Influence of Micro Jets on the Flow Development in the...
Transcript of Influence of Micro Jets on the Flow Development in the...
International Journal of Mechanical & Mechatronics Engineering IJMME-IJENS Vol:19 No:01 70
I J E N S IJENS February 2019IJENS © -IJMME-2828-191301
Abstract— In this paper, Computational fluid dynamics
method is used to simulate the supersonic flow. Convergent-
divergent (C-D) nozzle have been used with sudden expansion.
The base pressure controlled by using the microjets of 1 mm of
orifice diameter is arranged at ninety degrees at PCD 13 mm. The
Mach number is 1.87, and the area ratio of 3.24 was considered
for the present study. The L/D of the duct was used 10, and the
nozzle pressure ratio (NPR) considered for simulation was from
3, 5, 7, 9 and 11. The two-dimensional planar model has been
used using ANSYS commercial software. The total wall pressure
distribution and Mach number variation from the inlet to the
outlet was observed. From the results, it is found that the
microjets are capable of controlling the base pressure, the loss of
pressure and decreases in the drag. In the present study, the C-D
nozzle designed and modeled: K-ε standard wall function
turbulence model has been used and validated with the
commercial computational fluid dynamics (CFD).
Index Term— C-D nozzle, Wall Pressure; Flow Control; NPR;
CFD; Microjets.
I. INTRODUCTION
In engineering application, the sudden expansion of the flow
in supersonic regimes is significant and has applications in
many fluid flow problems. In rocket and jet engine test-cells
systems have been used to simulate the upper atmosphere flow
field; a jet discharging yields a low pressure which is very low
as compared to the atmospheric pressure. However, CFD
analysis has its advantage to simulate the flow field’s plays an
important role in current technologies of design optimization
by providing very accurate solutions for a given problem with
different commercially available tools. Recently, Khan et al.
identified the velocity and pressure effect in a suddenly
expanded converging-diverging (C-D) nozzle flow for area
ratio 6.25 [1], [2] and area ratio 3.24 [3] with and without the
presence of the micro-jets at the base using the CFD.
From literature, it is found that CFD simulation by different
available design and analysis tools have been used from the
last two decades. Some of them are highlighted here; the CD
nozzle used for convert pressure energy to kinetic energy in
order to yield thrust using CFD method in various performance
parameters [4]. CFD was used to optimize fluid flow in a
supersonic rocket nozzle at a various divergent angle of the
nozzle by using 2D axis-symmetric model [5]. The De-Laval
nozzles were used to convert the thermal and pressure energy
into kinetic energy using the CFD software ANSYS Fluent and
compared with theoretical results [6]. High-speed CD nozzle
has been modeled and optimized the flow after the throat at a
certain point using ANSYS FLUENT [7]. Numerical
simulation has been used to optimize the flow in a convergent-
divergent nozzle for Mach number M = 2.6 at nozzle exit using
the RANS equations with k-ω SST turbulent model [8]. CFD
simulation has been carried out to study the pressure and
velocity affects for different designed Mach numbers, area
ratios and length to diameter ratio of the CD nozzle [9]–[13].
Evaluating the optimum fineness ratio (ratio of length to
maximum diameter) of the human-powered submarine of
different shapes to reduce the drag force on the body using
CFD simulation [14]. Numerical simulation was carried out for
Box-wing configuration and simulated non-planar
configuration using ICEM CFD and ANSYS CFX solver [15].
Investigated the flow-field by a numerical approach using CFD
simulation to investigate the efficacy of the supersonic Mach
numbers due to the flow from the supersonic nozzle exhausted
in a larger circular duct [13].
From numerical simulation, the laminar flow in a sudden
augmented pipe subjected to a uniform suction speed has been
analyzed [16]. Different numerical methods have been used to
solve and account the viscous effects of the flow and compared
with the available results from the literature. It is concluded
that along the length of the duct with the progressive increase
in the values of blowing speed applied at the walls the vortices
generated near the step wall dwindles. Furthermore, separation
control using microjets has been examined in a canonical flow
such as a modified backward facing ramp [17] and for
aerospace applications for two-dimensional airfoils [18], [19].
