Numerical Simulation of Performance of an Axial Turbine ... · wkh remhfwlyh lw zdv frqvwuxfwhg d...
Transcript of Numerical Simulation of Performance of an Axial Turbine ... · wkh remhfwlyh lw zdv frqvwuxfwhg d...
LIST OF SYMBOLS
H: Total enthalpyS: Scalar measure of the deformation tensorT: TemperatureT2: Temperature at exit of staged: Distance from the wallfv1, fv2, fw: Empirical functions in the turbulence modelkK: Constant in the turbulence modelp: Pressurest: Timeu: Velocity component in a Cartesian systemx: Cartesian coordinateg,r,S�˜
: Density
ij: Shear stress tensor
i, j, k
in, out : Inlet and exit conditions0
INTRODUCTION
In the past, the experimental method was the single tool
-ance of computational techniques in the last 40 years, another
-
at the design point is around ±2%, if one takes into account uncertainty in the numerical methods, models, geometry,
Numerical Simulation of Performance of an Axial Turbine First StageVinícius Guimarães Monteiro1,*, Edson Luiz Zaparoli1, Cláudia Regina de Andrade1, Rosiane Cristina de Lima2
1
2
Abstract: T is work s pr s nt d t rst st g p rfor n t d sign nd off d sign op r ting points of n xi tur in , wit two st g s using nu ri si u tion xp ri nt t ods of pr di ting t p rfor n of xi tur in is ost nd ti onsu ing o p r d to t o put tion uid d n i s ppro T r for , o put tion t ni u s w r dopt d to d t r in t st g p rfor n T is stud n d t rst st g p rfor n of n
xi ow tur in , using o put tion too for si u ting t st d st t two t r di nsion vis ous ow o put tion uid d n i s softw r w s us d to so v t r ns u tions wit t sp rt r s tur u n od T o put tion uid d n i s r su ts w r o p r d wit t os o t in d fro t n in oss od
od T o p risons v n ondu t d to provid pr t st p rfor n for t tur in rst st g
Keywords: xi Tur in s, s Tur in s, o put tion uid n i s, u ri Si u tion, rfor n
175J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
Computational techniques are less costly and time-consuming if compared to the experimental approach to predict the
Dorney (2003) conducted a pretest performance for a
was to quantify the performance of the turbine at off- design
-tions were performed using a three-dimensional unsteady
uses a combination of the one-dimensional equations of
and they were used to help determining the locations of the
-
design and off-design performances of the 3D computational results are consistent with the mean line analysis used in the
-
losses than predicted by the mean line loss correlations and
the 3D computational results yield good agreement with the -
performance must be done at the beginning of an engine
satisfy all the operation requirements (design and off-design
Despite of 2D CFD approach limitations, it is important to
compared with the mean line loss model code ones, which
hub to tip of stator blade and rotor blade in the region near
parameters calculated by the 3D CFD simulations was made against mean line loss model code results generated by the
COMPUTATIONAL METHODOLOGY
Conservation equations
t
+ = 0x
ujj
(2)
uit xj
xjijxi
u
p
i uj
ui uj
Ht xj
u
p
Hj
uiui i j i jt
u Hj
xj
Tx
kj
t
176 J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
TURBULENCE MODEL
blades (Pecnik t
-
of the Spalart-Allmaras turbulence model are expressed by
t = vt , = v fv1vt �˜
v +Uj = cb1 v - cw1 fwj
�˜ 2�˜�˜�˜
�˜ �˜
�˜
�˜
v
vk
�˜
dv
+ (v + v) +k
1 k k
cb2 v v
b1 b2 v1 = 2 3
k ² cw1 =cb1 +
(1 + cb2), cw2 = 0,3, cw3 = 2, k = 0,41
fv1 = fv 2 = 1 - fw = gX 3
X 3+ c3v1
1 + c6w3
g6 + c6w3
X
1 + X fv1
16
X = g = r + cw2 (r6 - r),
Sk 2d
2r =v�˜ v�˜�˜
,v
S = S + S = 2 ij ijk 2d 2
fv2 ,v�˜ �˜ (10)
The tensor ij=1 i
2j
j i is the rotation tensor and d
is the distance from t
BOUNDARY CONDITIONS
t t
conditions to the absolute reference frame were applied to the
computational cost, due to the numbers of blade rows neces-
reason, it was chosen the mixing plane approach in the stage
The boundary conditions used in the inlet and outlet of 2D
Total pressure inletTotal temperature inlet 1,100 K
Static pressure outletTurbulent intensity inlet
The walls for 2D and 3D approaches are adiabatic and
+ are smaller than six for the
