era
THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS
345 E. 47 St., New York, N.Y. 10017
83-JPGC-GT-15
The Society shall not be responsible for statements or opinions advanced in papers or in
discussion at meetings of the Society or of its Divisions or Sections, or printed in its
publications. Discussion is printed only if the paper is published in an ASME Journal.
Released for general publication upon presentation. Full credit should be given to ASME.
the Technical Division, and the author(s). Papers are available from ASME for nine. months
after the meeting.
Printed in USA.
Copyright © 1983 by ASME
PERFORMANCE TESTING IN OXYGEN OF A HIGH-PRESSURE, HIGH-VOLUME OXYGEN COMPRESSOR
M. J. Tessier, Acting Manager, Test Engineering Group
R. A. Granger, Member, Technical Staff
Energy Technology Engineering Center
Rockwell International
Canoga Park, California 91304
ABSTRACT
In connection with the Coal Gasification Program
of the U.S. Department of Energy, a need was identified for a high-pressure, high-volume oxygen compressor. At the time, the highest steady operating pressure available from commercial-sized turbocompressors
was about 65 bar (950 psia), which was being used in
the partial oxidation process for ammonia or methanol
synthesis. For advanced coal conversion plants, compressors operating at 115 bar (1667 psia) would be
needed.
The U.S. Department of Energy (DOE) entered into
an agreement with the West German firm of Mannesmann
Demag, AG, to develop a high-pressure oxygen compressor. Mannesmann Demag designed and fabricated a third
casing centrifugal compressor (to be used in a train
with available compressors) having a nominal inlet
pressure of 65 bar (950 psia) and a nominal discharge
pressure of 115 bar (1667 psia). In exchange, the U.S.
DOE agreed to fund the modification and operation of a
NASA-owned test facility for testing the compressor.
The facility, CTL-V, was modified and operated by the
Rocketdyne Division of Rockwell International. Test
management and reporting was carried out by DOE's
Energy Technology Engineering Center (ETEC), operated
by Rockwell International's Energy Systems Group.
components) but that had to be converted to run endurance tests lasting several hundred hours.
INTRODUCTION
The objective of this program was to test the
high-pressure part of a multicasing oxygen turbocompressor train under original design and off-design
conditions to prove its thermodynamic and mechanical
performance and the overall integrity of the design.
The test was performed at the NASA-owned Rocketdyne
CTL-V, Cell 3B, test facility (Figure 1). The facility was modified by Specification BE627-65993-T3 and
operated by the Rocketdyne Division of Rockwell International under the direction of the Energy Technology
Engineering Center (ETEC). The test program was
funded by the Department of Energy. The compressor
was manufactured by the Compressor and Pneumatic
Equipment Division of Mannesmann Demag, AG, Duisburg,
This paper presents a brief description of the
compressor test article and test facility. The test
program, test results, and analysis are presented in
greater detail. The scope of the test program included
low- and high-pressure nitrogen shakedown tests, oxygen
performance and steady-state tests, and oxygen maximum
suction pressure tests.
The facility is unique because it is the only one
of its kind nationally that can provide the power to
drive the compressor and that has liquid oxygen/liquid
nitrogen capability (the facility is utilized for
development and testing of rocket engine turbopumps).
Also, testing and data acquisition, reduction, and
analysis were performed in a facility that normally
runs tests of few minutes duration (for rocket engine
f
%
ETEC-P98040CN
FIG. 1 DEMAG COMPRESSOR INSTALLED IN FACILITY
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E
TABLE 1
SUMMARY OF COMPRESSOR DATA AND MATERIALS
West Germany, and supplied through their New York subsidiary, Mannesmann Demag Corporation.
The following organizations were involved in this
test program:
•
•
•
•
•
Data
Compressor type
Suction pressure
05MV4B
40 to 50 bar
(580 to 725 psia)
Discharge pressure 90 to 135 bar
(1305 to 1958 psia)
10 to 17 kg/s
Mass flow
(7.93 to 13.5 x 10 4 lb/hr)
12,000 to 15,000 rpm
Operating speed
Up to 2500 kW (3354 bhp)
Coupling power
DOE/Fossil Energy Division - Technical Director
DOE/SAN - Contract Director
Demag Corporation - Test Requester
ETEC - Test Manager
Rocketdyne - Test Performer.
