GAS TURBINE POWER PLANTS INLET AIR COOLING

1
IMPROVEMENT OF TOTAL POWER OUTPUT
FOR GAS TURBINE POWER PLANTS BY
INLET AIR COOLING
Graduation Project
Submitted To Mechanical Engineering Department-University Of
Technology To Fulfillment Of The Degree Of The Requirements For The Degree
B.Sc In
Mechanical Engineering – General Mechanics
BY
Ahmed Abas Ridha
Supervised By
Dr. Amer AL- Dabagh
2017

2
Acknowledgments
Thanks and gratitude are due
I would like to express my deepest thanks and sincere gratitude my
supervisors Dr. Amer AL- Dabagh for their assistance,to guidance,
encouragement and help throughout the steps of this work
My gratitudealso goes to the staff members of the Mechanical Engineering
Department / University of Technology.
I would like to thank all persons who stood by me and help me to get this
degree especially my father and mother the persons without them I would not
be what I am today

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Table of Contents
Abstract
Nomenclature
Chapter one: Introduction
1.1 Background
1.2 How Do Gas Turbine work
1.3 Gas Turbine Performance
1.4 Claimof this work
1.5 Available Technologies for Turbine Inlet Cooling
1.5.1 Wetted Media Evaporating Cooling and fogging system
1.5.2 Chiller systemof vapor compression cycle
1.5.3 Chiller systemof vapor absorption cycle
1.6 object of this work
Chapter Two: Literature Survey
2.1 Introduction
2.2 Previous studies
Chapter Three: Modeling of Gas turbine
3.1 Introduction
3.2 Gas Turbine (simple type)
3.3 Inlet air cooling model
3.3.1 Evaporating cooling (Fogging)
3.3.2 Vapor Compression chillers
3.3.3 Vapor Absorption chillers
Chapter four: Results and Discussion
Chapter five: Conclusion and Recommendation
References

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Abstract
A gas turbine, also called a combustion turbine, is a type of internal combustion
engine. Ithas an upstreamrotating compressor coupled to a downstreamturbine,
and a combustion chamber or area, called a combustor, in between. the working
fluid is air. through the process we get turbine work which is used to drivethe
compressor and other devices such as an electric generator that may be coupled
to the shaft. gases turbines are used to power aircraft, trains, ships, electrical
generators, and tanks.
The main problemwe have for gas turbine in Iraq thatthe temperatures is too
high and that causes to a decreasing in total power we get fromthe turbine
Significantly becausethe gas turbine works in the samevolumetric flow rate for
all temperature and samerotational speed and in high temperatures the density
of the air is decreased so the mass flow rate entering the turbine is decreased and
the turbine work or power is decreased ,the solvefor this problemis to cool the
inlet air enters the turbine but we need some power to run the systems that cool
that air and the total net power we get and what we spent may be Economically
acceptable and depends on the method we use
In evaporating cooling by fogging air cooled to nearly 28c°but the best conditions
is on 15 c° but it cost a small power consumption
In other methods the chilling methods we spend more power on cooling systems
but we can reach the best temperature which it is 15c°but with more power
needed the net power we get is higher than evaporating cooling the best method
is depends on the costof each systemand power consumption

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Nomenclautre
Cp Specific heat at constant pressure [kj/kg k]
FHV Fuel heating value [kj/kg]
h Specific Enthalpy [kj/kg]
HR Heat rate [kj/kw h]
ṁ Mass flow rate [kg/s]
P Pressure [pa]
Q Heat Transfer Rate [kw]
r Compression pressure ratio [-]
T Temperature [k]
Td Dry bulb temperature [k]
Tw Wet bulb temperature [k]
W Power output [MW]
SFC Specific fuel consumption [kg/kwh]
ɸ Relative humidity [-]
ɣ Specific heat ratio [-]
η Efficiency [-]
Ѡ Specific humidity [kg]
V Volumetric flow rate 𝑚3
/s
W work Kj/s
r.p Pressure ratio [-]

