.5 flow residence time • Mixing depends on much larger coherent motions • Low Reynolds number in crossflow cause the mixing process to be “tearing up” rather than effective turbulent mixing
  • 36. Flow Configuration • Difference in flow configuration between non-reacting and reacting jet • Reacting case had thinner boundary layer thickness (shock tunnel) Non-reacting Reacting J 1.52 1.4 ± 0.1 Rejet ~420,000 ~480,000 Reδ ~190,000 ~3,000 δ 1.33 D 0.375 D Ujet 325 m/s 315 m/s
  • 37. Time-averaged Mixing Properties • Entrainment heavily depends on large coherent motion • Inefficient mixing quality in the near field (mixture fraction RMS ~ 0.5) • Flow residence time much smaller than ignition time delay
  • 38. Conclusions • LES captures unsteady motion of jet in supersonic crossflow accurately • Flow structures in JISC were studied • LES-DQMOM methodology was used to study supersonic combustion with multivariate ethylene-air reaction mechanism • Reacting case did not have enough near field mixing • No flame stabilization was found in the reacting case
  • 39. Questions Large Eddy Simulation based Studies of Reacting and Non-reacting Transverse Jets in Supersonic Crossflow Shaun Kim a,b Pratik Donde a Venkat Raman a Kuo-Cheng Lin c Campbell Carter d a b c d