performance test
DESCRIPTION
performance testTRANSCRIPT
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
1 Added client comments 2004-03-23 HKL GH
Description: Type 2 Performance Test Procedure Compressor LC1379
- First issue 2004-02-05 HKL GH Document no.: Rev.: Page no.:
Rev. Alterations Date By Check Auth. 10030365 1 1 / 28
Performance Test Procedure Procedure Engineering Department
TYPE 2 PERFORMANCE TEST PROCEDURE FOR A CENTRIFUGAL GAS COMPRESSOR COMPRESSOR TYPE 08MV8B SDDH ORDERNR: LC1379
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
2 / 28
Performance Test Procedure
Engineering Department
CONTENTS -
NOTATIONS......................................................................................................................................................... 3
INDICES ................................................................................................................................................................ 4
1 GENERAL INFORMATION ....................................................................................................................... 6
2 SPECIFIED OPERATING CONDITIONS ................................................................................................ 6
3 CONDITIONS OF TEST .............................................................................................................................. 6
4 CALCULATIONS TEST / SPECIFIED PERFORMANCE PARAMETERS. ....................................... 7
5 METHOD OF MEASUREMENT AND USED INSTRUMENTS............................................................. 9
6 COMPUTATION OF RESULTS ............................................................................................................... 10
7 TEST RUNS.................................................................................................................................................. 11
8 USED FORMULA........................................................................................................................................ 12
9 MEASURING TOLERANCES .................................................................................................................. 21
TEST SETUP....................................................................................................................................................... 24
TESTDATA SECTION 1.................................................................................................................................... 25
TESTDATA SECTION 2.................................................................................................................................... 27 Literature [1.] ANSI/ASME Power Test Code 10-1997 [2.] ISO 5167 Measurement of fluid flow by means of orifice plates, nozzles and venturi tubes inserted in
circular cross-section conduits running full. [3.] API Standard 617. Centrifugal Compressors for General Refinery Service. sixth Edition, Feb 1995. [4.] Thermodynamic properties in S.I., Department of Mech. Engineering, Stanford University by W.C. Reynolds. [5.] The polytropic analysis of centrifugal compressors, by John M. Schultz. [6.] Equation of State BWRS Fluid Thermodynamic properties for light Petroleum systems. K.E. Starling. [7.] Thermodynamic properties of R134a (1,1,1,2-Tetrafluoroethane) M.L. Huber and Mark O. Linden,
Thermophysics Division National Institute of Standards and Technology Boulder C) 80303-3328 U.S.A. [8.] Equations of State Exactly Representing the phase Behaviour of pure substances. E. Bender, Ruhr
University, Bochum, Germany. [9.] VDI 2045 part 1, Acceptance and Performance Tests on Turbo Compressors and Displacement
Compressors. Appendix: ICAAMC Correction method for the influence of Reynolds Number on the Performance of Centrifugal Compressors.
[10] BPBP Berliner Prozess Berechnungs Paket, Techische Universitat Berlin,1988. Prof. H. Knapp.
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
3 / 28
Performance Test Procedure
Engineering Department
NOTATIONS Symbol Description SI Units
bi C c cp cv ck
Tip width first impeller Coefficient of discharge Specific heat Specific heat at constant pressure Specific heat at constant volume Derived inverse sp. heat at const. pressure
m - kJ/kg.K kJ/kg.K kJ/kg.K kg.°C/kJ
do Do Dimp Di Dd dp dt
Throat diameter orifice Flow measuring pipe diameter Diameter first impeller Measuring station at inlet Measuring station at discharge Differential pressure Differential temperature
m m m m m bara °C
f Fa g H
Polytropic head factor Thermal expansion coeff. at orifice Acceleration due to gravity Head; Enthalpy
