-
BRL-MR-3838
MEMORANDUM REPORT BRL-MR-3838
BRLNCOMPARISON OF 155-MM GUN TUBE HEAT INPUT
WITH SOLVENTLESS AND SOLVENT PROPELLANT
ARTHUR A. KOSZORUIRVIN C. STOBIE
JUNE 1990 J 2&i990
APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLLMITED.
U.S. ARMY LABORATORY COMMAND
BALLISTIC RESEARCH LABORATORYABERDEEN PROVING GROUND,
MARYLAND
90 06 28 023
-
NOTICES
Destroy this report when it is no longer needed. DO NOT return
it to the originator.
Additional copies of this report may be obtained from the
National Technical Information Service,U.S. Department of Commerce,
5285 Port Royal Road, Springfield, VA 22161.
The findings of this report are not to be construed as an
official Department of the Army position,unless so designated by
other authorized documents.
The use of trade names or manufacturers' names in this report
does not constitute indorsement ofany commercial product.
-
UNCLASSIFIED
REPORT DOCUMENTATION PAGEJ_______,~~gb~~f~ ~ ~i~ @ n~lmt . m.tS
U Ud M'~ .d~ .~i~ wIwg OWgu~ of
1. AGENCY USE ONLY CL&W hilri) I2. 4111041T DATE 1*REPORT
TYPE AND DATE$ OEEI June 1990 IFendl -len R- 87
.TTU AND SUITITU S. FUNDING is I~RS
Comparison of 155-mm G;un Tube Heat Input with P:
IL162618AH80Solventless and Solvent Propellant
6. AUTHOR(S)
Arthur A. Koszoru and Irvin C. Stobie
7. PERFORMING ORGANIZATION NAME(S) AND ADORESS(ES) B. PERFORMING
ORGANIZATIONREPORT NUMMER
9. SPONSORING I MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10.
SPONSORING 'MONIORINGUISA Ballistic Research Laboratorv AGENCY
REPOT MUMMER
ATTN: SLCBR-DD-TBR- -3 8Aberdeen Proving GIround. MD 2
0W5-5066
11. SUPKIEMENTARY NOTES
I 2a. DISTRIBUTION / AVAILABILIT'Y STATEMENT 12b. DISTRIBUTION
CODE
Appronced for public reledse, distribution is unlimited.
13. AM)ILACT (Maximum 200 wod)A test to measure wall
temperatures of a 155-mm howitzer cannon was conducted at the
Ballistic
Research Laboratory as part of a Product Improvement Program
(PIP) which was formulated and conductedunder the auspices of the
Armament Research, Development, and Engineering Center. The main
objective ofthis ballistic study was to determine if the projected
gun tube wear from an alternative, ballistically equivalent.155-mm,
M203AI propelling charge containing solventless stick propellant is
comparable to the wearproduced by the standard M203A1 containing
M3IA1E1 solvent based propellant. The results of this studyindicate
that the solventless propellant charge does not appear to be more
erosive thanl the standard M203AIcharge. Additionally, the effects
of several of the charge constituents on the amount of heat
transferred to thetube were investigated, with a particularly
dramatic increase seen in heat transferred to the tube when thecase
was removed.)
14L SUBJECT TERAMS IL NUMMER OF PAGES
7 71155-mm; M199 Cannon, (jun Wear; Solventless Propellant
(XM41), M203AI, Heait FI W mc ootInput; Erosiun f)'
17. SICJRIIY CLASSWICATIO 18. SECURITY CLASSICKAWN It. WNCW~t
a.ASSON44CATON n0. : IATIOM OF ABSTRACTOF REPOR4T I Of THIS PAGE 1
OF ABISTRACT
UNCLASSIFIED IUNCLASSIFIED UNCLASSI FlED SARMSN 75404-1604500
UNCLASSIFIED Standard For 298 (111t 2-49)
fowe ow I lm% fig. II
-
INTENTIoNALLY LFT BLANK.