The project began on April 1, 1980, with the initiation of facility design activities. The compressor
was received at the test facility on February 3, 1982.
Testing was begun on May 26, 1982, and successfully completed on July 19, 1982. The test article was removed
from the test facility on August 6, 1982, and turned
over to Mannesmann Demag on August 6, 1982.
Material
Casing
Impellers
Shaft
Shaft sleeves
Inner casing and
diaphragms
Labyrinth seals
Casing seals
The test program consisted of the following
•
•
•
•
•
A low-pressure nitrogen shakedown test
A high-pressure nitrogen shakedown test
An oxygen performance test
An oxygen steady-state test
An oxygen maximum suction pressure test.
Stainless CrNi cast steel
NiCu alloy
Stainless CrNi steel
NiCu alloy
Bronze
CuNi alloy/silver
Teflon polymers (0 rings)
FIRST STAGE
SECOND STAGE
TEST ARTICLE
The test compressor was designed by Mannesman
Demag as the high-pressure part of a three-casing centrifugal compressor train suitable for the compression
of a normal mass flow of 13 kg/s (1200 tons/day) of
oxygen.
N
The test article contained two compression stages
with an interstage cooler. Each compression stage
contained two centrifugal impellers. The compression
stages were arranged "back to back" with an additional
balance drum at the second-stage inlet side to minimize the gas-pressure thrust on the rotor. The barreltype casing was stainless steel. Considering the reaction behavior (burn) of metallic materials in an oxygen
atmosphere, special attention was given to the material
selection. The general data and material selection for
the compressor are summarized in Table 1, and a simplified view of the compressor is shown in Figure 2.
H
FIG. 2 SIMPLIFIED ILLUSTRATION OF CUMPRESSOR
ERIIIIII V
DESCRIPTION OF TEST FACILITY
The Demag compressor was tested in Cell 3B of the
NASA-owned Rocketdyne CTL-V test facility. Before
testing was begun, the facility was extensively modified to extend its capability to test the oxygen compressor. The modifications included adding a highpressure main flow loop (Figure 3), controlled vent
systems, controlled gas supply and makeup systems, a
water cooling system, lube oil supply and return systems, additional instrumentation, a digital data
acquisition system, and analog magnetic tape.
7
^FV^E_oo_
^MAwF^ow ^o^ MF^^
To help detect a compressor seal failure, a differential pressure sensor was installed between the
buffer seal gas supply line and the buffer gas vent
line (from the compressor). The pressure measurement
had an alarm value of 0.07 bard (1.00 psid) and a redline (shutdown) value of 0.04 bard (0.60 psid) during
oxygen testing. A vent pressure higher than the supply pressure (nitrogen) would indicate that a compressor seal had failed.
FA
Q
FIG. 3 TEST SYSTEM
The compressor labyrinth seal leakage gas (oxygen
or nitrogen) was also vented to the atmosphere. A gas
2
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makeup system was provided to maintain the main flow
loop (MFL), as shown in Figure 3, at the required pressure. The gas makeup system consisted of a low-flow
(low MFL pressure) gaseous nitrogen supply and a highpressure liquid oxygen/liquid nitrogen system. The
low-flow gaseous nitrogen system was used to pressurize the MFL before the start of every test, for the
low-pressure nitrogen shakedown test, and for changing
the MFL back from oxygen to nitrogen prior to shutting
down the compressor. The liquid nitrogen makeup system was used during the high-pressure nitrogen shakedown test and for increasing the pressure in the MFL
before the changeover to oxygen. A continuous supply
of 3350 kg/hr of oxygen was required for the gas makeup
system.
The makeup gas was injected into the MFL upstream
from the aftercooler to ensure that the gas was preconditioned prior to entering the compressor.