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Chapter One
Introduction
1.1 background
The development of the gas turbine took place in severalcountries. Several
different schools of thought and contributory designs led up to Frank Whittle’s
1941 gas turbineflight. Despite the fact that NASA’s development budget now
trickles down to feed the improvementof flight, land based and marine engines,
the world’s firstjetengine owed much to early private aircraftengine pioneers
and somelower profile land-based developments.Gas turbines haveemerged as a
strong forcein the generation market. Gas and combined cycle power plants
dominate current orders fromelectricity generators. This followed the
development of gas turbines in the 1940s, their emergenceinto the peak power
market in the 1960s, and thegas turbine slump of the late 1970s and 1980s,
during which almostno gas turbines were ordered in the US. This new growth can
be explained by the way that R&D advancements interacted with other drivers to
gas turbine success. Theseother drivers werefuel availability, environmental
concerns, and changing market conditions stemming fromelectrical restructuring
The development of the gas turbine is a sourceof great pride to many engineers
worldwideand, in somecases takes on either industry sector fervor (for instance
the aviation versus land based groups)
Now days gas turbine are most widely used in power generation and Aviation

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1.2 How Do gas turbine work
The basic principle of the airplane turbine engine is identical to any and all
engines that extract energy from chemical fuel. The basic 4 steps for any
internal combustionengine are:
1. Intake of air
2. Compressionof the air
3. Combustion,where fuel is injected and burned to convert the stored
energy.
4. Expansion and exhaust, where the converted energy is put to use. In the
case of a piston engine, such as the engine in a car or reciprocating
airplane engine, the intake, compression,combustion,and exhaust steps
occur in the same place (cylinder head) at differenttimes as the piston
goes up and down.In the turbine engine, however, these same four steps
occur at the same time but in differentplaces.As a result of this
fundamental difference,the turbine has engine sections called:
1. The inlet section
2. The compressorsection
3. The combustionsection(the combustor)
4. The turbine (and exhaust) section.
The turbine sectionof the gas turbine engine has the task of producing
usable output shaft power to drive the generator. In addition, it must also
provide power to drive the compressorand all engine accessories.It does
this by expanding the high temperature, pressure,and velocity gas and
converting the gaseous energy to mechanical energy in the form of shaft
power. A large mass of air must be supplied to the turbine in order to
produce the necessarypower. This mass of air is supplied by the
compressor,which draws the air into the engine and squeezes it to provide
high-pressure air to the turbine. The compressor does this by converting
mechanical energy from the turbine to gaseous energy in the form of
pressure and temperature and this done by many stages contain of fixed
and moving blades the fixed blades work as a nozzle and reduce the high
kinetic energy the deceasing in the speed causes the pressure to increase,
and the moving blades suck the air and give a high kinetic energy to it.
If the compressorand the turbine were 100% efficient,the compressor
would supply all the air needed by the turbine. At the same time, the turbine
would supply the necessary power to drive the compressor.In this case, a

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perpetual motion machine would exist. However, frictional losses and
mechanical system inefficienciesdo not allow a perpetual motion machine
to operate.Additional energy must be added to the air to accommodate for
these losses.Poweroutput is also desired from the engine (beyond simply
driving the compressor);thus, even more energy must be added to the
air to produce this excess power.Energy addition to the system is
accomplishedin the combustor.Chemical energy from fuel as it is burned
is converted to gaseous energy in the form of high temperatures and high
velocity as the air passes through the combustor.The gaseous energy is
converted back to mechanical energy in the turbine by stages of moving
and fixed blades,providing power to drive the compressorand the output
shaft.
As air passes through a gas turbine engine,energy requirements demand
changes in the air’s velocity and pressure.During compression,a rise in
the air pressure is required, but not an increase in its velocity. After
compressionand combustionhave heated the air, an increase in the
velocity of gases is necessaryin order for the turbine rotors to develop
power. The size and shape of the ducts through
which the air flows affectthese various changes. Where a conversionfrom
velocity to pressure is required, the passages are divergent. Conversely, if
a conversionfrom pressure to velocity is needed,a convergentduct is used
Gas turbine components (1.1)