-
TABLE OF CONTENTS
Page
LIST O F FIG U R ES
..................................................................................................................
v
I. INTRODUCTION
..................................................... 1
II. EXPERIMENTAL
.....................................................
A. TEST MATRIX
....................................................
B. TEST FIRINGS
.................................................... 4
III. RESULTS
....................................................... 5
IV. CONCLUSIONS
....................................................... 8
R E FE R E N C ES
.........................................................................................................................
10
ACKNOWLEDGEMENTS ..............................................
10
APPENDIX A - PROPELLANT DESCRIPTION SHEETS
........................................... 11
APPENDIX B - PRESSURE TIME CURVES
..................................................................
15
D ISTR IBU TIO N LIST
............................................................................................................
63
* ~~~O Inr~ r.l I
'i/or
iii
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INTNimoNALLY LEFr BLANK.
iv
-
LIST OF FIGURES
Fur Page
1 155-mm, M 203A 1 Propelling Charge
............................................................................
2
2 155-mm, M203A1 Solvenfless PIP Propelling Charge
.................................................. 3
3 Gage and Thermocouple Schematic
................................................................................
4
4 Breech Pressure and Pressure Difference, Standard M203A1
................. 6
5 Breech Pressure and Pressure Difference, Solventless M203A1
................................ 6
6 Temperature Changes at Thermocouple Locations 1-4
...................... 8
v
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IMNTNONALLY LEFT' BUANK.
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1. INTRODUCTION
The M203A1, shown in Figure 1, is a 155-mm, single increment,
top zone propelling charge. Thecharge contains approximately 11.79
kg of M31A1E1 triple base, slotted single perforated stick
propellantand a lead foil/wax/TiO2 liner which acts as a
decoppering agent and wear reducing additive. Thepropellant and
liner are contained An a rigid nitrocellulose combustible case
which contains talc in itscomposition for wear reduction purposes.
Ignition is accomplished with a CBI/black powder basepad heldin
place by a combustible end cap. The M203A1 propelling charge was
type classified on 29 March 1985to replace the granular M203 (bag)
propelling charge. A PIP is currently being conducted on this
155-mm, stick propelling charge by the Armament Research,
Development, and Engineering Center(ARDEC). This PIP would provide
an alternate solventless stick propellant for the M203A1
propellingcharge. An ARDEC-developed solventless propellant, XM41,
was selected as the candidate for the PIP,which will complete full
scale evaluation and result in type classification of the
alternative propellant in theM203A1 configuration. The charge
expected to result from this PIP is shown in Figure 2.
ARDEC initiated several investigations to determine the
applicability of solventless propellants to theM203A1 charge
configuration and performance level. Such a charge, manufactured at
currently under-utilized facilities, would significantly contribute
to the number of charges available to support
mobilizationrequirements. Additionally, solventless propellants
retain their extruded dimensions with less distortionthan solvent
propellants, leading to better physical uniformity, thus reducing
the labor and cost of blendingpropellants to obtain the required
ballistic uniformity. ARDEC-sponsored investigations
includepropellant producibility, ballistic acceptability, safety
and other charge design related areas. As part of thisseries of
investigations, ARDEC requested that the Ballistic Research
Laboratory (BRL) examine theeffect on wear of the substitution of
the solventless propellant for the standard M31A1E1 propellant.
In the BRL portion of the evaluation of the M203A1 solventless
stick propelling charge, gun tube walltemperatures were measured to
determine if the heat input into the cannon with this charge
wascomparable to that with the 155-mm, M203A1, stick propelling
charge. From previous ballistic data, it wasdetermined that
eliminating the combustible case i and duitlive liner io'wers
pressure but increases theheat input into the cannon near the
origin of rifling, thus increasing wear and erosion. Utilizing
thisinformation, possible charge variations were developed to
examine the effect of several charge componentson the heat
transferred to the gun tube.