Figure 4 provides a schematic of the liquid oxygen (or nitrogen) makeup system. The method of operation was to utilize the liquid oxygen from one tank,
say V517, and at the same time fill the other tank,
V070, with liquid oxygen. When the supply of liquid
oxygen in tank V517 was nearly exhausted, the operation changed over to tank V070. Tank V517 was then
refilled with liquid oxygen. The run time on each tank
ranged from 45 to 90 min, depending on the MFL pressure
5K
CTL V - DEMAG COX COMPRESSOR CTL V CELL 3B
REFILL SYSTEM
GO2
600
operation ran from one tank, say Vll9, and filled the
other tank, V120, with liquid oxygen from an off-site
fill location. When the supply of liquid oxygen in
tank V119 was nearly exhausted, the operation changed
over to tank V120 and then filled tank V119 with liquid
oxygen from the off-site loading stations. During the
high-pressure nitrogen shakedown test, liquid nitrogen
was used in place of liquid oxygen. The low-pressure
nitrogen shakedown test used the gaseous nitrogen supply in place of the liquid nitrogen supply because the
makeup rate required for nitrogen was lower.
Before entering the MFL, the liquid oxygen from
the high-pressure tanks (either 517V or V070) passed
through a flowmeter, a filter, and a hydraulically
controlled supply valve (see Figure 4). The liquid
oxygen was then injected into the MFL via a "mixer."
During normal operation, the compressor was started up
with gaseous nitrogen; then, when the temperature of
the 11FL gas stabilized, the makeup gas was changed over
to liquid oxygen.
A lube oil system consisting of a skid-mounted
reservoir, heater, pump, heat exchanger, and electrical controls provided lubrication to the compressor
bearings and carried the friction-generated heat.
An elevated oil reservoir with a capacity of 0.227
m 3 (60 gal) was located 5 m (16.4 ft) above the compressor centerline. The emergency supply provided a
flow rate of 0.315 liter/s (5 gpm) at the compressor
for 250 sec in the event of a lube oil pump failure.
601
COD
The compressor was directly coupled to the three
5150-hp dc motors of the CTL-V drive system by a
flexible-diaphragm coupling. The connection to the
facility torquemeter shaft on the drive end was made by
a special adapter hub that was an integral part of the
coupling.
T4
602
A LT1
V120
451
LT2
US
110 psi,
V119
a5K
STORAGE
LOX
110IT-
ToRAIE
The alignment requirements for the coupling were
as follows:
LOX
• Maximum axial deflection: + 0.5 mm
• Maximum angular deflection: 0.02°.
The three dc drive motors were in turn driven by
a motor-generator set to change the speed of the
compressor.
201
COMPRESSOR FLOW LOOP
0
LOX
The first critical speed of the compressor was
8100 rpm, and the lowest attainable idle speed on the
CTL-V drive motor was 7632 rpm. This was attained
using a main gear ratio of 4.0 and an average gear
ratio of 17.0.
INEWI
FILTER
REGULATOR
GN 2
S-0 VALVE
S
LOX THROTTLE VALVE
r51 COX THROTI LE VAl VF
MIXER
VFNTURI ) A/C
IA FTER COO LEE
FILTER
VENT IO ATM
_DJ* ^ HACK PHFSSURf.
IC
I1TLR000LEHI
D
CONTROL VALVII
FTFE9E61,
FIG. 4 OXYGEN/NITROGEN MAKEUP SYSTEM
The high-pressure tanks, V517 and V070, were both
supplied with liquid oxygen from storage tanks V119
and V120. Tanks V119 and V120 each had a capacity of
45,000 gal. During the long-duration tests, the
The drive system provided two methods of stopping: Coasting stop and dynamic braking stop. During
the coasting stop, the system carne to a stop by the
frictional forces present in the compressor and the
drive system. This type of stop took about 250 sec.
When a quick stop was desired, the dynamic braking stop
was actuated. This separated the test motor stators
from the frequency changers and connected them to fixed
resistors. Acting as alternators, the test motors then
converted the system's stored energy into electrical
energy, which was dissipated in the resistor banks. A
complete stop from full speed by this method took about
6 sec. Both methods of stopping were used during the
test, with the dynamic braking the most desirable
method because of the reduced setup time required to
restart the drive system.
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A minicomputer-based digital data acquisition
system (DDAS) and a 14-channel analog magnetic tape
were used to record the test data. Both facility and
test article data were recorded on magnetic tape as a
permanent record of test information. The DDAS also
monitored data in real time and provided a variety of
data displays for assisting the engineers in conducting the test. Data were also recorded temporarily on
the disc to provide a data base of recent data that
could be recalled for troubleshooting or reviewing the
test program.