Khan et al. [20]–[29] experimentally investigated the
mechanism to assess the performance of the control
mechanism by the small jets at various level of expansion to
regulate the base pressure in a suddenly expanded circular
ducts at moderate and high supersonic Mach numbers. The
result thus produced showed that the highest gain in the base
pressure by more than 100 percent for Mach number 2.58.
For C-D nozzle with sudden expansion, the variation in
mean velocity profiles along x-axis where the four microjets
are placed at the designed Mach number has been studied to
identify the effects of the control mechanism [30]. An
experimental investigation has been carried out to investigate
Sher Afghan Khan1, Abdul Aabid1, and C Ahamed Saleel2
1Department of Mechanical Engineering, Faculty of Engineering, International Islamic University Malaysia,
Kuala Lumpur, Malaysia 2Mechanical Engineering Dept., College of Engineering, King Khalid University, Kingdom of Saudi Arabia
Influence of Micro Jets on the Flow
Development in the Enlarged Duct at
Supersonic Mach number
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the control of base pressure with and without the control in the
form of the microjets with axi-symmetric suddenly expanded
duct in the supersonic regime [31]. Experiments work has been
conducted in order to investigate the base pressure variation
from an axisymmetric nozzle having an exit diameter of 10
mm and Area ratio of 4.84 [32], [33]. This investigation
focused attention on the outcome of the wind-tunnel tests
conducted to control the base pressure in the recirculation
region and also investigated the efficiency of the control
mechanism to manipulate the base pressure in a suddenly
expanded duct [34], [35]. The effects of microjets were
investigated in a sudden expansion of air for different area
ratio and L/D of the circular pipes, at subsonic and sonic flow
regimes by [36]. Investigated the airflow from CD axi-
symmetric nozzles expanded suddenly into the circular duct of
larger cross-sectional area than that of nozzle exit area,
focusing attention on the base pressure and the flow
development in the duct [37]–[47]. A technique for estimating
the efficiency of microjets in a flow which is exhausted into
the large duct from a CD nozzle has been investigated. In the
evaluation for low, medium and high Mach numbers, the
pressure distribution of the flow behind the nozzle exit is
computed, and the results indicate the presence of oblique
shock, Mach waves, and expansion fan when the shear layer is
exiting from the nozzle exit which depends upon the level of
expansion [48]–[50].
To control base pressure at the sudden expansion static as
well as the dynamic control cylinder has been used to regulate
the base flows. The effect of the control mechanism has been
identified when rotated clockwise inside the recirculation zone
at different locations at the base region to reduce the drag. The
study considered to control the base pressure for different
Mach number, area ratio, L/D, and NPR. The study shows the
effectiveness of the control mechanism to control the pressure
with sudden expansion for CD nozzle, and it also discussed the
effect of the low-cost base drag reduction technique [40], [51]–
[61].
The objective of this paper is to investigate the flow field in
a C-D nozzle. The parameters considered, in this investigation
are the L/D ratio of 10, and the NPR considered are 3, 5, 7, 9,
and 11 for an area ratio of 3.24. The flow-field is pressure and
Mach number. The 1 mm orifice diameter microjets have been
employed at the base of the nozzle to optimize the
effectiveness of the control and the influence of the microjets
on the flow development in the duct. The results have been
shown using contours and base pressure as well as pressure
plots for different NPR.
II. PROBLEM DEFINITION
Figure 1 illustrates the designed CD nozzle for Mach
number 1.87. Four microjets are used of 1mm of diameter and
located at the pitch circle diameter of 1.3 mm. This study aims
to analyze the pressure and Mach number flow for L/D 10 and
different NPR using 2D CFD simulation with and without
microjets. These microjets are operated at sonic Mach numbers
even though the stagnation pressure in the control chamber
was very high. To generate supersonic flow instead of circular
orifice we should have C-D shapes of the microjets.