- - m/s2 kJ/kg
k ln
Ratio specific heats cp/cv of a real gas Naperian (natural) logarithm
- -
m M Mm N np ns
Pol. exp. for a path on the p-t diagram Molecular weight Machine Mach number Speed Pol. exp. for a path on the p-v diagram Isentr. exp. for a path on the p-v diagram
sp v
n =kY
= c / cY
- kg/kmol - rpm - -
p P Pm Pr Pse qv qm
Pressure Power Total mech. losses (equivalent) Ext. heat losses from casing & adjoining piping Seal losses Volume flow rate Mass flow rate
bara kW kW kW kW m3/s kg/s
R Ra Rem rp s Sc t
Gas constant Absolute gas constant Machine Reynolds number Pressure ratio Entropy Enveloped area compressor casing Temperature
J/kg.K J/kmol.K - - kJ/kg.°C m2 °C
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
4 / 28
Performance Test Procedure
Engineering Department
Symbol Description SI Units
T u U V v X Y Z
Absolute temperature Internal energy Blade tip speed Velocity Specific volume Compr. function of compressor process Compr. function of compressor process Compr. factor
K J/kg m/sec m/s m3/kg - - -
α αr
η µ υ ρ σ
Flow coefficient orifice Heat radiation factor Diameter ratio flowmeter Expansion factor flowmeter Linear expansion coefficient Efficiency Dynamic viscosity Kinematic viscosity Specific density Measuring tolerance
- W/(m2.°C) - - m/(mK) - Ns/m2 m2/s kg/m3
-
φ Volume flow coefficient
uD
q
imp
iv
××=
2
,
4πφ
-
Ψ Head coefficient
2/2uHp=ψ
-
INDICES
Indices Description
a abs b be c co D dyn g ge imp m Me o oil p r s se sp st t
Ambient Absolute Atmospheric Bearing Compressor-housing Coupling Pipe diameter Dynamic Gas Gearbox Impeller Mass Mechanical Orifice Oil Polytropic Radiation Isentropic Seal Specified Static Test
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
5 / 28
Performance Test Procedure
Engineering Department
Indices Description tot u v i d
Total Peripheral Volume Suction conditions Discharge conditions
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
6 / 28
Performance Test Procedure
Engineering Department
1 GENERAL INFORMATION A type -2- aerodynamic performance test will be conducted on a gas compressor for the Salman Oil Field.
The test will be performed at the Siemens Demag Delaval Testbed in Hengelo, according PTC-10, 1997 [1]. The compressor is equipped with a 8-stage bundle, type 08MV8B
At site the compressor will be driven by a Alstom Cyclone Gasturbine through a BHS gearbox
Overall test program:
Order Description Mechanical running test
No load string test
Type I performance test
Type II performance test
Bearing inspection
Gas Leakage test
LC1379 Main rotor x x - - x x
LC1380
Spare rotor x1) - - x x -
1) Mechanical running test will be done in Type 2 performance test setup.
This document describes the type-2 performance test of the spare rotor. 2 SPECIFIED OPERATING CONDITIONS
For the specified and guaranteed operating conditions, see the latest relevant data sheets. The guarantee point is operating case “rated”. Compressor performance characteristics are guaranteed as per API 617[3]
3 CONDITIONS OF TEST The performance curve of the compressor will be determined by a test classified as type-2 acc. ASME
PTC-10, 1997 and fully in accordance with the contract specifications including API 617, 6th edition, February 1995. [3]
The test will be carried out in a closed loop arrangement with test gas mixture of 85% CO2 and 15% R134a.
Some relevant properties of the testgas:
Description Units CO2 R134a Mixture Critical pressure bara 73.8 40.56 64.1 Critical temperature K 304.2 374.18 314.4 Mol. weight Kmol/kg 44.01 102.03 52.71
The calculations of the test results measured with the test gas mixture will be done with the equations,
given in literature [6].
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
7 / 28
Performance Test Procedure
Engineering Department
4 CALCULATIONS TEST / SPECIFIED PERFORMANCE PARAMETERS. 4.1 GENERAL Type-2 tests are conducted subject to the limits of Table 3.2 of PTC10.[1] The calculated values of the test and specified parameters in the next sections are given on pages 25 thru 28. 4.1.1. Volume ratio gas at test / design conditions The polytropic exponent nd for the design gas is determined from:
( )( )
+
==
i
d
dd
ii
i
d
spdi
spidspp
pp
nxTzxTz
n
pp
n
vvn
ppnn
11
1
/1
/1.. acc. PTC-10, Eq.n0 [5.2T-7]
The polytropic exponent nt for the test gas is determined from:
+×
×= mean
sppp
mean XcM
zm
)(
134.8314η acc. PTC 10 [5. 3. 9]
[ ]meanmeant XmY
n+−
=11
acc PTC 10 [5. 3. 8]
At a test/specified speed ratio, the pressure ratio rp.t at test conditions can be derived from:
sp
t
NN [ ]
[ ]
2/1
2/11
...