Data acquistion to magnetic tape and disc
High-rate disc dump to tape (for unplanned
events)
Trend plot on CRT (remote)
Data reduction output on CRT and line printer
TV display of tabulations
Recall data and plot via printer/plotter
Cut/alarm limits via relays
Instrument calibration programs
Hardcopy computer activity log
Store and modify calibration, alarm, reduction
data
High-frequency tape: start/stop
Real-time fast Fourier spectrum analyzer.
Five proximity-type transducer systems were provided with the compressor. Each proximity system was a
gap-to-voltage transducer that was sensitive to the
static and dynamic change in distance between the tip
of the probe and the conductive material that was observed (compressor shaft). The transducers measured
the movement of the compressor shaft and were installed
at the locations shown in Figure 5.
o
DNIVE
sEa°E°
(SEQUENCE )5)
COMPRESSOR BEARING
BEARING
/THERMOCO UPLE3
f5E0UENCE ]JI
LE6 IS EOUENCE T61
COMPRESSOR BEARING
THERMOCOUPQE4
(SEQUENCE
0
STAGE DSTAGE
DRIVE
ENO
-
COMPRESSOR'
SHAFT
The DDAS had the following capabilities:
GMPRESBGR^
COMPRESSOR BEARING
THERMOCOUPLES
p
0
o
0
^SEDU SSOR I E ,
COMPRESSOR BEARING
THERM OCO UPLE2
ISCOVESCE 7n
_ TEST COMPRESSOR
ETEC-98055
FIG. 6 COMPRESSOR BEARING THERMOCOUPLE LOCATION
gas and controlling the compressor inlet pressure at
3.0 bard (56 psig). During the test, compressor labyrinth exhaust valve A was maintained fully open, and
labyrinth exhaust valves B and C were maintained fully
closed. This was done because of the low pressure
level of the MFL during the test. The MFL throttle
valve was initially set to the full open position prior
to start of the test and was repositioned to 48% at
10,290 rpm. When idle speed was reached, the axial
shaft position alarm was reset to +0.161 mm. This
preplanned sequence of operation was due to the change
in axial shaft position when the compressor was rotating. The compressor speed was held at 15,295 rpm (115%
speed) for 15 min.
After the 115% speed run was complete, the compressor speed was lowered to 13,965 (105% speed). At
this speed, the MFL throttle valve setting was varied
to produce the following pressure ratios:
COMPRESSOR
SHAET
s,A E
RADIAL POST TION /
PROBE 315E vENCE 831
HORIZONTAL
POSITION
PROBE 4 ISEOUENCE 8 ]i
1 ERTI(A-
o D D ^/P°^TENPROBE
Rq UTALPO5ITION
PROBE 1(SEQUENCE 84)
HO HICONTAL
RADIAL POSITION
PROBE 21SEQUENCE 851
E RTICAL
ETEC-96056
FIG. 5 COMPRESSOR PROXIMITY TRANSDUCER SYSTEM
INSTALLATION
The output signals from the proximity transducers
were recorded on the DDAS and analog tape recorder. In
addition, the signals were also accessible to an oscilloscope and a real-time spectrum analyzer. The monitoring system provided a time domain and a frequency
domain analysis of the raw signal on a real-time basis.
Six chromel-alumel thermocouples were supplied
with the compressor to measure the compressor bearing
temperatures. The locations of these six thermocouples are shown in Figure 6.
LOW-PRESSURE NITROGEN SHAKEDOWN TEST
Test 362-821 was initiated at 1208 hours on
May 26, 1982. The test was performed using nitrogen
Throttle
Pressure
Ratio
(P 2 /P 1 )
Valve
Position
(%)
1.6
1.8
2.0
2.22
2.35
2.45
Surge
41.5
37.7
32.7
25.9
22.6
16.5
15.8
The compressor speed of 105% was held for 4 hr and
then returned to idle speed. The shutdown was executed
in the coastdown stop mode.
During the test, the power spectral density (PSD)
data from each of the five shaft position transfers
were examined on the spectrum analyzer and reproduced
on the plotter/printer. The proximity instrumentation
showed low vibration levels throughout the test.
