Environmental Engineering Reference
In-Depth Information
Table 12-4. HAWT Test Rotor Configuration Data
Case
Rotor
diam.
Rated
power
Teeter
axis
angle
Hub
coning
angle
Tip
chord
Rotor
speed
Blade 1st
chordwise
frequency
Blade
gravity
moment
Ref.
D
P
d
3
q
c
t
N
w
c
M
g
(m)
(kW)
(deg)
(deg)
(m)
(rpm)
(cpm)
(kN-m)
A
28.0
200
-90
7
1.11
40.0
174
71
(a)
B
38.1
200
-90
7
0.46
40.0
160
62
"
C
38.1
150
-90
7
0.46
31.0
160
62
"
D
38.1
200
-90
7
0.61
40.0
164
69
"
E
38.1
150
-90
7
0.61
31.0
164
57
"
F
60.9
2,000
-90
9
0.86
35.0
146
739
(b)
G
30.6
100
0
3
1.03
34.0
171
91
(c)
H
39.1
100
-20
3
0.67
31.0
117
130
"
I
39.0
104
0
3
0.67
20.0
163
104
"
J
39.0
50
1
0 3
0.67
20.0
163
104
"
K
39.0
50
1
0 3
0.67
20.0
163
82
"
L
79.0
4,000
-30
6
1.16
30.0
125
1,112
(d)
M
91.4
2,500
0
0
1.44
17.5
108
3,254
(e)
1
Maximum allowable during test
(a) [Spera and Janetzke 1981, Birchenough 1981]
(b) [Spera and Janetzke 1981, Collins
et al.
1981, Spera
et al.
1979]
(c) [McDade and Pfanner 1985, Ensworth 1985]
(d) [Young and Hasbrouck 1983, Johnson and Young 1985]
(e) [Sullivan 1984, Boeing 1985]
the number of blades or the effect of turbulence generated by upwind turbines on fatigue load
spectra.
The test results from these 13 data cases are graphed in Figures 12-11(a) to (m), with
sketches of the individual blade planforms and control surfaces. This reference data base
contains almost a million measurements each of (1) wind speed at hub elevation, (2) cyclic
torque in the turbine shaft, calculated from the generator output power and rotor speed, (3)
cyclic flatwise (or flapwise) blade moment near the root, and (4) cyclic chordwise (or edge-
wise) blade moment at the same location. One sample of tower bending moment is also in-
cluded. The load cycles are all of Type I. Taken as a whole, these data are representative of
the fatigue load spectra that can be expected during long-term operation of HAWTs and (to a
certain extent) VAWTs, and can be used as a guide for preliminary design and testing.
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