1
...2/1
2/1,
,
11
Re11Re
−×××××−
× −×××××−
=×
=−
−
sp
nn
spptspispisp
corrt
nn
tpsptitit
spp
corrtp
rMTZfn
n
mrMTZfn
n
W
mW
acc. PTC-10; Eq.no. 5.3.1/2/3 The volume ratio over the compressor at test and specified conditions becomes now:
[ ] [ ]specifiedvdvitestvdvi qqqq // = = sp
np
t
np rr
=
11
acc. PTC 10 Eq.no [5.3.4] and [5.3.5]
4.1.2. Calculation of Mach number
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
8 / 28
Performance Test Procedure
Engineering Department
2/12/134.8314
6034.8314
×
×××
××=
×
××=
MYTzk
ND
MYTk
UMm
i
iii
imp
i
ii
π acc. PTC-10;Eq no [5. 5 .3]
4.1.3 Calculation of Reynolds number
i
i
impimp
i
iimp
i
ibND
v
bND
vbu
m
ρµ
ππ
×
×××=
××××
=×
=6060
Re acc. PTC-10;Eq no [5. 5 .4]
4.1.4. Calculation Flow Coëfficient
232
460.
460
.. πρππρ
φ ×××
=××
=impi
m
impimp
i
m
DNq
DND
q acc. PTC-10;Eq no [5. 2T-1]
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
9 / 28
Performance Test Procedure
Engineering Department
5 METHOD OF MEASUREMENT AND USED INSTRUMENTS The closed loop system will be designed and installed according ASME POWER TEST CODE PTC-10,
1997 [1] see page 24. 5.1 Mass flow The mass flow of the compressor will be measured by means of a concentric square edge orifice
according ISO 5167 [2]. 5.2 Pressures and temperatures Static pressure and temperature measuring stations at the inlet and discharge of the compressor will be
located as mentioned in chapter 4 of PTC-10 [1]. Static pressure, differential pressure and temperature measuring stations at the flow measuring device are
located as mentioned in ISO 5167-1 [2]. The temperatures will be measured by means of iron constantan (J) thermocouples. Static pressures will be measured by means of absolute pressure transducers. Differential pressures will be measured by means of differential pressure transducers. The output signals of the transducers and the thermocouples are fed into an automatic data acquisition
system. 5.3 Power at coupling The gas power at test is calculated from the mass flow and the temperature rise of the gas. The mechanical losses of the compressor will be calculated from the measured values of the temperature
rise of the oil and the amount of oil. 5.4 Speed The speed signal is taken directly from the shaft keyphasor and the output of the speed monitor is fed into
the data logging system. 5.5 Calibration Instruments will be calibrated with standards traceable to international standards. Updated certified instrument calibration sheets will be available prior to actual testing.
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
10 / 28
Performance Test Procedure
Engineering Department
6 COMPUTATION OF RESULTS 6.1 Flow The suction volume of the compressor is calculated from the mass flow and the density of the gas at the
suction. The density at the inlet is calculated with the aid of the total inlet pressure and temperature. The suction volume (capacity) varies directly with the speed for conversion to specified speed.
Reynolds correction on head and efficiency will be applied acc. the correction method for the influence of Reynolds Number on the performance of a compressor between test and specified conditions, acc PTC-10,1997 para. 5.6.3.
t
sptvspv N
Nqq ×= .. [m3/hr]
6.2 Head The polytropic head at the test will be calculated from inlet- and discharge conditions, and converted to a
work-input coefficient. The polytropic head varies with the square of the speed for conversion to specified speed.
corrt
sptpspp m
N
NHH Re
2
.. ×!"#$%&
×=
[kJ/kg] 6.3 Efficiency The gas efficiency on a polytropic basis will be calculated.
corrtpspp mRe.. ×≡ ηη
6.4 Power
The gas efficiency on a polytropic basis will be used to calculate the gas power at specified conditions with capacity and polytropic head.
( ) ''()
**+, ×=
spp
sppspmspgas
HqP
.
... η
[kW]
For the shaft power, at the coupling of the compressor, mechanical losses have to be added. The
mechanical losses vary with the speed to the power 2.5.
( ) ( )P PN
Nmech sp mech tsp
t. .
.