Two data plots taken during the test are shown in
Figures 7 and 8. These plots consist of the following:
1) Compressor speed (sequence 66) versus time
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L
ETEC DPUP PLOT
DONE
X
I_ W PPE`^S [^N
COMPHESSOP
Sri K7 DDEN TEST
L
^^
D
P
I
r-
0
E1
I
1
0
11111
HOUR
xlu
SE[
3
2
5
4
ELRPSED TIME [HOURS]
5/26/82
5/26/82
5125182
5/26'82
5/26/82
5/26/82
o
0
0
o
n
o
II
0
D
xsE[
12
0
o
13
0
0
14
0
D
16
15
0
o
o
7
6
9
5/26/82
5/26/82
0
0
o
1]
0
0
8
5/26/82
IB
0
0
19
0
D
5/26/82 DPI
20
D
D
D
NDa
xl
ms
ns c
FIG. 7 LOW—PRESSURE SHAKEDOWN TEST DATA PLOT, COMPRESSOR SPEED VERSUS TIME
ETEC TUTU P'.0T
n r
RHO
6 2ST( xl 711 BOCG 8FSED
oUH1UU1IIHU6
DEMPG OXYGEN COMPRESSOR
RHO
LOW PRESS GNE SHRKE EDEN TEST
wti
w
n^
hU v
0
2UwWvVUv^"
U ✓ UUuiuUVU
✓
7^
ti1.M/1/1M^/^
on
OUT
HOUR
o
5/26/12
11
z
1
5/26/82
12
IN
0
E[
U
TTIES
5/26/82
13
s
5/26/82
IS
v
s
ELRPSED TIME IHJLRSI
5/26/82
IS
5/26/82
16
r,
5/26/8'
17
7
5/26/82
18
e
5/26/82
19
s
5/26/5? 098
HOUR
20
0
0
0
U
0
0
0
0
0
xlx
0
0
0
0
0
0
0
U
D
SEc
0
0
0
0
0
0
0
0
U
0
X9ec
FIG. 8 LOW—PRESSURE SHAKEDOWN TEST DATA PLOT, COMPRESSOR GAS TEMPERATURE VERSUS TIME
5
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2) Compressor gas temperature versus time
•
•
•
•
Sequence
Sequence
Sequence
Sequence
1
2
3
4
-
First-stage inlet temperature
First-stage outlet temperature
Second-stage inlet temperature
Second-stage outlet temperature
95%
2.15
2.24
2.34
2.38
1392
1440
1471
1547
105%
1.96
2.11
2.32
2.53
2.64
2.83
1252
1368
1493
1615
1713
1791
110%
2.10
2.30
2.53
2.82
3.01
1356
1486
1640
1841
1938
HIGH-PRESSURE NITROGEN SHAKEDOWN TEST
Test 362-825 was completed on June 16, 1982. The
compressor was operated for 6 hr, 30 min and achieved
all of the objectives defined for the high-pressure
nitrogen test with the inlet operating at 55 bar (797
psia). The makeup system functioned satisfactorily on
liquid nitrogen, demonstrating readiness for operation
on liquid oxygen. Data were acquired at 110% speed
with the following pressure ratios:
Pressure
Ratio
Second-Stage
Discharge Pressure
(psig)
1599
1731
1808
1376
2.03
2.18
2.27
1.73
Performance data from the 2.27 pressure ratio test
point are shown in the appendix.
Selected performance data for the oxygen performance test are shown in the appendix.
OXYGEN MAXIMUM-SUCTION PRESSURE TEST
Test 362-8219 was initiated on July 19, 1982.
Compressor speed was set at 102%, and the first-stage
inlet pressure of the compressor was increased to 52
bar (754 psia). The throttle valve was then adjusted
to obtain a compressor second-stage discharge pressure
of 135 bar (1956 psia). After conditions were stabilized, the maximum pressure condition was held for
1 hr. Selected performance data are shown in the
appendix.
