MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE...

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0 DOE/NASA/0058-79/1 NASA CR-159494 MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ANALYSIS General Electric Company Space Division February 1979 Prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Lewis Research Center Under Contract NAS 3-20058 1. MAY 1980 r 'J3fS MCDGtL RESEARCH & t-ME T. LOUIS for U.S. DEPARTMENT OF ENERGY Office of Energy Technology Division of Distributed Solar Technology ,i8O- 737 https://ntrs.nasa.gov/search.jsp?R=19800012380 2018-07-14T12:17:34+00:00Z

Transcript of MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE...

Page 1: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

0 DOE/NASA/0058-79/1 NASA CR-159494

MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ANALYSIS

General Electric Company Space Division

February 1979

Prepared for

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Lewis Research Center Under Contract NAS 3-20058

1. MAY 1980 r 'J3fS

MCDGtL RESEARCH & t-ME

T. LOUIS

for U.S. DEPARTMENT OF ENERGY Office of Energy Technology Division of Distributed Solar Technology

,i8O- 737

https://ntrs.nasa.gov/search.jsp?R=19800012380 2018-07-14T12:17:34+00:00Z

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NOTICE

This report was prepared as an account of work sponsored by an agency of

the United States Government. Neither the United States nor any agency

thereof, nor any of their employees, makes any warranty, expressed or

implied, or assumes any legal liability or responsibility for any third

party's use or the results of such use of any information, apparatus,

product, or process disclosed in this report, or represents its use by

such third party would not infringe privately owned rights.

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MOD 1 WIND TURBINE GENERATOR DOE/NASA/0058-79/1 NASA CR-159494

FAILURE MODES AND EFFECTS ANALYSIS

General Electric Company Space Division Advanced Energy Systems Philadelphia, Pennsylvania 19101

February 1979

Prepared for

National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 Under Contract NAS 3-20058

For U. S. DEPARTMENT OF ENERGY Office of Energy Technology Division of Distributed Solar Technology Washington, D.C. 20545

Under Interagency Agreement EX-77-A-29-1010

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TABLE OF CONTENTS

SECTION PAGE

Introduction Task Approach Summary & Conclusions ....................iv Rotor Blade ........................ 1 YawSubsystem ........................ 4

Yaw Structure ..................... 4 Yaw Drive ......................... 5 Yaw Hydraulics .................... 7

Drive Train ......................... 8 Rotor Hub ......................... 12 Pitch Change Mechanism ................... 14

PCM Hydraulics ...................... 17 Power Ceneratjon ....................... 24 Nacelle - Fairing ......................... 31 Nacelle - Bedplate ....................... 32 Controls ........................... 33

CRU ............................. NMU .......................... 36 GMU .......................... 47

Tower ........................... 52 Structure .......................... 52 Lift Device ....................... 53

Appendix A - Blade

Unbalanced Loads after Blade Separation ...... . A-i Interface Ring Flange ........... • • • A-2 Test Program ..................... A-6 Quality Program ......... ... ....... . A-b

Appendix B - Rotor Overs peed ................. B-i FIGURES

1 FMEA System Diagram V 2

. MOD-i Blade vi

.3 Yaw Motor/Drive vii 4. Yaw Hydraulics viii 5 . Drive Train . . . . ix 6 Pitch Change Mechanism . x 7 . PCM Hydraulic Package . xi 8 . Power Generation FMEA Diagram . xii 8a . Trip Circuits . . Xiii 8b FNEA Diagram/Drawing CrOss Reference xiv 9 Control Subsystem xv 9a Control Subsystem (cont.) xvi

10 Emergency Shutdown Redundancy xvii

(i)

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FAILURE MODES AND EFFECTS ANALYSIS

Introduction

The following figures and tables present the results of a Failure Modes and

Effects Analysis (FMEA) of the Mod 1 Wind Turbine Generator. This analysis

was of limited scope, in accordance with Statement of Work NS3-26058, and was

directed primarily at identifying those critical failure modes that would be

hazardous to life or would result in major damage to the system. As a result,

the analysis was conducted from the "top down", minimizing the extent of an-'

alysis that would lead to trivial conclusions, had the analysis been approached

from the "bottom up". For example, a component-by-component analysis of the

lubrication system was not pursued, once it had been established that all lubri-

cation system failures lead to the same, non-critical conclusion.