= ×
-./
0132 2 5
[kW]
6.5 Expected error of measurements The accuracy of the direct measurement magnitudes will be: Pressure : ± 0.3 % Abs. temperature : ± 0.35°C (premium-grade thermocouple, type J calibrated condition) Speed : ± 0.1 % Test gas analysis : ± 0.25 % (molweight) The accuracy of the specified characteristics at guarantee point will be:(for details see page 26&28)
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
11 / 28
Performance Test Procedure
Engineering Department
7 TEST RUNS The loop will be evaporized and filled with the test gas. Operating conditions of all points to be measured are given in the table below.
OPERATING TEST CONDITIONS
Section -1-
Section -2-
Specified speed
rpm 9800
=∧ 70%
13919
=∧ 99.4%
14700
=∧ 105%
9800
=∧ 70%
13919
=∧ 99.4%
14700
=∧ 105%
Test speed rpm 6900 9800 10350 6900 9800 10350
Test inlet Press.
bara 2 2 2 6.5 6.5 6.5
Test inlet temperature
oC 35 35 35 35 35 35
Test discharge Press.
bara 4 7.3 9 18 24.5 28
Power kW 250 500 550 350 600 700
On the 99.4% speedline 5 measuring points will be taken; maximum flow, between maximum flow and guaranteed operating point, guaranteed operating point, between guaranteed operating point and surge, surge. On the 70% & 105% speedline 3 measuring points will be taken; maximum flow, between maximum flow and surge, and surge.
Two or more trials will be made to detect surge at all speedlines of 105% ; 99.4% and 70%. A test point to indicate the minimum stable capacity shall be set as close to the surge as possible. The reliability of the determination shall be demonstrated by repeating the setting. During the stabilising interval for each test point the temperature rise and its drift can be shown on the computer screen. The time necessary for stabilising depends on the size of the machine and on the temperature. The data for the test point are gathered with 60 scans equally spread over 5 minutes i.e. one scan every 5
seconds. The duration of one scan is approx. 1 sec. (with one scan all data are gathered). The allowable temperature drift over 10 minutes is 5% of the temperature rise of the gas over the compressor. 7.2 Report Aerodynamic performance: The report will comprise the following information: - Summary and conclusions on front page - Signed measuring point data
- Hand calculation of the design point. - Converted Performance test curves showing 70%, 99.4% and 105% speed and surgeline.
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
12 / 28
Performance Test Procedure
Engineering Department
8 USED FORMULA Equation of state [4] 8.1 TESTCONDITIONS 8.1.1. Barometric pressure p measuredb = ( ) N/m2
8.1.2. Orifice upstream pressure p measuredo st. ( )= N/m2
8.1.3. Diameter ratio orifice throat and measuring pipe
β = dD
o
o
-
8.1.4. Expansion factor orifice (acc. ISO 5167 )
( )stoos
o
pndp
..
435.041.01×
+−= βε
p dpo st o. + → measured values
ns o. = to be determined from equation of state.
8.1.5. Density at orifice
ρ oo st
o t o
p MT z
= ×× ×
.
..8314 34 kg/m3
toto tT .. 15.273 += K
)(. measuredt to = °C Zo = to be determined from equation of state.
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
13 / 28
Performance Test Procedure
Engineering Department
8.1.6. Thermal expansion coefficient at orifice
( )[ ]F ta o o t= + −1 202λ . -
8.1.7. Discharge coefficient orifice (acc. ISO 5167)
75.065.281.2
Re10
0029.01840.00312.05959.0 456789
+−+=D
C βββ
( ) 3'2
1441 0337.010900.0 βββ LL −−+ −
where:
0'21 == LL
and:
Re
.
Do
o
m t
o o
o
o
o
V Dv
q
DD
= × =× ×
:;<<<
=>??? ×
ρ π
µρ
42
Startvalue of ReD = 1.0 x 106 ReD to be determined with the calculated value of qm.t. If the deviation between the assumed and the calculated value of ReD is less than 0.05%, the value of qm.t and ReD will be fixed. 8.1.8. Mass flow orifice (acc. ISO 5167-1)
[ ] ( ) 2/122/14. 2
41 oooatm dpdFC
q ρεπβ
×××××××−
= kg/s
8.1.9. Static inlet pressure
)(. measuredp sti = N/m2
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
14 / 28
Performance Test Procedure
Engineering Department
8.1.10. Density at inlet (acc. PTC-10 5.4.2)
ii
stii zT
Mp××
×=
34.8314.ρ kg/m3
ii tT += 15.273 K
)(measuredt i = °C
=iz to be determined from equation of state. 8.1.11. Inlet volume flow
i
tmiv
ρ.
