mme.modares.ac.ir
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Numerical study of a detonation wave structure in annular chamber
Mohammad Farahani
*, Mohammad Badrgoltapeh
Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
* P.O.B. 11155-1639 Tehran, Iran, [email protected]
A RTICLE I NFORMATION A BSTRACT
Original Research Paper Received 06 April 2016 Accepted 25 June 2016 Available Online 06 August 2016
Detonation engines are expected to be used as propulsion system in aerospace applications in the future.
Several types of detonation engines are currently under examination, including the rotating detonation engine (RDE). In this work, the feasibility study for design of a laboratory sample RDE which has an annular geometry with diameter of 76 mm has been performed. In this sample, hydrogen and standard air are separately injected into the combustion chamber of detonation engine. First, numerical studies are validated comparing the FLUENT results with the experimental ones. Then, the geometry and equivalence ratio of injection mixture are investigated parametrically. Considering the negligible variations of thermodynamics parameters in the radial direction of flow field to reduce the computational costs, also a 2D model is used for numerical simulations. Three different equivalence ratios were employed. Results show for the case with the equivalence ratio of 1.2, detonation speed, pressure, and temperature behind detonation front is more than the equivalence ratio of 0.8. Also, maximum detonation speed and pressure behind detonation take place in stoichiometric conditions. The parametric study of the chamber length effects was also conducted using a length 0.5 and 2 times of the main chamber. Because the chamber outflow is subsonic at some regions, chamber length change has a significant effect on the engine performance and flow field. The results point out that increasing the chamber length in low injection pressure and high injection pressure leads to increasing and decreasing the height of detonation front, respectively.
Keywords:
Rotating Detonation Engine
Rotating Detonation Combustion Modeling Geometry Design of RDE
2D simulation of RDE
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1Standing Detonation Engine (SDE)
2Pulse detonation engine (PDE)
3Deflagration To Detonation Transition (DDT)
4Rotating Detonation Engine (RDE)
5Continuous Detonation Engine (CDE)
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7 Computational Fluid Dynamics (CFD++)
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1 Richtmyer-Meshkov Instabilities (RMI)
2 Kelvin-Helmholtz Instabilities (KHI)
3 Half-Reaction Zone Length (HRL)
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4 Large-Eddy Simulation (LES)
5 Vorticity
6 Dissipation
7 Small-Scale Structures
8 Sub-Grid Scales (SGSs)
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Table1Comparison of one-dimensional detonation properties at different grid scales
(m/s) (mm) TStatic (K)
PStatic (bar)
0.5 × 1 1110
2904 18.01
0.25 × 0.5 1250
3271 20.29
0.125 × 0.25 1252
3276 20.32
0.0625 × 0.125 1255
3284 20.37
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Fig. 4 Different injection conditions based on the local combustion chamber pressure on inlet boundary
4 Detonation Wave
In je ct o r
InjectorIn je ct o r
Fuel / Oxidizer P0P0
P0
P
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wInjector
Wall Injector
Wall Detonation Wave Detonation Wave
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Pw P0
2) Subsonic Injection:
P0 > Pw Pcr
3) Sonic Injection:
Pw Pcr
F u el / O x id iz er
Fuel / OxidizerCombustion Products Outlet
75 (mm) Wall Changed to
Periodic Wall Changed to
Periodic
(H2 + Air) Inlet 95 (mm)
Exhaust
Outer wall
Exhaust
Inlet Inner wall
Outer wall Inner
wall
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Table 2 Different region propertise for the initial conditions (K) (bar)
1 3000 10
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Error = ±
Combustion Products Outlet
20 (mm)
Product @ 25 (bar) & 3000 (K)
Reactant @1 (bar) & 298 (K) Product @ 1(bar) & 298 (K)
(H2 + Air) Inlet 1 (mm)
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Fig.6Comparison of experimental [9] and numerical results for pressure variations at the outer side wall 15 mm from the inlet boundary
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7 Fig.8 Static pressure contour at different times
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Time (ms)
P re ss u re (M P a )
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Time (ms)
P re ss u re (M P a)
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0 1 2
3 Experimental Data [9]
Present Work (Air - H
2)
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Fig. 9 Detonation-shock combined wave
-
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Fig.11Velocity Vector
11 Fig. 12 Designed RDE geometry
12 RDE
- -11
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H + 0.5(O + 3.76N ) H O + (O ) + 0.5(3.76)N ) ( 16
= 1.2 :
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Table 3 Injection pressure and injected mixture properties in numerical simulation for various equivalence ratio
(kg/s)
(kg/s)
(bar)
1 0.39 65.64
1.4075 397.69
1.48143
0.8 1.4073
376.29 1.44105
1.2 1.4076
418.85 1.52029
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Table 4 Detonation wave parameters for different equivalence ratios (m/s)
TStatic (K) PStatic (bar)
1 1250
3271 20.29044
0.8 1132
2960 18.93272
1.2 1210
3232 19.53543
Fig.13 Static temperature contour for different lengths of chamber 13
5
Table 5 Detonation parameters for different chamber length
(mm) (mm)
(m/s) TStatic
(K) PStatic
(bar)
50.75 19.142
1168 3185 19.62631
101.5 19.741
1250 3271 20.29044
203 21.667
1420 3465 21.58263
.
0.8 1 . 1.2
1.2 0.8
. . .
0.5
. 2 .
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50.75 . 203
- 16
CDE k
DDT
) ( bar
PDE
RDC RDE
) ( K x
V y
k z
k
) kgm
-1s
-1(
) kgm
-3(
air (x, 0, t) = w C k
mix react ref 0
-17
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