11. EXPEkIMENTAL
A charge test matrix was developed by ARDEC and BRL to compare
heat input from a solventlesscharge with similar components to that
from a standard M203A1 charge. Further, an attempt was madeto
determine what effect the addition of flash-reducing agents and the
removal of the wear-reducing lineror combustible case would have on
the heat input to the gun wall.
A. Test Matrix
The ballistic test consisted of fourteen, control, M203A1,
solvent stick propelling charges, LotIND85M738-1B-3 and twenty
eight, experimental, M203A1, solventless stick propelling charges.
ARDEC-
1
-
N w
Ln4
0
Lg
00~
zz
ccLU L
SL0IL. ' IC
0 LU
zC.C6
C.))
mm
0.U
0 u2
-
z00a
-i zIs. WA
I- 00u4
x
CV) cc0ZwN WoJ cz 5
00 I0
zLo 15 ;: 1 fU)
T-LJQ IQ x
z c
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uJU
(A.
JLU
j0
39
-
developed XM41, solventless, slotted stick propellant, Lot
RAD-PD-736-8C was used in all the solventlessexperimental charges.
PXR6325 projectiles, Lot 1OP86D002S067, were used with both the
solventless andsolvent charges. All charges were conditioned at
twenty one degrees Celsius for twenty four hours prior
tofiring.
The solventless charges were subdivided into five sets,
consisting of the following components:
1. Variation 1. Seven charges contained 11.39 kg of solventless
propellant, a combustible case,
basepad, and TiO2/wax liner.
2. Variation 2. Seven charges contained 11.39 kg of solventless
propellant, a combustible case, and
basepad.
3. Variation 3. Six charges contained 11.39 kg of solventless
propellant, a combustible case, basepad,TiO 2/wax liner, and a
0.113-kg KNO 3 flash reducer.
4. Variation 4. Seven charges contained 11.39 kg of solventless
propellant, a combustible case,
basepad, TiO2/wax liner, and a 0.113-kg K2SO, flash reducer.
5. Variation 5. One charge contained 11.39 kg of solventless
propellant and a basepad.
B. Test Firings
The gun fuings were conducted at the Ballistic Research
Laboratory's Sandy Point Firing Facility (R-18), in a 155-mm, M199
cannon, serial no. 32000. The M199 cannon was modified to accept
two Kistler
607C4 piezoelectric pressure transducers and five thermocouples.
Chamber pressure measurements weremade by modifying the M199
cannon's spindle to accept one pressure transducer and machining
a
thrcaded port 904.2 mm from the rear face of the tube (RFT) at
the 12 o'clock position to accommodatethe second pressure
transducer in the tube sidewall. A schematic showing the gage anA
thermocouplelocations is given in Figure 3.
FOUR THE RMOCOUPLES 900 APART MOUNTED NEARORIGIIN OF RIFLING,
.060 INCH FROM INSIDE LAND
PRESSURE GAGESONE AT PROJECIILE BASE.
ONE IN BREECH
Figure 3: Gage and Thermocouple Schematic
4
-
To obtain the heat input measurements, holes were drilled in the
gun tube sidewall at the desired
thermocouple locations to a depth at 1.59 mm from the bore
surface. Constantan wires 0.13 mm indiameter were welded to the
bottoms6 of the holes using a capacitive discharge technique to
formconstantan-gun steel thermocouples near the bore surface. Four
thermocouples were located at 3, 6, 9,and 12 o'clock positions at a
distance of 1060 mm from the RFT at the origin of rifling. An
additionaldownbore thermocouple was located at 12 o'clock at 1524
mm from the RFT. This technique was initiallydeveloped by Brosseau3
to measure wall temperatures in 37-mm guns. The technique was
modified forthis M199 cannon to determine the extent of asymmetric
heating in a 155-mm howitzer.4 The asymmetricheating study provided
a reasonable data base for the evaluation of solventless
heating.