. = m3/s
8.1.12. Inlet mass flow
iivtm qq ρ×= .. kg/s 8.1.13. Dynamic inlet pressure (acc. PTC-10 5.4.4)
2
2
..
421
@@@@
A
BCCCCD
E
××=
i
ividyni
D
qp πρ N/m2
8.1.14. Static discharge pressure
)(. measuredp std = N/m2
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
15 / 28
Performance Test Procedure
Engineering Department
8.1.15. Density at discharge (acc. PTC-10 [5.4.2])
dd
stdd zT
Mp××
×=
34.8314.ρ kg/m3
dd tT += 15.273 K
)(measuredtd = °C
=dz to be determined from equation of state. 8.1.16. Dynamic discharge pressure (acc. PTC-10 5.4.4)
2
2
..
421
FFFF
G
HIIIIJ
K
××××=
dd
tmddynd
D
qp πρ
ρ N/m2
8.1.17. Total inlet pressure
dynistitoti ppp ... += N/m2
8.1.18. Total discharge pressure
dyndstdtotd ppp ... += N/m2
8.1.19. Pressure ratio over the compressor
totitotdp ppr .. /= N/m2
8.1.20. Isentropic exponent
i
sd
ps
In
rInn
ρρ .
= -
For ρd.s and ρi (calculated with equation of state)
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
16 / 28
Performance Test Procedure
Engineering Department
8.1.21. Isentropic head
disd HHH ''. (calculated with equation of state) kJ/kg 8.1.22. Isentropic efficiency
id
isds HH
HH−−
= .η -
8.1.22a. External radial heat losses: Radiation and Convection (acc. PTC-10 [ 5.4.16])
[ ] raccr ttSP α−= kW Sc = 10.4 m2 αr = 0.14 KW/(m2.K.S) 8.1.22b. Corrected isentropic efficiency: (with Radiation and Convection heat)
)(1
1
.
)(
idtm
r
s
corrs
HHqp
−+
=
η
η -
8.1.23. Polytropic work factor (acc. PTC-10 equation [5.4T-10])
[ ]itotisdtotds
s
isd
vpvpn
nHH
f×−×
−
−=
...
.
1
-
8.1.24. Polytropic exponent (acc. PTC-10 equation [5.4T-11])
i
d
p
In
rInn
ρρ= -
8.25. Polytropic head (acc. PTC-10, [5.3.3])
itotin
n
ptp vprn
nfH ××
LMNOPQ
−×−
×=−
.
1
. 1)(1
kJ/kg
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
17 / 28
Performance Test Procedure
Engineering Department
8.1.26. Polytropic efficiency (acc PTC-10 Eq.no [5.2.T-9])
)(.
.. cors
isd
tptp HH
Hηη ×
−= -
8.1.27. Mechanical losses Bearings:
oiloilvoiloiltm qdtQ ρα ×××= .. kW
α oil = 2 0. kJ/kg°C
ρ oil = 800 kg/m3
qv oil. = volume of oil flow (measured) m3/s
oildt = temperature rise oil (measured) °C Seals:
Power loss of seals will be taken from manufacturer data. 8.1.28. Gas power
Pq H
g tm t p t
p.
. .=×η
kW
8.1.29. Machine Reynolds number (acc. PTC-10, [5.5.4])
t
ii
vbND
m RSTUVW×
×××=60
Reπ
-
8.1.30. Machine Mach-number (acc. PTC-10, [5.5.3])
[ ]tiiis
i
TzRn
NDMm XY
Z[\]×××
××= 2/1.60π
-
8.1.31. Volume ratio of flow over the compressor (acc. PTC-10, [5.5.5])
[ ] [ ]t
nptdviv rqq ^_`abc=1
.. / -
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
18 / 28
Performance Test Procedure
Engineering Department
8.2 SPECIFIED CONDITIONS 8.2.1. Specified inlet volume flow
qt
sptvspv N
Nqq Re.. ××=
m3/hr
8.2.2. Specified polytropic efficiency
ηηη Re.. ×= tpspp
8.2.3. Specified polytropic head
Ht
sptpspp N
NHH Re
2
.. ×de
fghi×=
kJ/kg
The factors cp.d and ck.d have been calculated with the aid of the compressor design data bank using the real gas equations for the given design gas.
dp
pdp dt
Hc jjk
lmmno ×= 1
. η kJ/KG.°C
di
dp
i
d
dk
TT
H
dtpp
c pppp
q
r
sssst
u
×
×=
log
log
. kg°C/KJ
Where didd TTdt .. −= °C
8.2.4. Specified temperature difference
spp
spp
sppsp
H
cdt
.