Evaluation Criteria

The criteria used for evaluation of the system is that none of the following

injuries or damage shall occur because of a single failure or a single failure

following an undetected failure of the wind turbine system.

Category I: Failures which would result in death or serious injury to the

operator or general public.

Category II: Failures which would result in major or significant damage to

the wind turbine system, extended outage, or damage to the

connected utility.

All other failures are Category III. The failure categories are listed under

Column 9 in the attached tables.

(ii)

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Task Approach

Figure 1 illustrates how the Mod 1 Wind Turbine Generator system was broken down

for analysis. This organization corresponds roughly to the drawing system,

defined by Drawing Tree 298E470. Since subsystem descriptions are beyond the

scope of this report, reference should be made to the drawings that are identi -

fied on the Drawing Tree, should further details be required. Figures 2 through

10 provide an overview of each subsystem, with circled numbers corresponding to

principal line items in the accompanying tables. Figures 8, 9 and 10 are sim-

plified diagrams to further break down the Power Generation and Controls subsystems.

Each subsystem was approached from the top down, and broken down to successive

lower levels where it appeared that the criticality of the failure mode warranted

more detailed analysis. The attached tables, pages 1 through 55, were prepared

as worksheets through several stages of review, including review by qualified

GE specialists outside of the Mod 1 program and two reviews by knowledgeable'

NASA LeRC personnel. These summary tables were supplemented by analyses on

topics of special interest that are included as appendices to this report

covering:

• Unbalance Loads after Blade Separation

• Blade Interface Ring Flange Stress Analysis

• Blade Test Program

• Blade Quality Program

• Rotor Overspeed

(iii)

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Summary and Conclusions

The results of this study have been evaluated and the failure evaluation criteria

have been met for all Category I failures, except for the blade

and its attachment structure. Should a blade separate, as shown in Appendix A.

no additional failures would propagate. Also, the probability of a blade separ-

ation is acceptably small based on the other information presented in the Appendices,

i.e., the analysis of the interface ring flange, the design verifications to be

achieved by the test program (especially the 1.7.4 tests of fatigue strength of

welds), the inspections and checks of the quality program, and the redun-

dancy built into the overspeed shutdown circuits.

A few Category II failures are-also possible. These mainly involve conserva-

tively designed items such as shafting, bearings, and gears where the possibility

of failure, or premature failure, is acceptably small and it is not practical

to comletely avoid such failures. These items are discussed in more detail

in the tables.

Some minor changes have been identified as a result of this study and are

being incorporated. They are

o Pitch jam circuit redesigned to be fail-safe

o Overspeed reset redesigned to mechanically latch after power

failure

o Software revised to check sensors in their non-active state

o Specific inspection points identified for checks during periodic

maintenance

It may be necessary to incorporate additional changes later, if, for example,

additional Category I or II failure modes are identified during the test and

field check-out phases.

(iv)

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POWER GENERATION FMEA

FMEA DIAGRAM/DRAWING CROSS REFERENCE

() BLUE RIDGE ELECTRIC MEMBERSHIP CORPORATION

TRANSFORMER ASM 273A6418

AUX SUPPLY 273A6509 (PART)

MAIN BREAKER 273A6509 (PART)

SLIP RING 273A6519

GENERATOR 273A6429

jJ EXCITATION 273A6510 (REGUL.PART)

(13 STABILIZER 265A7O87

RELAYING 273A6510 (PART)

() SYNC 273A6510 (PART)

MOTOR CONTROL 273A6431

GND. C.P. 848E893

8 NAC. C.B. 132D6390

103 b BATTERY ASM 273A6432

WARN LAMP 273A6690

LIFT REEL 132D6046

(13) CONTROL ENCLOSURE 273A6507

J TRIP CIRCUIT RELAYS ONE-LINE DIAGRAM 298E475 REV. 3

(xiv)

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Page 49: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

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Page 50: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

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Page 61: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

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APPENDIX A - BLADE

Unbalance Loads after Blade Separation

Interface Ring Flange

Test Program

Quality Program

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I-i UNBALANCED LOADS AFTER BLADE SEPARATION

A loads analysis was performed to determine the loads on the major

items of structure resulting from the loss of a blade. These

loads are presented on Table I-i. For comparison purposes, the

maximum infrequent loading condition of emergency feather - 15%

overspeed is presented. Effects on major items are:

The remaining blade has loads imposed which are within its capacity

and should suffer no damage.