OXYGEN PERFORMANCE AND STEADY-STATE TEST
CONCLUSION
Test 363-8210 was initiated at 1751 hours on
June 23, 1982. The compressor was successfully operated on oxygen for 17 hr, 45 min. During that time,
performance data were taken at all of the following
pressure ratios with the compressor operating at
100% speed:
Pressure
Ratio
Compressor Discharge
Pressure
(Sequence 8)
(psig)
1.79
2.02
2.27
2.44
2.50
2.61
1162.5
1294.2
1482.1
1563.5
1611.9
1660.4
Test 363-8.211 was initiated at 0932 hours on
June 29, 1982. The compressor was operated continuously on oxygen for 82 hr at 95%, 105%, and 110%
speed. Performance data were taken at the following
ratios:
Speed
95%
Pressure
Ratio
Compressor Discharge
Pressure
(Sequence 8)
(psig)
1.75
1.93
1122
1228
The objectives of the oxygen performance test
were to evaluate the mechanical performance of the
compressor and to verify the thermodynamic performance
at the following four speeds: 12,635 (95%), 13,300
rpm (100%), 13,965 rpm (105%), and 14,630 rpm (110%).
The only critical speed of the compressor within the
operating range was 8,100 rpm.
The compressor seal leakage (oxygen) during the
oxygen performance test was 0.79 kg/sec (1.73 lb/sec)
at 95% speed, 0.78 kg/sec (1.71 lb/sec) at 100% speed,
and 0.78 kg/sec (1.72 lb/sec) at 105% speed. During
the maximum suction pressure test (752 psia inlet/1956
psig outlet), the oxygen seal leakage was 0.92 kg/sec
(2.02 lb/sec).
The oxygen flow range for the compressor can be
seen in Figure 9 along with the actual performance
data (total pressure versus suction volume) that was
obtained from the performance test plotted against the
predicted performance. The predicted performance was
provided by Mannesmann Demag.
Compressor shaft stability during the test series
was very good. During the maximum suction pressure
test, shaft vibration was as follows:
3.98 um peak-to-peak
Coupling side X-axis
Coupling side Y-axis
5.85 um peak-to-peak
Thrust bearing side X-axis 10.35 um peak-to-peak
Thrust bearing side Y-axis
8.74 um peak-to-peak
The axial shaft position was at a constant
-0.17 mm.
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FIG. 9 OXYGEN PERFORMANCE TEST DATA PLOT, TOTAL PRESSURE RATIO VERSUS SUCTION VOLUME
APPENDIX
High-Pressure
GN2, Pressure
Ratio = 2.27
Oxygen
Performance,
Pressure
Ratio = 2.61,
100% Speed
Oxygen
Performance,
Pressure
Ratio = 2.38,
95% Speed
Oxygen
Performance,
Pressure
Ratio = 2.83,
105% Speed
Maximum Suction Pressure,
1612 h,
752 psia In,
1956 psia Out
First Stage Inlet
Flow rate [kg/s (lb/s)]
11.64 (25.66)
10.98 (24.20)
10.92 (24.06)
11.97 (26.38)
15.74 (34.69)
Density [kg/m 3 (lb/ft 3 )]
60.37 (3.77)
57.42 (3.58)
59.11 (3.69)
57.10 (3.56)
67.72 (4.23)
Pressure [bar (psia)]
54.83 (795.01)
44.23 (641.30)
45.30 (656.90)
43.99 (637.83)
51.84 (751.68)
Temperature [°C (°F)]
33.02 (91.43)
Enthalpy [kJ/kg (Btu/lbm)] 307.06 (132.01)
30.17 (86.30)
29.00 (84.19)
30.17 (86.31)
29.49 (85.08)
265.62 (114.20)
264.20 (113.58)
265.69 (114.22)
263.13 (113.13)
11.81 (26.04)
11.62 (25.62)
12.93 (28.50)
16.70 (36.82)
First Stage Outlet