.
.
1η
×= °C
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
19 / 28
Performance Test Procedure
Engineering Department
8.2.5. Specified pressure ratio
Ω=vw
xyz= 10.
i
dspp p
pr -
where:spspi
spspisppspk dtT
dtTHc
1log
.
... ×
+××=Ω
This formula has been derived from:
[ ]spid
idsppspkspid TT
TTHcTT |
~−
××=/
log/log .. -
8.2.6. Specified discharge pressure
spisppspd prp ... ×= N/m2
8.2.7. Specified discharge temperature
spispspd TdtT .. += K
8.2.8. Specified mass flow
spispvispm qq ... ρ×= kg/s
where:
spispi
spspispi Tz
Mp
..
.. 34.8314 ××
×=ρ kg/m3
8.2.9. Specified gas power (acc. PTC-10 [5.4.13])
spp
sppspmspg
HqP
.
... η
×= kW
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
20 / 28
Performance Test Procedure
Engineering Department
8.2.10. Specified mechanical losses (acc. PTC-10 [5.6.8])
tmt
spspm P
N
NP .
5.2
. ×
= kW
8.2.11. Shaft power compressor (acc. PTC-10 [5.4.14])
spsespmspgspsh PPPP .... ++= kW
8.2.12. Specified machine Reynolds number (acc. PTC-10 [5.5.4])
sp
ispisp v
bNDm
××××
=60
Reπ
-
8.2.13. Specified machine Mach-number (acc. PTC-10 [5.5.3])
[ ] 2/1...60 spispispspsi
spisp
zTRn
NDMm
×××
××=
π -
where spi
vp
spi
ispsi Y
cc
Yk
n
=
=/
.
8.2.14. Specified polytropic exponent
spdid
idi
psp
TpZTpZ
rn
××××
=ln
ln -
8.2.15. Specified volume ratio of flow over the compressor
[ ] spnsppspvdspvi rqq1
... / = -
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
21 / 28
Performance Test Procedure
Engineering Department
9 MEASURING TOLERANCES 9.1 Tolerance on mass rate of flow. For the calculated values see attached figure 4. a) Uncertainty of discharge coefficient C (ISO 5167- 8.3.3.1)
cσ = 0.6 % for β ≤ 0.6
cσ = β % for 0.6 < β ≤ 0.75 b) Uncertainty of expansion factor ε. (ISO/5167 - 8.3.3.2)
o
o
pdp×±= 4εσ %
c) Tolerance of measuring pipe diameter
( )valuemeasuredoD 0. ±=σ % d) Tolerance of throat diameter orifice plate
( )valuemeasuredod 0. ±=σ % e) Tolerance of differential pressure orifice plate
3.0. ±=odpσ %
where σdpo = uncertainty differential pressure transducer f) Tolerance of specific inlet density
( )RTipifi
σσσσ ρ ;;=
piσ = ± 0.3 %
tiσ = ± 0.35 °C
10035.0 ×±=i
Ti Tσ %
Rσ = ± 1 % for mix gas
Rσ = ± 0.5 % for pure gas
[ ] 2/1222RTipii
σσσσ ρ ++= %
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
22 / 28
Performance Test Procedure
Engineering Department
g) Tolerance of mass rate of flow (ISO/5167 - 11.2.2)
2/1
2.
2.
2
2
42
2
4
422
41
41
12
12
++
−+
−
++= oodpdDcqm ρε σσσβ
σβ
βσσσ %
h) Tolerance of combined straightener (VDI 2040 Blatt 1, Abschnitt 4.4.5.4) σ str . .= ±0 5 % Tolerance on mass rate of flow
strqmqm σσσ +=
% 9.2 Tolerance on inlet volume flow
[ ] 2/122Nqmqv σσσ +±= %
9.3 Tolerance on polytropic head
( ) →−−
= iiddiip vpvpTRZn
nH .