The blade retention bearing in the hub also will be subjected to

loads which are within its capacity and will suffer no degradation.

The hub bearing on the bedplate side will be subjected to loads

which are substantially higher than the emergency feather condition.

The bearing has the capacity to carry these loads for the few cycles

they will be imposed-with a small reduction in life.

The bedplate will experience local yielding but no failure due to loads

somewhat in excess of design values.

The yaw bearing will be subjected to bending moments which approach

the maximum moment capability of the bearing. For the few cycles this

loading occurs, there should be no damage to the rollers or races.

The yaw brake, however,will slip due to the high yawing moment.

The tower base will experience overturning bending moments approaching

50 x 10 6 ft-lbs. This will result in local yielding of some of the

tower secondary members; however, the 4 corner legs have the inherent

stability in buckling and as a column to carry the higher loads.

A-I

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1-2 BLADE INTERFACE RING FLANGE

A three-dimensional finite element stress was performed for the WTG

blade ring adapter (Boeing DWG #276-10509, Rev. B, 5/11/78, trans-

mitted via Datafax). It was performed to verify the design and

analysis submitted by Boeing.

The ring adapter was analyzed using the latest worst case loads

for both fatigue conditions and emergency feather conditions. The

equivalent axial load at the blade attachment section was 1,404,000

pounds (.7,152 psi) for the fatigue case, and 4,379,130 pounds

(22,310 psi) for the emergency feather case. The bolt preload was

given as 110,340 pounds (-31,022 psi).

RESULTS

As expected, the peak stresses in each case occurred at the root of

the elliptical transition section on the outer surface of the ring,

immediately adjacent to the bolt head location. For the fatigue

case, the peak principal tensile (cyclic) stress was found to be

20,200 psi. For the emergency feather case, the peak principal ten-

sile stress was found to be 5G,aOC psi. The margins of safety were

found to be +.416 and +.26, respectively. Also, the preload applied

by the attachment bolts was not exceeded.

ALLOWABLE STRESSES

The allowable stresses in the ring adapter material are given as

MAXFATIGUE = 28,600 psi IRef: Blade Spec. 273A6684]

MAXFEATHER = 63,000 psi

A-2

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MARGINS OF SAFETY

The margins of safety were determined using the peak stresses ob-

tained from the finite element run.

For the fatigue case: M.S. = 28,600 - 1 = .42 20,200

For the emergency feather case:M.S. = 63,000 - 1 =+.,2& 50,000

7.M7T VCT

A sketch showing the modelling approach is presented on Figure 1-2.

The stress distribution within the WTG blade ring adapter was determined by using

the finite element method, due to the non-uniform geometry of the ring cross-section.

The SAP V finite element computer program was used for the actual numerical deter-

mination. This code was developed at the University of California, Berkeley, and

is well documented and accepted throughout the technical community. Using the

initial geometry of Figure 1-2, a three-dimensional finite element model was

developed for the 1/112 section. This model consisted of 765 elements and 1185

nodes.

A-3

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Table I-I DYNAMIC & GRAVITY LOADS

Two Blades One Blade LOAD 50 MPH 40.25 RPM REV F BLADE 35 MPH 35 RPM REV E BLADE

LBS FOR SHEAR 'T-LBS FOR MOMENT MEAN CYCLIC (+) MEAN CYCLIC(+)

V 396,130 7,518 293,050 26,138 BLADE VY -25,435 18,956 -12,830 19,434 RET BRNG V 65,021 22,400 31,943 12,154 (BLADE M 5,968 17,769 8,399 16,195 SIDE)* M -3,107,330 1,021,300 -1,485,420 523,030

