2.1 Physical model and flow parameters

The physical model is a rectangular channel, which is 250mm long, 20mm wide and 20mm high, and these values are chosen in order to consider the wall effect on the working process in a real scramjet engine for its engineering application. An injector with its diameter being 2mm is set on the bottom wall of the channel. The geometric structure of the calculation domain is shown in Fig. 1. The incoming flow is from left to right. The coordinate origin is set at the centre of the injector, and it is 100mm away from the inlet of the incoming flow. The whole flow field is symmetrical about the XOY plane.

Figure 1.

Schematic diagram of the physical model employed in the current study.

The flow parameters are consistent with the work of Erdem et al. [Reference Erdem and Kontis20] The incoming flow is air, and it is composed of 21% oxygen and 79% nitrogen. The jet is hydrogen, with its jet angle being 90°, and the jet momentum flux ratio (J) is 1.85. The jet momentum flux ratio is defined as the ratio between the momentum fluxes on the jet exit and in the crossflow, and its equation can refer to Ref. [Reference Huang5]. Table 1 shows the specific flow parameters of the incoming flow and the jet. Due to the symmetry of the flow field, half of the calculation domain is selected for this solution. The boundary conditions are set as follows, namely the supersonic incoming flow is set as the far pressure field, the fuel injector is set as the pressure inlet, the downstream outlet boundary is the pressure outlet, and the other surfaces are no slip wall.

The waveform of the pulsed jet is sine wave, and the frequencies are f ₁ = 12.5kHz, f ₂ = 20kHz and f ₃ = 50kHz, respectively. The pulsed realisation of the jet outlet relies on the user-defined function (UDF), and it shows the change law of the pulsed jet with the variation of the momentum flux ratio.

(1) \begin{align} J = {J_0} + {J_a} \times \sin\!(2 \times 3.14159\,ft) \end{align}

Herein, J is the momentum flux ratio which varies with time, and J ₀ is the benchmark momentum flux ratio. J _a is the amplitude of sinusoidal variation, and its value is 1.0. f is the frequency of sine wave, and t is the flow time in the flow field.

In order to make the calculation results of the pulsed jet stable and reliable, the calculation of the unsteady flow field is started on the basis of the steady state of the basic calculation example, and the UDF is loaded by compiling. In the process of calculating each time step, when the residual curve drops by more than three orders of magnitude and remains stable, it is considered that the time step converges. In the unsteady state calculation, the time steps of f ₁ , f ₂ and f ₃ frequency pulsed jets are set to be 4.0 × 10⁻⁶s, 2.5×10⁻⁶s and 1.0×10⁻⁶s, respectively.

2.2 Numerical approach and validation

The structured grids of the computational domain are obtained by the ANSYS ICEM, and the numerical simulation is conducted by means of the ANSYS Fluent. Then, Tecplot and Origin are used for post-processing of computational results. At the same time, a parallel computing environment provided by Beijing Supercomputing Center is utilised to improve the computational efficiency. The flow field is solved based on the cell centred finite volume method, and the SST·k-ω model is selected as the turbulence model. An implicit, steady/unsteady solver based on density coupling is used to solve the three-dimensional compressible Reynolds-averaged Navier Stokes (RANS) equations. The upwind scheme with spatial second-order accuracy, AUSM vector splitting scheme and green Gauss·cell-based gradient calculation method are utilised, and the CFL number is keep as 0.5 during the calculation process.