1 . d
i
i
idp
RTf
ppH
ρρ×
−=
[ ] 2/12222TiRipipdHP
σσσσσ ρ +++= −
a) Tolerance on differential pressure compressor suction discharge
42.03.03.0 22 ±=+=− pipdσ %
b) Tolerance on suction pressure
3.0±=piσ %
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
23 / 28
Performance Test Procedure
Engineering Department
c) Tolerance on gas constant
Rσ = ± 1 % for mix gas
Rσ = ± 0.5 % for pure gas d) Tolerance on suction density.
( )RTipii f σσσσ ρ ;;= %
e) Tolerance on suction temperature
10035.0 ×±=i
Ti Tσ %
f) Tolerance on discharge density
( )RTdpdd f σσσσ ρ ;;= %
3.0±=pdσ %
10035.0 ×±=d
Td Tσ %
9.4 Tolerance on gas power
( ) ( ) ttcHH dpqmidqmp −×=−= ;; σσσσ
0.1=pcσ (gas mixture), 3.0=
pcσ (pure gas) %
10035.035.0 22
×−+=−
idtitd TT
σ %
9.5 Tolerance on speed of rotation
1.0=Nσ %
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
24 / 28
Performance Test Procedure
Engineering Department
TEST SETUP
Item Description T11 Suction temperature section 1 P11 Suction pressure section 1 T12 Discharge temperature section 1 P12 Discharge pressure section 1 T13 Temperature before flow orifice section 1 P13 Pressure before flow orifice section 1 PD13 Differential pressure over flow orifice section 1 T21 Suction temperature section 2 P21 Suction pressure section 2 T22 Discharge temperature section 2 P22 Discharge pressure section 2 T23 Temperature before flow orifice section 2 P23 Pressure before flow orifice section 2 PD23 Differential pressure over flow orifice section 2
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
25 / 28
Performance Test Procedure
Engineering Department
TESTDATA SECTION 1 TEST DATA FOR PERFORMANCE TEST
Customer: Salman Orderno: LC1379 Type: 08MV8B
Contractor: Section 1 Operation
Description Units Specified Test Case of operation Rated Gas Composition design gas 85% CO2 / 15%R134a
Moleculair Weight Gas MW kg/kmol 25.68 52.712
Isentropic exponent ns 1.18 1.236
Polytropic exponent np 1.25 1.28
Rate of inlet volume flow qv1 am3/hr 6414 4516 Mass rate of flow m kg/hr 77707 18803
Inlet pressure pi bara 12.3 2
Inlet temperature ti °C 54 35
Inlet compressibility factor zi 0.96 0.988 Inlet density ρ kg/m3 12.10 4.16
Discharge pressure pd bara 43 7.27
Discharge temperature td °C 151.00 137.80
Discharge compressibility factor zd 0.95 0.985
Discharge density ρd kg/m3 32.96 11.379 €
Speed Ν rpm 13919 9800
Speed ratio Ντ / Νd % 0.70 Polytropic head H Kj/kg 144.60 71.82 Polytropic efficiency η % 78.2 78.2 Gaspower Pgas KW 3991.3 484
Pressure ratio rp = pd / pi 3.50 3.63
Specific volume ratio rv = vi / vd 2.722 2.733 Machine Machnumber Mm 0.793 0.798 Machine Reynoldsnumber Rem 4.265E+06 1.035E+06
Flowcoefficient φi 4.610E-01 4.610E-01 Dyn.viscosity µ kg/(s.m) 1.200E-05 1.560E-05
Specific heat factor at p=const. cpmean J/(kg.°C) - 936.1
Diameter first impeller Di mm 377
Exit tip width first impeller bi mm 15.4 Compressibility function [5] (X1+X2)/2 0.052 Compressibility function [5] (Y1+Y2)/2 1.0119
Reyn.corr.factorPTC-10 on Qv % 1.000
Reyn.corr.factorPTC-10 on Hpol % 1.008
Reyn.corr.factorPTC-10 on Ethapol.t % 1.008
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
26 / 28
Performance Test Procedure
Engineering Department
Description Units PTC-10 Limits Test
Specific volume ratio rv.t / rv.sp 0.95<--->1.05 1.00