Fig. 1. CD nozzle with enlarged duct
The procedure for the data analysis was followed as in Ref.
[17]. In this paper, the step height is 3 mm having area ratio as
2.56, and the level of expansion in the control tank is similar to
that of the storage tank. This research aims to study and
quantify the possibility of the flow regulation where small jets
are used as the blowing in the base area as the flow regulation
mechanism for restraining the base pressure.
The dimensions of the CD nozzle with suddenly expanded
duct are mentioned in table I. Table I
Dimension of CD nozzle
Mach Number 1.87
Inlet diameter (Di) 28.72
mm
Throat diameter (Dt) 8.648
mm
Exit diameter (De) 10 mm
Extended diameter (D) 18 mm
Convergent length
(Lc)
35 mm
Divergent length (Ld) 12.926
mm
Extended length (Le) 180 mm
Micro-jets diameter
(Dm)
1 mm
III. FINITE ELEMENT METHOD AND ANALYSIS
Figure 2(a) illustrates the finite element two-dimensional
planar model of CD nozzle and figure 2(b) illustrate closed of
finite element meshing. ANSYS Workbench has been used
and created a structural mesh, the number of elements has been
used high to create the fine mesh in a closed area at the edge of
the planar body. Total, 36,388 binary nodes, were generated
for the 2D planar model.
(a)
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(b)
Fig. 2: 2D planar fluid body (a) Finite Element Model (b)
Meshing.
A. Setup for Solution Initialization
Computations of the flow field inside the control volume were
done using RANS (Reynolds-Averaged Navier-Stokes)
equations with the k-ε standard turbulent model [62].
The most important settings that have been applied are;
• Solver: steady, absolute, 2D planar pressure-based
• Model: viscous, k-ε standard wall function, the
Energy equation
• Fluid: air, ideal gas, viscosity by Sutherland law,
three coefficient methods
• Boundary conditions: inlet, pressure inlet (pa); outlet,
pressure outlet; wall, wall
• Solution method: Pressure (standard); density,
momentum, turbulence kinetic energy, turbulence
dissipation rate, energy (second-order upwind)
• Solution initialization: standard, from inlet •
Reference value: inlet (solid surface body)
IV. RESULTS AND DISCUSSION
A. Validation of Finite Element Model
In order to validate the finite element (FE) results, the
configuration considered as shown in figure 1 of Khan et al.,
(2003) is selected. Khan et al. (2003) conducted experiments at
Mach 1.87 for area ratio 3.24 for NPR from 3 to 11. The
transducer used for the data acquisition take three hundred
fifty samples per second and takes the average of all the data
and then display on the monitor and at the same times, it writes
on the hard disk. By comparing the experimental results
obtained by Khan et al., (2003) and the present FE results, the
agreement is presented in figure 3 for the different cases. Fig.
3 shows the matching of the wall pressure and the flow field in
the duct for various NPR for different L/D ratios of the present
study. The results obtained by the simulated are within the
acceptable limit.
(a)
(b)
(c)
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(d)
(e)
(f)
Fig. 3. Wall pressure distribution for different NPR and L/D
B. Pressure Flow
Fig. 3 to 7 illustrate the pressure flow from the inlet to the
outlet without control. In this case, the optimized pressure is in
Pascal and wall is considered from the inlet to the outlet of the
C-D nozzle. Fig. 4 to 8 show the wall pressure plot and
contour which indicate that the pressure variation has a sudden
change when the level of expansion NPR increases. Also, it is
seen that the length of the recirculation zone at the corner of
the C-D nozzle is high which results in low pressure at the
base area and gives more drag. Therefore, to control base flow
and hence reduce the base drag in sudden expansion region we
have placed the microjets which will break the vortex at the
base, and that will result in manipulation of the recirculation
zone. This process will increase the base pressure and will also
result in forwarding movement of the reattachment point of the
flow which as shown in fig. 9 to 13. When micro jets
employed at the base region of the sudden expansion the wall
pressure with and without the control remains the same.