A calibration factor of 52 microvolts per degree Kelvin was used
to compare known voltage calibrationsteps to the response of the
thermocouples. The maximum temperature change for each
thermocouplewas noted for each round. The heating effects of the
various rounds in this study, as well as in Reference4, were
expressed in the maximum temperature change. The maximum
temperature change at each
thermocouple is a reasonable measure of heat input from the
various charges since all the rounds hadsimilar maximum pressures
and pressure durations. Given the pressure similarities, the
assumption wasmade that the heat input took place in the same
amount of time for all of the rounds.
A 15-GHz continuous wave doppler radar and discriminator were
used to obtain on-line velocity/timerecords.
The maximum breech and forward pressures, differential pressure,
projectile velocity and change intemperatures were recorded and
reduced by the Ballistic Data Acquisition System (BALDAS) under
thecontrol of a PDP 11/45 minicomputer.
III. RESULTS
The maximum pressures, muzzle velocities and sample sizes for
all the firings are summarized in Table1. The maximum temperature
changes for the thermocouples at three positions at the origin of
rifling aresummarized in Table 2. The two other thermocople
positions - origin of rifling at 9 o'clock and downbore- are not
included due to the failure of the thermocouple junction at these
positions for most of therounds.
5
-
Variation 1 was the substitution of solventless propellant for
the standard M31AIE1 slick propcllant.Breech pressure-time and
pressure difference (forward - rear gages) plots are given for the
standardM203A1 and the solventless propellant M203A1 in Figures 4
and 5 respectively. A complete record of thepressure-time curves
and thermocouple plots are contained in Appendix B. The maximum
pressure andmuzzle velocity were higher for the solventless
variation in comparison to the standard M203A1 charge.The cause of
these higher values was attributed to the fact that the solventless
charges were fired with 0.3kg more propellant than was required to
ballistically match the M203A1 charge. The maximum change
intemperatures with these charges agreed within the scatter of the
data with the standard charge, indicatingno effect on thermal
erosion produced by substitution of the solventless propellant for
the solventpropellant. The temperature-time traces for a
solventless M203A1 firing are given in Figure 6. Thesetraces are
typical of all those obtained in this study.
BREECH, FORWARD & DELTA PRESSURE
00
35@
300
c3
U)
so-
_50 -1-
is 2030 .1 0I cI[ ( MS )
Figure 4: Breech Pressure and Pressure Difference, Standard
M203AI
BREECH. FORWARD & DELTA PRESSURE
350
30
490
LAJr,
(I)
LUI
lea
IS 0 30TI I LI. (H I
Figure 5: Breech Pressure and Pressure Difference, Solventless
M203AI
6
-
Sample Breech Forward MuzzleCharge Size Pressure Pressure
Velocity
(MPa) (MPa) (m/s)
M203A1 14 366 325 827
Solventless/ liner 7 380 334 839
Solventless/ wo litver 7 364 321 835
Solventless/ KNO 3 6 384 350 844
Solventless/ K2SO4 7 382 340 841
Solventless/ no case 297 262 794
Table 1. Pressures and Velocity
Sample Max Temp Rise (°C) Avg atCharge Size 12 3 6 Origin
M203A1 14 113±8 81±3 108±3 101±5
Solventless/ liner 7 116±8 82±3 114±4 104±3
Solventless/ wo liner 7 119±6 87±2 120±3 110±4
Solventless/ KNO 3 6 115±5 83±2 113±2 105±3
Solventless/ K2SO4 7 116±8 82±2 111±2 105±5
Solventless/ no case 1 139 -- 138 133±10
Table 2. Thermocouple Data
7
-
2S5
l ogLU7
a
i- soLU
25
0 5 li0 Iso 200 250 300T ME iMs
Figure 6: Temperature Changes at Thermocouple Locations 1-4
Variation 2 was the solventless charge without the TiO2/wax/lead
liner. As expected from previous
experience with the M203A1, this variation resulted in reduced
pressures and velocities in comparison tothose from Variation 1.