Machine Mach number ratio Mm.t - Mm.sp acc.PTC-10-1997 -0.06< >+0.08 0.005
Machine Reynolds number ratio Rem.t/Rem.sp acc.PTC-10-1997 0.10 : 20 0.243
Flowcoefficient ratio φt /φsp 0.96<--->1.04 1.000
MEASURING TOLERANCES FOR PERFORMANCE TEST Customer: Salman Orderno: LC1379
Type: 08MV8B Contractor: Stage: 1
Operation Description Units Tolerance +/- Unit
Inlet/discharge pressure p bara 0.3 % Inlet/discharge temperature t °C 0.35 °C
Upstream pressure orifice p bara 0.3 %
Differential pressure orifice dp mbar 0.3 %
Orifice temperature t °C 0.35 °C
Section 1:
Rate of mass flow m kg/hr 0.92 %
Rate of inlet volume flow qv1 am3/hr 0.93 % Polytropic Head H kJ/kg 0.7 % Power P kW 0.99 % €
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
27 / 28
Performance Test Procedure
Engineering Department
TESTDATA SECTION 2 TEST DATA FOR PERFORMANCE TEST
Customer: Salman Orderno: LC1379 Type: 08MV8B
Contractor: Section 2 Operation
Description Units Specified Test Case of operation Rated Gas Composition design gas 85% CO2 / 15%R134a
Moleculair Weight Gas MW kg/kmol 25.76 52.712
Isentropic exponent ns 1.21 1.266
Polytropic exponent np 1.41 1.40
Rate of inlet volume flow qv1 am3/hr 1703 1199.00 Mass rate of flow m kg/hr 74075 16684
Inlet pressure pi bara 40.5 6.5
Inlet temperature ti °C 58.5 35
Inlet compressibility factor zi 0.87 0.961 Inlet density ρ kg/m3 43.49 13.92
Discharge pressure pd bara 153.7 24.48
Discharge temperature td °C 181.00 173.43
Discharge compressibility factor zd 0.94 0.966
Discharge density ρd kg/m3 111.55 35.97 €
Speed Ν rpm 13919 9800
Speed ratio Ντ / Νd % 0.70 Polytropic head H Kj/kg 149.30 75.32 Polytropic efficiency η % 60.7 60.7 Gaspower Pgas KW 5061 580
Pressure ratio rp = pd / pi 3.80 3.77
Specific volume ratio rv = vi / vd 2.575 2.585 Machine Machnumber Mm 0.877 0.87 Machine Reynoldsnumber Rem 7.469E+06 1.685E+06
Flowcoefficient φi 1.220E-01 1.220E-01 Dyn.viscosity µ kg/(s.m) 1.200E-05 1.528E-05
Specific heat factor at p=const. cpmean J/(kg.°C) - 985.6
Diameter first impeller Di mm 404
Exit tip width first impeller bi mm 7 Compressibility function [5] (X1+X2)/2 0.155 Compressibility function [5] (Y1+Y2)/2 1.0372
Reyn.corr.factorPTC-10 on Qv % 1.000
Reyn.corr.factorPTC-10 on Hpol % 1.0079
Reyn.corr.factorPTC-10 on Ethapol.t % 1.0079
eng_portrait Rev.2 - 10/2001 copyright by law
Siemens Demag Delaval Turbomachinery B.V.
Description: Type 2 Performance Test Procedure Compressor LC1379
Document no.: 10030365
Rev.:
1
Page no.:
28 / 28
Performance Test Procedure
Engineering Department
Description Units PTC-10 Limits Test
Specific volume ratio rv.t / rv.sp 0.95<--->1.05 1.00
Machine Mach number ratio Mm.t - Mm.sp acc.PTC-10-1997 -0.04 >+0.07 -0.007
Machine Reynolds number ratio Rem.t/Rem.sp acc.PTC-10-1997 0.10 : 20 0.226
Flowcoefficient ratio φt /φsp 0.96<--->1.04 1.000
MEASURING TOLERANCES FOR PERFORMANCE TEST Customer: Salman Orderno: LC1379
Type: 08MV8B Contractor: Stage: 2
Operation Description Units Tolerance +/- Unit
Inlet/discharge pressure p bara 0.3 % Inlet/discharge temperature t °C 0.35 °C
Upstream pressure orifice p bara 0.3 %
Differential pressure orifice dp mbar 0.3 %
Orifice temperature t °C 0.35 °C
Section 2:
Rate of mass flow m kg/hr 0.70 %
Rate of inlet volume flow qv1 am3/hr 0.71 % Polytropic Head H Kj/kg 0.7 % Power P KW 0.80 % €