Environmental Engineering Reference
In-Depth Information
Symbol
ʲ
Thermal expansion coef
cient
ʲ
*
SST k-
ˉ
thermal expansion coef
cient
ʴ
ij
0fi
6
¼ j
1fi ¼ j
Kronecker delta
ʵ
Turbulent dissipation rate
ʵ
0
Ambient turbulent dissipation rate
c
eff
Effective intermittency
γ
M
Dilation dissipation
γ
y
ʳ
ap correction term
γ′
Conditional statement of effective intermittency
˃
Surface tension
˃
k
,
˃
ε
,
˃
ˉ
Turbulent Schmidt number
ʸ
Temperature in Reynolds stress model
ʼ
Dynamic viscosity
l
t
Turbulent viscosity
ˁ
Density of
fl
uid
ω
Turbulence speci
c dissipation
ω
0
Ambient turbulence speci
c dissipation
Subscripts
a
Air
b
Two-phase breakup water outlet
fl
ow
e
Exit
i
Inlet
i,
j, k
Coordinate direction/tenser index
m
Mean parameter
w
Water
Superscripts
T
Transpose
1 Introduction
Aluminum-based propellants are commonly used in solid rocket motors (SRM)
(Xiao and Amano
2006
) due to their high energy densities (Rapp
1968
). However,
the alumina (Al
2
O
3
) particles produced during aluminum propellant combustion
present performance issues. These particles
flow along the combustion chamber
to the nozzle in liquid form causing chemical and mechanical erosive damage.
This erosive behavior should be avoided in an SRM because it decreases the
ballistic performance (Thankre and Yang
2009
). Since particle size and trajectory
fl
Search WWH ::
Custom Search