Mz -1,043,770 792,160 -59,430 733,800

V 396,130 7,518 293,050 26,138 VY -2,576 20,684 -5,884 19,693

BLADE V 69,130 23,843 32,522 12,810 RET BRNG M 5,968 17,769 8,399 16,195 (HUB M 3,207,870 1,126,200 -1,556,400 670,340 SIDE) M 10,940 869,910 -141,498 604,410

V -52 66,225 276,610 833,230 HUB BRNG V 35 86,466 6,846 69,698 (HUB V

SIDE) MZ-2,359 18,680 -13,432 10,363

106 606,630 -50,535 266,490 2,639 2,339,700 -3,187,200 769,480

Mz 66,386 184,210 -194,540 628,260

V -91,795 13,970 -66,665 52,678 V, -5,286 21,627 -4,333 156,720

HUB BRNG V -2,359 18,680 -13,432 10,363 (B/P SIDE Mx 82,336 507,490 -3,964 2,167,700 SIDE)** M 1,311,000 1,051,600 749,170 1,933,900

M 66,386 184,210 -194,540 628,260

YAW BRNG** V -339,830 17,162 -318,650 219,810 VX 18,220 60,879 -8,156 268,110 V -6,105 34,807 -13,586 57,064 Mx -5,369 636,680 57,842 5,285,900

842,030 947,600 103,970 2,210,700 M -35,132 454,260 -326,310 1,351,600

V -680,180 22,181 -662,290 382,840 V

ITOWER V-23,166 -6,779

80,510 45,747

-1,227 348,320

BASE**71,981 -9,793

M M

-4,539 807,110 143,550 6,073,900 1,168,500 5,539,300 2,305,400 5,279,500

Mz -3,149,500 10,766,000 -797,300 47,697,000

*Ref. to blade angle @ 3/4 +Blade coord (rotating) **Tower coord (stationary)

3LE

A-4 ,

\ TOWER /2

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Figure 12. Model Geometry and Coordinate System

A-5

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1-3 BLADE TEST PROGRAM - 1.

Three areas of testing have been planned for the Mod--1 blade. To

verify design assumptions or to demonstrate specification compliance:

1) ENGINEERING DEVELOPMENT TESTS

Tests performed on sub-element structures to obtain early mdi-

cation of design adequacy.

2) BLADE DEVELOPMENT TESTS

Tests performed on full-scale portions of the blade to ascertain

structural adequacy. In most cases, the test data from these

tests will be available after the final design is complete.

3) BLADE TESTS

Tests which will be performed on the completed blade to determine

dynamic characteristics or basic property data such as elastic

axis location, static moment, chordwise c.g. locations, and

stress and deflection data vs. load.

A summary of the tests in each of the above categories follows in

Table 1-3, 1-4 and 1-5.

A-6

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Page 84: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

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Page 85: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

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1-4 QUALITY PROGRAM

The blade Quality Program is summarized on Table 1-6. The trailing

edge portion of the blade is, at this writing, just completing the

development phase. Consequently, the Quality Control plans for it

are preliminary and subject to change.

A-lO V

Page 87: MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... · MOD 1 WIND TURBINE GENERATOR FAILURE MODES AND EFFECTS ... results of a Failure Modes and Effects Analysis (FMEA) of

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A-12

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APPENDIX B

ROTOR OVERSPEED

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ROTOR OVERSPEED

One of the more serious failure scenarios on a wind turbine is rotor overspeed. If periitted to "run-away", blade separation due. to large rotor centrifugal stress is a probale final result. The MOD-1 pitch control system is the mechanism whereby over-speed is controlled, with redundant stored energy and redundant deadman control valve

elements built into the system.

The maximum rotational speed of the rotor is a function of rotor inertia, accelerating torque due to loss of load and wind increases, a time delay from the start of accel-eration to initiation of blade pitch motion towards feather, and the torque rate of change with time, which is a function of pitch rate. In order to simplify the following analysis, step changes in wind velocity over the entire rotor disc were assumed, a con-dition not reasonably occurring in nature. Acceptable response to these step inputs will indicate better than acceptable response to realistic wind perturbations.