Moreover, for NPR 3 the microjets behave differently due to
the low-pressure inlet and the jets are highly over expanded.
With further increase in the NPR, the level of overexpansion
will go down, and the control effectiveness will improve.
(a)
(b)
Fig. 4. NPR 3 without microjets control (a) Contours (b) Plot
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(a)
(b)
Fig. 5. NPR 5 without microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 6. NPR 7 without microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 7. NPR 9 without microjets control (a) Contours (b) Plot
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(a)
(b)
Fig. 8. NPR 11 without microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 9. NPR 3 with microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 10. NPR 5 with microjets control (a) Contours (b) Plot
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(a)
(b)
Fig. 11. NPR 7 with microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 12. NPR 9 with microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 13. NPR 11 with micro jets control (a) Contours (b) Plot
C. Mach Number
The effect of Mach number also considered ascertaining the
losses incurred given the wavy nature of the flow field. In this
case, the Mach number is increasing at the exit of the CD
nozzle whenever jets are under-expanded, and for
overexpanded there will be an expansion fan or oblique shock
wave which will result in increase or decrease of Mach
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number. Fig. 14 to 18 shows the Mach number variation
without micro jets control. The contours and plots have been
considered to optimize the flow variables. From the Figs. 13
to 17, show the recirculation is very high at the base corner.
Moreover, to control this enhanced recirculation zone the
microjets becomes active, and suction becomes very low this
means that the control has resulted in a decrease of the drag
and the downward direction in the downstream the flow at the
exit of the nozzle which may result in increases the Mach
Number which is shown in fig. 19 to 23. For low-pressure
variation, the Mach number varies differently, and at the exit
of the nozzle, the value of the Mach number is low for other
cases the value will become high.
(a)
(b)
Fig. 14. NPR 3 without microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 15. NPR 5 without microjets control (a) Contours (b) Plot
(a)
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(b)
Fig. 16. NPR 7 without microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 17. NPR 9 without microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 18. NPR 11 without microjets control (a) Contours (b)
Plot
(a)
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(b)
Fig. 19. NPR 3 with microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 20. NPR 5 with microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 21. NPR 7 with microjets control (a) Contours (b) Plot
(a)
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(b)
Fig. 22. NPR 9 with microjets control (a) Contours (b) Plot
(a)
(b)
Fig. 23. NPR 11 with microjets control (a) Contours (b) Plot
D. Flow Circulation at Base Region
Figs. 24 to 25 indicate the flow field in the re-circulation zone
with and without control. In the absence of control, there is a
re-circulation zone seen creating a low-pressure region.
However, when the control is employed at the base, it can
break the dominant vortex present in the base region and able
to increase the base pressure.
Fig. 24. Without Microjet Control
Fig. 25. With Microjet Control
V. CONCLUSIONS:
Based on the above discussions we may draw the following
conclusions:
The base pressure flow field and the Mach number
have been considered to optimize the solution using
CFD simulation.
After designing the nozzle for a specific Mach
number, the nozzles were fabricated. After fabrication
of the nozzle, the nozzle was calibrated. Finally, the
calibrated Mach number is used for simulations for
different NPR and L/D ratio of 10 for the area ratio of
3.24.
The effect of micro-jets was found to be useful for a
given level of expansion and a fixed level of inertia.
From the above results, it is concluded that total
pressure varying from the inlet to the outlet and value
of total pressure is high for NPR 11.
As pressure decreases due to the formation of the
expansion fan at the nozzle exit, the velocity will also
increase, and the simulation results proved that the
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pressure is low by considering the total wall pressure
flow and velocity is high by monitoring the Mach
number at the exit.
Results indicate the flow field in the re-circulation
zone with and without control. In the absence of
control, there is a recirculation zone seen creating a
low-pressure region. However, when the control is
employed at the base, it can break the dominant
vortex present in the base region and able to increase
the base pressure.
The validated results obtained through simulation as
well as experiments will be handy during the initial
design stage of the aerospace vehicle.
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