The RANS method solves the averaged control equations. After Favre averaging, the transport equations can be obtained. In order to verify the calculation accuracy of the numerical method adopted in this paper, a numerical simulation is conducted based on the ground experiment of a transverse jet in the supersonic crossflow conducted by Santiago et al., [Reference Santiago and Dutton21] and the calculation results are compared with the available test data captured from the experimental velocity contours which are also available in Ref. [Reference Kawai and Lele22]. In this test, the materials for the crossflow and transverse jet are both set to be air, and the ratio of its specific heat is 1.4. Three mean velocity components were measured through the two-component, frequency preshifted laser Doppler velocimetry. The Mach number of the crossflow is 1.6, with its static pressure and temperature being 56.7kPa and 198K, respectively. For the jet, the Mach number is 1.0, the static pressure is 247KPa, and the static temperature is 250K. The momentum flux ratio is 1.7. The calculation domain is a rectangular channel, with its dimensions being −37.5 < x/D < 37.5, 0 < y/D < 9, −9.5 < z/D < 9.5. Herein, D is the diameter of the injector, with its value being 4mm, and the coordinate origin is set at the centre of the injector.

In order to ensure that ${y^ + }$ is less than 1.0, the height of the first layer of grid on the wall is set to be 0.001mm, and the elements are refined in the area with complex flow fields near the injector. In order to ensure the reliability of the calculation results and avoid the influence of mesh size, three mesh sizes are selected for calculation, and the mesh independence is verified. The number of elements are 2.0 million, 2.5 million and 3.0 million, respectively. Figure 2 shows the division results of the moderate grid employed in the current study.

Table 1.

Flow parameters employed in the current study

Figure 2.

Schematic diagram of the moderate grid employed in the current study.

Figure 3 shows the calculation results of three mesh sizes, which respectively represent the distribution of dimensionless flow velocity along the normal direction at different flow positions (x/D = 4, 5) which are on the centre of the symmetry plane. The obtained results show that the mesh size only has little effect on the calculation results, and there is little difference between the moderate and fine meshes mostly. The numerical method can effectively obtain the characteristics of the flow field, and the predicted results are in good agreement with the available experimental data in terms of trend and value. This may imply that the numerical method is reliable for subsequent calculations.

Figure 3.

Comparison of numerical and experimental nondimensional velocities in the flow direction.

3.1 Time evolution characteristics of flow field

In order to analyse the change law of the pulsed jet flow field structure in a cycle, the pulsed jet flow field with a frequency of 50kHz is selected to show the flow field structure at different times in a cycle.

Figure 4 shows the contours of hydrogen mole fraction on the central symmetry plane at different times. 0/4T represents the starting point of upward movement in this cycle. At this time, the instantaneous jet momentum flux ratio of the pulsed jet is 1.85, and this is the same as the steady jet. The main effect of the pulsed jet on the flow field is form a high-low alternating wavy structure in the flow field. The appearance of this structure makes the hydrogen surface in the flow field no longer smooth. At the wavy structure, there is a high hydrogen concentration, and the wavy structure appears intermittently in the flow direction, which has an important impact on the mixing performance of the fuel jet.

Figure 4.

Hydrogen mole fraction contours on the symmetry plane at different times.

The shape of the hydrogen core near the injector is different at different times. At 0/4T, the area of the hydrogen core is the smallest, and its tilt angle is the largest. At 1/4T and 2/4T, the hydrogen cores are larger in the flow field, their flow fields are more similar, and the differences in the hydrogen core and the structures of the recirculation region are smaller. The flow field structure at 3/4T is similar to that at 0/4T.

The flow positions of the jet downstream wavy structure are different at different times. The wavy structure will move downstream of the jet with time. In the early stage of the formation of the wavy structure, the hydrogen surface near the injector will form a bulge, where the jet penetration depth will be improved, which is conducive to the normal transportation of fuel, generating a larger normal distribution, and avoiding the accumulation of heat on the wall during combustion. With the development of time, the wavy structure will be separated from the mainstream of the jet in the influence of the crossflow, and forming an independent structure. The flow distance of the wavy structure in the flow field is about 10mm, and almost only one structure is formed in a cycle. Therefore, it takes some time for the pulsed jet to establish its influence in the whole flow field.

3.2 Comparative analysis of steady jet flow field and pulsed mean flow field

In this section, the steady jet flow field and the mean flow field of the pulsed jet are compared and analysed. The mean flow field is the average of two cycles of flow after the pulsed effect is established in the whole flow field.