Values utilized in the analysis are:

Inertia of rotating system 2.1 x 106 lb-ft-sec2 Rated torque (2160 KW, 34.7 RPM) 4.4 x 105 ft-lb (1007.) Nominal control delay 0.2 sec Maximum blade rate 14 deg/sec Maximum torque rate 1507. /sec at 14 deg/sec

Wind steps considered and their torque effects are:

1.0 to 1.4 normalized velocity 1007. to 235% normalized torque 1.0 to 1.8 normalized velocity = 100°!. to 376% normalized torque

The torque increase does not follow a wind velocity cubic due to assuming initial con-ditions just at rated wind velocity near the peak power coefficient value. Any wind increase thus is effective at a reduced power or torque coefficient value. A linear torque-pitch relationship, no compensation for torque change with rotor speed, and no losses are assumed. The combined effect of these assumptions is believed to balance out as the second and third assumptions are conservative, while the first is not conser-vative.

Four scenarios, as follows, describe a range of increasingly severe accelerating torque conditions. Loss of load is considered to be a "normal" design event as the main circuit breaker can be tripped open due to a variety of electrical anomolies.

B-i

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Case 1 loss of 40% load No Cust

Case 2 loss of 1007. load No Cust

Case 3 loss of 1007..load 1.4 Gust

Case 4 loss of 1007. load 1.8 Gust

Response was computed on, the basis of a normal control system de-energizat ion of

the feather solenoid valves, permitting the fluid in the feather accumulators to discharge into the blade actuators towards feather through a programmed flow valve.

This valve has the characteristics and adjustability shown in Figure 1.

A no program for the flow valve has been selected with the dual goals of limit-ing peak speed in a significant upgust wind and also limiting blade loading in de-celerating torque conditions. The initial rate is at a blade equivalent of 14 deg/sec for 0.8 seconds, followed by a linear decrease to 4.4 deg/sec over the next 1.6 seconds, then maintained at 4.4 deg/sec. Starting from 0.0 degrees, this schedule reaches 90.0-.degrees feather in 17 seconds,with25 degrees change in the first 2.5 seconds. The flow program is field modifiable for rate change, final rate, and time at maximum rate.

Results, with 0.2 second nominal control delay and activation of the feather system due to either high wind, breaker opening, large yaw error, or vibration are as

follows:

Case 3. 2 3 4

Max. spd 7. .77 3.08 10.71 22.7

over 1007.

Time at max .47 .87 3,25 1,72

sec

Hybrid runs of cases analogous to the above cases 2 and 4 were made during the course of system design simulation. The control algorithm was to shift to speed control at rated speed reference . with no delay. On 100% load loss, 2.27. overspeed

occurred and with a 1.8 gust, 11% overspeed occurred. Pitch angle response started at the maximum rate near 14 deg/sec and maintained a higher rate than the programmed

valve, due to. -the speed control loop gain. These two cases are shown in Figures 2 and3. . . .

If a control system failure prevents initiation of the feather system at rated rotor speed, software and hardware switch actuation of the feather valves are provided as backup. Present settings for the software and hardware overspeed switches are 57. and 107. respectively. These speeds are additive to the response values and in the case of the realistic 1.4 wind gust, result 16.15.7 to 20.77. overspeed. Resetting of. these switches to 3 and 6% respectively is recommended to reduce maximum speed, providiAg adequate separation from startup variation, overshoot and switch tolerance bands can be maintained. The lower settings would result in 13.7 or 16.7% overspeed for software and hardware initiated feather with the nominal valve program and a Case 3 scenario.

B-2

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To summarize, maximum rotor ovcrspccd is expected to be less than 57. (3.08 7. calculated) on lo';s of load and less than 20% on loss of load plus a sustained 1.4 upgust plus a primary control input or output failure requiring use of the hardware backup ovcrspccd circuit. These values are acceptable for a rotor and blade system with positive stress margin at a rotor speed above 20'/. overspeed. The MOD-1 blade has positive margin near 207. ovcrspecd.