of the wall is applied appropriately to the turbulent boundary layer, when
Numerical Simulation of Performance of an Axial Turbine First Stage
177J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
NUMERICAL METHODS
The 2D approach was simulated by ANSYS Fluent
is coupled, implicit, with a time marching to reach the steady state condition, and taking into account the turbulence effects
The 3D approach was simulated by ANSYS CFX soft-
CFX software for the 3D simulation, because the software
the turbulence effects by Spalart-Allmaras one-equation
The algebraic multigrid was employed to accelerate the
MESH GENERATION
The mesh was constructed for two sub-domains, one for
In the 2D model, the mesh is composed by quadrilaterals elements near to the blade region, in order to capture high
-
-
Figure 1 represents the mesh of all computational domains
The mesh constructed in the 3D model is composed by
made in regions where there are high gradients normal to the
MEAN LINE LOSS MODEL CODE The mean line loss model code uses a combination of the one-dimensional equations of motion in the mean line and
t
from hub to tip in regions near the leading and trailing edges
analysis used by the manufacturer in the conceptual design of
t
178 J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
The performance maps constructed by CFD simulation
The loss model is established by means of applying boundary layer theories, basic thermodynamic equations, and
-
instance, attached blade boundary layers, the loss mechanisms
the loss mechanisms are still not clearly understood and
edge loss ( Te), tip leakage loss ( Tip), end-wall boundary layer loss ( b), shock loss ( s o k p
;
p Te Tip Eb
i
shock
HH T2
PERFORMANCE MAP
performance maps were constructed, which are the most
et
t), pressure ratio (rp orr), and corrected speed ( orr
(13)Hinin out
outt
HH H
p0 inprp0 out
(14)
mcorrm T0 inT0 in
TN
0Ncorr
in
RESULTS AND DISCUSSION
The
and rotor blades in the 2D simulation, which imply that the law of
It will be presented, at the design point operation, the
of these parameters calculated by 3D CFD approach was
The mean line analysis represents a good comparison tool
can be attributed to the fact that the design data do not take
Numerical Simulation of Performance of an Axial Turbine First Stage
179J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
distribution along the blade span, as mentioned by Tomita and
The boundary layer effects, in the hub and tip of the blade, are
Table 2 presents a comparison of design data against 2D
Descriptions Design data
2D CFD results
Difference (%)
3D CFD results
Difference (%)
- -
Pressure ratio
The difference between CFD results and design data is mainly due to one-dimensional characteristic of the mean
Similar conclusion can be obtained when comparing 2D and 3D
-
by empirical correlations (Kacker-Okapuu loss model), which
et
Leading edge
Trailing edge
Leading edge
Trailing edge
180 J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
suction side of the rotor blade, which reduces the pressure
The present study also focused on the performance maps
but 3D CFD results are in better agreement with Denton loss
et
Numerical Simulation of Performance of an Axial Turbine First Stage
Leading edge
Trailing edge
Leading edge
Trailing edge
181J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
ratios, which produce chocking conditions at some point in
Chocking conditions happen when the pressure ratio is
CONCLUSIONS
-
concludes that the 3D CFD results are consistent with mean line
by the CFD simulation and mean line loss model using Denton
results are in better agreement with Denton loss model when
et
182 J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
-
-ison is made against mean line loss model code, is the large
ACKNOWLEDGMENTS
The authors thank e So u es e nergi (VSE) for the
REFERENCES
et
-
-
-
et
et Secondary Flow of a Transonic Turbine Stage Using
et
-
et
Numerical Simulation of Performance of an Axial Turbine First Stage
183J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012
-
-
et
et
184 J. Aerosp. Technol. Manag., São José dos Campos, Vol.4, No 2, pp. 175-184, Apr.-Jun., 2012