This reduction should be expected, since the elimination of the
liner effectivelyincreased the chamber volume. The temperature
measurements were slightly higher at all of thethermocouple
positions. The temperature results indicate the minimal effect of
the wear reducing additivein this charge.
Variations 3 and 4 were the solventless charges with flash
reducers of KNO3 or K2SO4. Higherpressures and velocities were seen
with the flash reducer shots when compared with other
solventlessrounds due to the reduction of free chamber volume. The
flash reducers produced no effect on thetemperature increases.
Variation 5 consisted of a solventless charge without the
combustible cartridge case. The pressures andvelocities were less
than the other solventless rounds due to reduction of the amount of
energetic materialin the charge and the effective increase in
chamber volume due to the elimination of the case and
parasiticcomponents. The maximum temperature at the two measured
positions increased dramatically over theother solventless charges.
These results were anticipated because the combustible case has a
flametemperature near 2200 K while the flame temperature of the
solventless propellant is approximately 2737K. The combustible case
not only reduces the effective flame temperature of the entire
charge, but has anadded cooling effect in that gases from its
combustion are produced near the boundary layer, thecharacteristics
of which govern the heat input to the tube.
IV. CONCLUSIONS
From the data gathered in this study, we can draw several
conclusions regarding the effect several ofthe charge constituents
have on the amount of heat transferred to the gun tube during the
interior ballisticcycle.
8
-
A combustible-cased charge containing solventless XM41
propellant does not appear to be moreerosive than the standard
M203A1 charge containing M31A1E1 stick propellant, based on the
amount ofheat input at the origin of rifling.
The wear reducing additive in the solventless charge reduces the
maximum temperature change, andthus the heat input, at the origin
of rifling. The magnitude of the reduction appears small;
however,testing performed during the M203A1, product improvement
program predicted a wear life significantlylower without the
liner.
The addition of a flash reducer in the amount typical of that in
a fielded charge (0.113 kg) does notaffect the amount of heat
transferred to the gun tube. It does, however, increase the maximum
chamberpressure to the degree expected.
The elimination of the combustible cartridge case significantly
increases the heat input at the origin ofrifling, as expected. The
cooling effect of the entrainment of the case gases, which are
cooler than thoseof the propellant, into the boundary layer was
dramatically demonstrated by the the comparison of thetemperature
rise in the vicinity of the origin of rifling with cased and
uncased charges.
9
-
REFERENCES
1. T.L. Brosseau, I.C. Stobie, J.R. Ward and R.W. Geene, "120-mm
Gun Heat Input Measurements,"
BRL-TR-02413, US Army Ballistic Research Laboratory, Aberdeen
Proving Ground, MD, July 1982.
2. F.A. Vassallo, "An Evaluation of Heat Transfer and Erosion in
the 155-mm M 185 Cannon," Technical
Report No. VL-5337-5-1, Calspan Corporation, Buffalo, NY, July
1976.
3. T.L. Brosseau, "An Experimental Method of Accurately
Determining the Temperature Distribution and
Heat Transferred in Gun Barrels," BRL-R-1740, US Army Ballistic
Research Laboratory, AberdeenProving Ground, MD, September
1974.
4. D.L. Kruczynski, "Gun Tube/Charge/Projectile Interactions and
Gun Tube Wear," BRL-TR-3004, US
Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD,
June 1989.
ACKNOWLEDGEMENTS
The authors wish to thank the crew at Range 18 - Messrs. J.
Bowen, J. Hewitt, J. Stabile, R. May, J.Tuerk, D. Meier, and S.
Little - for the experimental support in conducting the firing
program.
10
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APPENDIX A
Description Sheets for XM41 and M3AE1 Propellants
11
-
IM'ENTONALLY LXEFT BUANK.