Figure 5 shows the steady jet and the mean flow field structures of three different frequencies. The contours of hydrogen mass fraction and streamlines are shown on the x = 3 and 10mm cross-sectional planes. According to the hydrogen mass fraction contours in Fig. 5, the hydrogen concentration in the x = 3 and 10mm cross-sectional planes of the steady jet is greater than that in the mean flow field of the pulsed jet, indicating that the mixing efficiency of the pulsed jet is higher, and the mixing is complete earlier for the pulsed jet. Among them, the hydrogen concentration are the smallest on the 50kHz jet, and this means that the mixing efficiency are the highest for these conditions employed in this study. The hydrogen distributions of the two low-frequency pulsed jets on the x = 10mm cross-sectional plane are higher in the normal direction, and they have the highest penetration at this time. However, in the 50kHz jet, the fuel distribution shown in Fig. 5 almost have not raised in the normal direction.

Figure 5.

Hydrogen mass fraction contours and streamlines on cross-sectional planes located at x = 3mm and 10 mm of steady jet and the mean flow field of pulsed jet.

In order to analyse the mixing in the transverse jet flow field, the mixing efficiency, the total pressure recovery coefficient and jet penetration depth are all selected for analysis.

The mixing efficiency is used to evaluate the mixing and combustion process along the flow direction. It is defined as the ratio of the fuel mass flow passing the flow cross-sectional planes that can participate in the combustion to the total fuel mass flow. Its expression is shown in the formula (2) [Reference Gerlinger, Stoll, Kindler, Schneider and Aigner23].

(2) \begin{align} {\eta _{{\textit{mix}}}}({{x}}) = \frac{{\int_A {{\alpha _{react}}\rho udA} }}{{\int_A {\alpha \rho udA} }} \end{align}

(3) \begin{align} {\alpha _{react}} = \left\{ \begin{array}{l@{\quad}l}\alpha & \alpha \le {\alpha _{stoic}}\\[5pt] {\alpha _{stoic}}(1 - \alpha ){\rm{ /}}({\rm{1 - }}{\alpha _{stoic}}) & \alpha \gt {\alpha _{stoic}}\end{array} \right. \end{align}

The fuel is hydrogen, $\rho $ is the local density, u is the local velocity, A is the axial area of mixing, α is the mass fraction of fuel, ${\alpha _{stoic}}$ is the mass fraction of fuel at the chemical equivalence ratio. For hydrogen, this value is 0.0283. From the expression, when the mass fraction of hydrogen is less than 0.0283, hydrogen and air are mixed, and the mixing efficiency reaches 1.0.

The penetration depth is an important characteristic parameter of the engine. It is calculated according to the fuel centroid, and its expression is shown in the formula (4) [Reference Lee and Mitani24].

(4) \begin{align} {P_{{H_2}}}({{x}}) = \frac{{\int_A {\alpha \rho uydA} }}{{\int_A {\alpha \rho udA} }} \end{align}

The total pressure recovery coefficient is the ratio of the local total pressure to the crossflow total pressure, and it can reflect the thrust of the engine.

Figure 6 shows the mixing efficiency, penetration depth and total pressure recovery coefficient curves of steady and pulsed jets. From the mixing efficiency curve, the application of the pulsed jet can enhance the mixing effect of flow field. Among them, the mixing efficiency of 50kHz pulsed jet is higher, the influence of two low-frequency pulsed jet on the mixing of flow field is mainly reflected in the far-field downstream of the jet, and the mixing efficiency is significantly improved in the far-field. In the penetration depth curve, the 50kHz pulsed jet can improve the penetration depth of the downstream far-field region. In the near field, the penetration depth of the low-frequency pulsed jet is deeper. However, in the downstream of the flow field, the penetration depth will first decrease and then increase, and the penetration depth of the steady jet is above them finally. The pulsed jet has little effect on the total pressure recovery coefficient at the outlet of the channel.