Flow rate [kg/s (lb/s)]
12.35 (27.23)
Density [kg/m 3 (lb/ft 3 )]
78.24 (4.88)
78.51 (4.90)
78.30 (4.89)
79.94 (4.99)
93.08 (5.81)
Pressure [bar (psia)]
89.14 (1292.52)
77.11 (1118.10)
74.99 (1087.39)
80.15 (1162.17)
91.01 (1319.62)
Temperature [°C (°F)]
100.09 (212.17)
105.32 (221.58)
96.85 (206.33)
112.40 (234.32)
103.58 (218.45)
Enthalpy [kJ/kg (Btu/lbm)] 377.82 (162.43)
335.03 (144.04)
326.76 (140.48)
341.80 (146.95)
331.41 (142.48)
Pressure ratio
(first stage)
1.63
1.74
1.66
1.82
1.76
Gas power (kW)
(first stage)
829.90
774.85
690.16
929.55
1088.66
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Li
High-Pressure
GN2, Pressure
Ratio = 2.27
Oxygen
Performance,
Pressure
Ratio = 2.61,
100% Speed
Oxygen
Performance,
Pressure
Ratio = 2.38,
95% Speed
Oxygen
Performance,
Pressure
Ratio = 2.83,
105% Speed
Maximum Suction Pressure,
1612 h,
752 psia In,
1956 psia Out
Second Stage Inlet
Flow rate [kg/s (lb/s)]
12.35 (27.23)
11.81 (26.04)
11.62 (25.62)
Density [kg/m3(lb/ft 3 )]
94.06 (5.87)
98.46 (6.15)
95.79 (5.98)
101.85 (6.36)
115.24 (7.19)
Pressure [bar (psia)]
88.68 (1285.92)
76.54 (1109.80)
74.47 (1079.78)
79.58 (1153.85)
90.11 (1306.59)
Temperature [°C (°F)]
41.41 (106.53)
35.91 (96.64)
35.76 (96.38)
37.45 (99.41)
38.38 (101.09)
264.07 (113.53)
264.37 (113.66)
265.02 (113.94)
263.76 (113.40)
Enthalpy [kJ/kg (Btu/lbm)] 310.95 (133.68)
12.93 (28.50)
16.70 (36.82)
Second Stage Outlet
Flow rate [kg/s (lb/s)]
10.82 (23.84)
10.28 (22.67)
10.20 (22.48)
11.28 (24.86)
14.91 (32.86)
Density [kg/m 3(lb/ft 3 )]
111.13 (6.94)
121.60 (7.59)
115.97 (7.24)
128.31 (8.01)
142.70 (8.91)
Pressure [bar (psia)]
124.70 (1808.12) 115.46 (1674.11) 107.61 (1560.40) 124.45 (1804.56) 134.91 (1956.24)
Temperature [°C (°F)]
89.62 (193.31)
93.47 (200.25)
86.48 (187.66)
99.99 (211.99)
91.54 (196.78)
Enthalpy [kJ/kg (Btu/lbm)] 362.68 (155.92)
317.66 (136.57)
311.40 (133.88)
323.37 (139.02)
313.05 (134.59)
Pressure ratio
(second stage)
1.41
1.51
1.45
1.56
1.50
Gas power (kW)
(second stage)
591.53
585.78
507.29
699.72
772.00
Total Pressure Ratio (meas.) 2.27
2.61
2.38
2.83
2.60
Overall Gas Power (kW)
1360.63
1197.46
1629.26
1860.66
97.81 (208.07)
1421.43
Bearing Temperatures
[°C (°F)]
Thrust outside
103.25 (217.86)
89.69 (193.44)
93.57 (200.43)
91.45 (196.62)
Thrust outside
97.34 (207.22)
85.58 (186.05)
87.81 (190.06)
87.11 (188.79)
93.81 (200.85)
Thrust inside
57.39 (135.31)
56.34 (133.41)
54.34 (129.82)
58.80 (137.84)
57.51 (135.52)
Thrust inside
57.75 (135.94)
56.69 (134.04)
54.70 (130.45)
58.92 (138.05)
57.75 (135.94)
Journal NOE
59.85 (139.74)
59.27 (138.68)
57.28 (135.10)
62.31 (144.16)
61.73 (143.11)
Journal DE
61.02 (141.84)
59.39 (138.89)
57.86 (136.15)
61.49 (142.69)
59.97 (139.95)
Coupling side X-axis
7.67
8.10
6.37
8.39
3.76
Coupling side Y-axis
9.04
8.22
7.11
9.11
5.85
Shaft Vibration (um)
Thrust bearing side X-axis 12.50
11.86
10.59
12.98
10.27
Thrust bearing side Y-axis 9.98
10.88
10.55
9.81
8.49
Axial shaft position (mm)* -0.21
-0.16
-0.18
-0.15
-0.18
*Motion to coupling side - positive sign
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