12
-
XM41
P AF ROPELLYAMMNTO LNT .S RADFORD, SHA. DunO-7--4
CObv Cetr SMQtEN ae 101 /8 37.214 o PT1 0 mlb *~
MAX % ____m__
1131 - - 10ANU ACTURL OF .... !L...N! mc ACU
0.5 m/c oain Lodenist nte-- -08
700 cccleloa df 38
CONSWUNTPOROULAAD M A
uaiin- 200 ±10-- NoFue -Ih
Nitroglycri n manfacure by. RAA; Oirgaiiemfacue byOAN SnlWr
A.AP
1.3
-
N131AIE1
'Aane allyOR AYMUuNITION PLANT, RAFRmm, VA.~ AAgUC40
AC Inn=as OUM Los MT91"Cwl .. atrC 1" 31C
so 12.92 -184p
-te.tooemueetu upeciftlonerequiren..,,:
McmUI 2a43 mbin hold 4
Incrase t A' n-rhour2514
-
APPENDIX B
Computer generated plots of breech, forward, and delta (breech
minus forward) pressures, andthcrmocouple output.
(Plots are in order of firing).
15
-
INTnTimoNALLY LEVI BLANK.
16
-
PROPELLANT LINER FLASH
RD # TYPE Yes/No REDUCER
36 M31AIEI Y ---
37 XM41 Y ---
38 M31IE1 Y ---
39 XM41 N ---
40 M3AIEl Y ---
41 XM41 N ---
42 XM41 Y ---
43 M31IE1 Y ---
44 M31AIE1 Y ---
45 XM41 Y ---
46 XM41 N ---
47 M31A1E1 Y ---
48 XM41 Y K2so 449 XM41 Y KNO
50 M31AIE1 Y ---
51 XM41 Y KSO 4
52 XM41 Y KNO 3
53 M3IAIE1 Y ---
54 XM41 Y KSO4
55 XM41 Y KNO
56 M31IE1 Y ---
57 XM41 Y KSO 4
58 XM41 Y KNO
59 M31AIE1 Y
60 XM41 Y ---
61 XM41 N ---
62 M3lIAE1 Y ---
63 XM41 Y
64 XM41 N
65 XM41 Y ---
17
-
PROPELLANT LINER FLASHRD # TYPE Ycs/No REDUCER
66 XN141 N--
67 XM41 Y--
68 XN141 N--
69 N131AlEl Y--
70 XM41 Y
71 XM41 N--
72 XM41 Y K 2 S0 473 XM41 Y KNO 374 M31AlEl Y--
75 XM41 Y K 2 SO 476 XM141 Y KNO 377 M31A1E1 Y--
78 XM41 Y K 2S0 4
18
-
WEAR 36BREECH c. FORWORO PRESSURE
'Is,
389
0-
250
S 290-
Q Is*0-
.
TIME (M1S)
WEAlR 36DELTA P
76-
0-
-25as 30 i 9s4)s
TIM 2MS
DAA OS
a-9
-
WEAR 37BREECH PRESSURE
RIs@
355-
a0. 300
2S@
LA]
205-CA
01 7 2 .2 27 32 37 42TIME (MS)
DATA LOST
WEAR 37TC *0, 90. 180, 270 DEG
126
0. 765m
I
-AJ
25-
* so 5 le Is 209 210 3ioTIME (MS)
20
-
WEAR 38BREECH & FORWARD PRESSURE
-"
ties
35,
250
D 200
w M
too-
soi00
ii 23 28 i3 38 43TIME (MS)
WEAR 39DELTA P
IS'
75
5-
LiJ
LL
Id
2S Is23 is i3 i8 43
TIME (MS)
WEAR 38TC 0 , 90. 180. 270 DEG
126
w
C.. 75IJ
-J
25
S so oS 5i 25O 25@ 300
TIME (MS)
21
-
WEAR 39BREECH. & FORWARD PRESSURE
S300
259
La
Ir ISOC-
TIME (MS53
WEAR 39DELTA P
7S
0.
5 so
w
as.