Figure 6.

Comparison of mixing parameters of steady jet and the mean flow field of pulsed jet.

3.3 Comparative analysis of steady jet and pulsed instantaneous flow field

In this section, the steady jet reference case and the instantaneous flow field structure of the pulsed jet will be analysed. The instantaneous jet momentum flux ratio of the pulsed jet is 1.85, and it is in the upward range of the sine wave. For the convenience of subsequent analysis, different cases are named as Case1–Case4, and their boundary condition settings are shown in Table 2.

Table 2.

Boundary condition settings for different cases

Figure 7 shows the contours of hydrogen mass fraction on the cross-sectional planes of x = 0, 5, 10, 15, 20 and 25mm, and the red solid line represents the streamline of hydrogen mass fraction being 0.01, which can represent the normal and spanwise hydrogen distribution on the section.

Figure 7.

Hydrogen mass fraction contours and 0.01 streamline on the cross-sectional planes.

Figure 7(a) represents the case of the steady jet. The hydrogen has just left the injector and gathered in a relatively concentrated area. In the process of flowing downstream, it is gradually divided into two parts, and there is an obvious gap between the hydrogen plumes in the two parts.

In the process of hydrogen flowing downstream in the pulsed jet, the region with high hydrogen concentration will appear intermittently, and this indicates that the pulsed impact on the jet flow field exists. On the cross-sectional plane of x = 0mm, the steady jet plume occupies a larger area, while the plumes of the three unsteady flow fields are relatively concentrated in a smaller area. At this time, the steady flow field has deeper normal penetration and spanwise distribution at the jet outlet. On the x = 5mm cross-sectional plane, Case1 has the highest hydrogen concentration, Case4 has the lowest hydrogen concentration and the core of the plume is at a higher position. The hydrogen distributions of Case2 and Case3 are basically similar except for different distributions in the spanwise width. Therefore, at this position, the steady jet has a lower mixing efficiency, the pulsed jet of 50kHz has a higher mixing efficiency, and the two pulsed jets with relatively low frequency have the same mixing efficiency. Moreover, the hydrogen at 50kHz has higher penetration depth and spanwise distribution.

In the process of flowing downstream, Case4 first appears the first high concentration area of hydrogen, which is at the position of x = 20mm. The mixing between the hydrogen and the crossflow is greatly affected here, the mixing effect here decreases significantly when compared with its previous cross-sectional planes, the hydrogen plumes on this cross-sectional plane gather again, and the previous gap no longer exists. However, the high concentration area of hydrogen in Case3 appears at a later position than Case4, where x = 25mm, and its concentration has increased more than Case4. The hydrogen mixing becomes worse here, it can be seen that Case3 has a lower mixing efficiency here. The hydrogen concentration of Case2 at x = 15, 20 and 25mm is the lowest. At this time, its mixing is more efficient. On the cross-sectional plane shown in Fig. 7, Case2 has not yet appeared the first high hydrogen concentration area, and it should be in a more backward position.

Figure 8 shows the contours and streamlines of hydrogen mole fraction on the cross-sectional planes of x = 5 and 20mm. On the x = 5mm cross-sectional plane, the counter rotating vortex pair is basically under the hydrogen plume, while on the x = 20mm cross-sectional plane, the position of the core of counter rotating vortex pair is basically equivalent to the core of plume, indicating that the vortex structure plays an important role in the fuel transportation process, in the process of flowing downstream, the size of the vortex pair will increase, and the greater the role of the vortex pair on fuel transportation. The area occupied by the hydrogen plume of Case4 on the section of x = 5mm is the largest, and its concentration is also the lowest, the frequency of 50kHz on this section has the highest mixing efficiency and deepest penetration depth, which is consistent with the above conclusion. Case2 and Case3 are affected by the pulse, the areas occupied by the hydrogen plume decrease, and the hydrogen penetration reduces, but their mixing efficiencies improve that of the steady state. In the two low-frequency jet, the wake vortex structure appears on the section x = 5mm, but does not appear in the other two frequencies. On the x = 25mm section, Case1 and Case4 have a similar jet penetration depth, but Case4 has a higher mixing efficiency, and its penetration depth is weaker than that of the x = 5mm section, while the penetration depth in Case1 is improved, and the hydrogen spanwise width of Case4 is also less than that of Case1.

