Environmental Engineering Reference
In-Depth Information
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Experimental data for composite blade
ANSYS simulation with K= 0.3 W/(m.
o
C), h=6 W/(m
2
.
o
C)
ANSYS simulation with K= 0.3 W/(m.
o
C), h=7 W/(m
2
.
o
C)
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23
0
100
200
300
400
500
600
Time (sec)
Fig. 8.17
Validation of the computational model developed in ANSYS with the experiments
Fig. 8.18 Different heater
layouts. a Aligned square
layout. b Staggered square
layout. c Aligned circular
layout. d Staggered circular
layout
Aligned
Staggered
(a)
(b)
(c)
(d)
A uniform 3 mm glaze ice layer on the blade from the leading edge to 40 % of
the chord length is incorporated into the numerical model, as shown in Fig.
8.19
.
The ice layer covers all of the distributed resistors mounted on the blade. This
uniform ice thickness model is assumed for the purpose of optimizing the heater
layout. However, a nonuniform ice layer based on experimental field data is
needed for the purpose of investigating aerodynamic efficiency degradation and
calculating lift and drag coefficients for an icy airfoil, which is not the focus of this
chapter. The physical properties of the glaze ice layer and the composite blade
were carefully modeled in ANSYS, including the melting point, density as a
function of temperature, specific heat as a function of temperature, and thermal