TIME (MS)
WEAR 39TC .9. 99. 190. 279
Iff
CIE
4- 7;-j
as
lie O ISO 20 215., 305TIME (MS1
22
-
WEAR 40499 BREECH & FORWARD PRESSURE
'I"
3SOJ
2se
266
LiS Is#
IGO
68
16 21 62 1 ITIME (MS)
WEAR 40DELTA P
7S
2S.
CL
-2 s - Ii
TIME (MS)
WEAR 40TC 0. 90, M, i 270 DEG
CL 761
a Go
2S L
TIME (MS)
23
-
BREECH I FOrW11LR ITELCSIREI4se
46B-
3SOe
a 3eO0:
C')
1:9
:L
TIME (MS)
WEAR 41its DELTA P
76
a
CLJ
TIME (MS)
WEAR 4 1TC 0 . 9o. 180. 270 DEG
(X so
1-5
-j
a 7
2-
a
224
-
WEHR 4'BREECH & I-ORVPID 1CLS;UrE
I&SO
400
300
260w
200
.U
" ISO
so
19 a' 934 30 44'TIME IMS)
WEAR 42Iffu- DELTA P
7 -
20.
Lso
w
0.
Is 2's 22 3'I 30 lTIME (MS)
WEAR 42TC 0 e. 90. 180. 270 DEG
126
IJ IO
0
$0 los.O 20 S O
I-
a gI--Ja
2S
S 0 so lt li i 29 1TIME (MS)
25
-
BREECH & I-Oli! ILU
Qs-
250
hicn
ISOso
10 i4 i9 44
TIME (MS)
WLFR 43DELTA P
7s
a0..L
26
CL.
-asIS 24 29 W
TIME (MS)
WEAR 43TC 6 0. 99, 190 DEG
ISO
129
hlo
75
I"-
I-
29
Si Ile IeO 2OO 2gi 3"
TIME (MS)
26
-
WEAR 44BREECH &FORWARD PRESSURE
360-
a~
20
wmW
017 22 27 i2 37 412TIME 01S)
WEAR 414DELTA P
79
0.
so.
2SSE
a..
-2 2 7i i 9
go. 750 0 80 7 E
126-
- 7
as
DELTl TEMP (DE
27
-
WEAR 45B~REECH FORAR PRLESSURIE
360-
260-
Of ISO0.
If
17 22 22 37 1TIME (MS)
WEAR '45DELTA P
lee
26-
0-
TIME (MS)
WEAR 45TC 0G. 99. 190. 279 DEG
LU
a S
0. is le li6il iTIE(S
W2
-
WEfk 116
BREECH & FORWARD PRSSURE
q gov .".-
0-.
2s.
1*4
200
LiJ
0-
IO
l
019 24 28 3 0TIME (MS)
WEAR 46DELTA P
C5
ix
-I
.
.
TIME (MS)
WEAR 46TC 0.O 90, 180 DEG
r26-
InS
_,
Li IN.
0T $0
I--Jwa
21
so lie lie 2go 260 StTIME (MS)
29
-
WEHP 11,;SR[FCH FPJ l IF:'~
350
a .30
250
20
w0! is#
0.
I"
20 30 ;5 lie uslTIME (MS)
WEAR '47Iff. DELTA P
7S-
0.
sa.
TIE MS
nER 4
CL
.a
In.
LuJ
a t
TIME (MS)
30
-
WEAR 49
: GO BREECH &FORWARD PRESSURE
36e-
300
0) 20
u
20 No a035IsTIME (MS)
WEAR 48
____________DELTA P
75
26.
TIME (MS)
WEAR '49TC a 0, 90, 199 DEG
* 2
76
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62
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No of No ofCopies Organization £Qks Organizaion
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DepartmentATN: OHE200, M. GersteinLos Angeles, CA 90089-5199
2 University of UtahDepartment of Chemical EngineeringATTN: A.
Baer
G. FlandroSalt Lake City, UT 84112-1194
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USER EVALUATION SHEET/CHANGE OF ADDRESS
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