Figure B-I

rrogrammed Flow Valve Characteristics

6TThVV1,)&-

5rc'Pa-I I

.r?).' 0 (+114zr

En 16%. -. CI :. ............ --

ii t4oINL SETrIA&-S

lOt:_1±JI'

I PERCENT VALUE STROKE

B-3

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COS POWER ANGLE

0± 1.25

VARIABLE

WIND AT 1.2 sec AHEAD

BLADE #1 WIND

BLADE #1 TORQUE

Figure B-2

-91 k-10 sec

FULL SCALE 40

UNITS ;flTiT'T TTI [

O±I25FPS

-(-;--f---4-----I ,-..-•--4- -,-.---4--s--+---I-I--4

2[ZijIJT rfJ±I±:[1

0 - 125 FPS 1rm1I1ffcri11rfft(1m1(ffcI1fflT((iIr(111 i4-

4-4--I-4- -1---F -4- .--4---+-- -

7j J

0 ± 1,250,000 ft-lb

- - L

• GENERATOR POWER

PITCH ANGLE

• I __________ 1:Il :.1..ft: 1 t:1+H -4--4--$--+--t -4 4t' ..-$--.---4- -4-.

':IL liL'!!: !

.8 ± 2.5 Pu

0 ± 50 deg.

vrn I IT I • T1i j tm':j u t'L J'i1

-H-" --'--

J:j- —I-- ---

mIi: E'ft! •.1-. _-I-1iET: I : i : i :i: r.t1l_ fl:ft F

GENERATOR

1800 ± 119 rpm SPEED

ROTOR SPEED

34.7 ± 4.8 rpm

.77 rpm

= 22% overshoot

B-4

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-f-4-4--4

BLADE #1 WIND

0 t 125 FPS

BLADE #1 TORQUE

0-t 1,250,000 ft-lb

Figure B-3

VARIABLE

FULL SCALE UNITS

WIND AT

0 t 125 FPS

1.5 GUST 1.2 sec AHEAD

4-4-4-I -•-4--4- 4-I

GENERATOR .8 ± 2.5 Pu POWER

-i- I -I -l-----+--..-

PITCH ANGLE

Ot50deg. f..LL.iHIJTTI 60to220

3.84 rpm

ROTOR SPEED

34.7 t 24 rpm F 144

= 11% overshoot

B-5

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1. R'C2159494 2. Government Accession No. 3. Recipients Catalog No.

4. Title and Subtitle 5. Report Date

MOD 1 WIND 1IJRBINE GENERATOR FAILUREFebruary 1979 -

6. Performing Organization Code

NODES AND EFFECTS ANALYSIS

7. Author(s) 8. Performing Organization Report No.

10. Work Unit No

9. Performing Organization Name and Address General Electric Co.

11. Contract or Grant No. Space Division P. 0. Box 8661 Philadelphia, PA 19101

13. Type of RLpon nd Period C,ered Contractor Report

-

12. Sponsoring Agency Name and Address

U. S. Department of Energy Division or Distributed Solar Technology Washington, D. C. 20545 .

-

14. Sponsoring Agency-ø.4

Report No. DOE/NASA/0958-79/

15. Supplementcry Notes

prepared under Interagency Agreement EC-77-A-31-1044 Project Manager, R. Putlioff NASA Lewis Research Center, Cleveland, Ohio 44135

16. Abstract

A Failure Modes and Effects Analysis (FA) was performed for the Mod 1 Wind Turbine Cenerator. The analysis was directed primarily at identifying those critical failure modes that would be hazardous to life or would result in major damage to the system. Each subsystem was approached from the top down, and broken down to successive Lower Levels where it appeared that the criticality of thefailure mode-warranted more detail analysis. The results were reviewed by knowlegeable specialists from outside the Mod 1 program, and corrective action taken wherever recommended. -

17. Key Words (Suggested by Author(s)) 18. Distribution Statement

Wind turbine generator; failure modes, Mod 1 WTG

Unclassified - unlimited STAR Category 44 DOE Category UC-60

19. Security Classif. (of this report) 20. Security Classif, (of this pag) -! 21. No. of Pages 2?. Price'

Unclassified Unclassified 91

For sale by the Ndtion! Technical lnforinat;on Service. Spriuglicici. Vtigina 22161

NASA-C-168 (Rev. 10-75)*USGPO: 1980-657-145/5216