$B_M$	Mass Spalding number $[-]$
c	Progress variable $[-]$
d	Droplet diameter [m]
D	Mass diffusivity [m${}^2$ s${}^{-1}$]
L	Length scale [m]
P	Pressure [Pa]
$P/T$	Pilot-to-total fuel split [%]
$q^{″}$	Heat flux [W m${}^{-2}$]
$S_r$	Source of radiative energy [W m${}^{-3}$]
$S_h$	Sherwood number $[-]$
T	Temperature [K]
$We$	Weber number $[-]$
s	Curvilinear abscissa [m]
Y	Species mass fraction $[-]$
Z	Mixture fraction $[-]$
ACARE	Advisory Council for Aeronautics Research in Europe
BC	Boundary Condition
CAEP	Committee on Aviation Environmental Protection
CFD	Computational Fluid Dynamics
CHT	Conjugate Heat Transfer
CIAM	Central Institute of Aviation Motors
DES	Detached Eddy Simulation
DO	Discrete Ordinate
FAR	Fuel Air Ratio
FGM	Flamelet Generated Manifold
ICAO	International Civil Aviation Organization
LES	Large Eddy Simulation
NSE	Navier Stokes Equation
NEWAC	NEW Aero engine core Concepts
OPR	Overall Pressure Ratio
PDF	Probability Density Function
PERM	Partial Evaporation and Rapid Mixing
RANS	Reynolds Averaged Navier Stokes
RTE	Radiative Transfer Equation
SAFE	Source bAsed eFfusion modEl
SAS	Scale Adaptive Simulation
SRS	Scale-Resolving Simulation
TIT	Turbine Inlet Temperature
UDF	User Defined Function
$\alpha$	Inclination angle (streamwise direction) ${[}^{\circ }]$
$\omega$	Turbulence frequency [s${}^{-1}$]
$\mathsf{\Theta }$	Spanwise angle ${[}^{\circ }]$
$\psi$	Generic variable $[-]$
$\rho$	Density [kg m${}^{-3}$]
40	Referred to Plane 40 (combustor exit)
c	Progress variable
$eq$	Equilibrium
g	Gas phase
rad	Radiation
vK	von Karman
w	Wall