Figure 8.

Hydrogen mole fraction contours and streamlines on the cross-sectional planes located at x = 5mm and 25mm.

Figure 9 shows the contours and streamlines of hydrogen mole fraction on the central symmetry plane, in which the structure of the two upstream reflux areas and the downstream low-speed reflux area can be observed.

Figure 9.

Hydrogen mole fraction counters and streamlines on the symmetric plane.

It can be seen from Fig. 9(a) that in the steady jet, the surface of the hydrogen core is relatively smooth, the concentration of hydrogen decreases along the flow direction, and the penetration depth increases. Compared with Fig. 9(a)–(d), the pulsed jet increases the unsteady characteristics of the flow field. Under the action of the pulse, the surface of the hydrogen plume twists and turns, and the uneven wavy structure appears. The hydrogen distribution of Case2 and Case3, the two low-frequency pulse, is relatively similar, and the main difference is in the positions of the first hydrogen high concentration area in the downstream and the size of the upstream reflux area. In Case2, the location of the downstream high concentration area is relatively backward, and the low concentration area downstream of the jet occupies a larger area, which is also the reason why the high concentration area is not shown in Fig. 7(b). In Case3, the appearance of this area is earlier, and the appearance of this high concentration area represents that the fuel mixing is not completed well. It is found that the increase of pulses frequency reduces the downstream low concentration area occupy.

In Fig. 9(d), the pulsed frequency is 50kHz, which causes the wavy structure on the surface of hydrogen in the flow field to show intensive, the distance between the wavy structure is small, and hydrogen is mainly distributed in the near-field area downstream of the jet. Compared with the flow field of low pulsed frequency, the pulsed frequency of the hydrogen jet is faster, but the amplitude of the fluctuation is not as large as that of the low-frequency pulsed jet flow field, the spanwise area of the hydrogen in the downstream near-field area on the wall is larger and gradually decreases along the flow direction, which is different from the development law of the wall hydrogen distribution of the low-frequency jet.

Figure 10 shows the mixing efficiency curves of steady jet and pulsed jets. In the unsteady jet flow field, the high concentration region of hydrogen mass will appear intermittently downstream, which will cause the repeated process of the mixing efficiency enhanced-weakened-enhanced in the flow field. Compared with Case3, the turning point of the curve in Case2 lags behind, while Case4 has a relatively short distance of the wavy structure in the flow field, and through the fluctuation of its mixing efficiency curve, it is obviously different from the low-frequency jet cases.

Figure 10.

Comparison of mixing efficiencies between steady and pulsed jets with different frequencies.

The mixing efficiency of Case4 basically fluctuates above the steady jet curve, that is, the 50kHz pulsed jet has high mixing efficiency in the whole region. Pulsed jet can enhance the mixing of transverse jet flow field, 50kHz pulsed jet can improve the mixing efficiency almost the whole flow field, while low-frequency pulsed jet will cause great fluctuation of mixing efficiency in the flow field, which may be detrimental to the working process of the engine.

According to the expression of jet penetration depth, the penetration depths on different flow cross-sectional planes are calculated and drawn into Fig. 11. In the near-field region, Case4 has advantages over other cases in improving the penetration depth of the jet, but after the pulsation of Case2 and Case3 begin, Case4 loses this advantage. Downstream of the jet, the penetration depth of all pulsed jet cases begins to fluctuate around the steady curve.

Figure 11.

Comparison of penetration depths between steady and pulsed jets with different frequencies.