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1.3 Gas turbine performance
The thermodynamic process used in gas turbine is the Brayton cycle two main
parameters that effect on the performanceof this cycle the pressureratio and
the firing temperature the pressureratio depends on the work of the
compressor and it design
And the main other parameter is the firing temperature some turbines are
sensitiveto the inlet temperature which is limited but the higher firing
temperature leading higher to higher efficiency but the high temperature can
be tolerated by the turbine blade metal alloy the temperatures that the
blades can handle about 1200c°to 1400c°but in some cases the reach higher
than that by cooling the blades it may reach 1600c°
Cooling of the blads(1.2)
the combustion turbines are constant-volumeengines and the power output is
directly proportional and limited by the mass flow rate which depends on the
ambient temperature and relative humidity in high temperature means less air
density and that means less mass flow rate and less power because less air pass

10
into the turbine and the performanceof the gas turbine is presented by the
power output and specific fuel consumption and it is sensitive to ambient relative
humidity and ambient temperature increase reduce the thermal efficiency but
the much greater effect is the temperature effect on the efficiency and total
power gain.
1.4 claim of this work
Iraqigovernmentinstalled number of gas turbines power plants in total power of
9000 MW simple gas turbine engines manufactured by GE Mostof these engines
enter the serviceand they handle about 50 % of total national electric generation
during summer in hot day and long days with high demand on electric to run air
conditioning additionally to normalloads the total electric production don’t
satisfy the demand so one of the methods to increasepower in summer is to cool
air inters the compressor to increase power output and in this work weseek the
best possibleway to do it with respect the cost and power gain.
1.5 Available Technology for Gas turbine inlet cooling
1.5.1 Evaporating Cooling (wet media and fogging)
Traditional media based on evaporativecoolers have been widely used in gas
turbine industry for severaldecades especially in hot arid areas the basic principle
of evaporating cooling is that as water evaporates it cools the air becauseof its
latent heat of vaporization.

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Evaporating wet media (1.3)
For the fogging system It’s thesame principle of wet media which it’s the water
evaporates and it cools the air by the heat of evaporation but it can reach the air
too high relative humidity nearly 100 % even in humid conditions the water is
compressed and its sprayed into the air it can boostthe power output from10%
to 20% in hot places
Fogging system (1.4)
1.5.2 Chiller systemof vapor compressioncycle
For this method we can reach the inlet air enters the turbine too the optimum
temperature but we have to spend more energy on it, and the cooling is done
by water inters the cooling coil too cool the air and that water is cooled by the
refrigerantenters the cooling coil we calculate the cooling load which it is the
air fromhot degree to 15 c° and design the chillers loads depends on this
capacity

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In this method we usea compressor to compress the refrigerantto the high
pressure(condenser pressure) and the refrigerantexchange heat with water also
that goes to chilled in a cooling tower so wehave to cycle of water here between
the evaporator and water goes to cool the inlet air and the water with open cycle
goes to cooling tower and the refrigerantcycle.
Chiller cooling coils(1.5)

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1.5.3 Chiller systemof vapor
Absorption chillers are not like mechanical chillers it consistof generator and
absorber and solution pump and valve instead of the compressor in the vapor
compression cycleand consistof the condenser and evaporator also the
electricity in this cycle is only needed to run the solution pump and water pumps
but this cycle need amount of for the solution in the generator to makethe
refrigerantreach the superheated state, the heat of flue gases used to heat up
the generator and a heat exchanger
1.6 object of this work
gas turbine inlet air temperature determine the gas turbine total power gained so
inlet air cooling used to increasethe power output and the mass flow rate will
increase by decreasing the temperature but there is more than a systemused to
cool the air we fine the optimum way with respect that the method must be
economical and efficient also we find the gas turbine performancefor multi
degrees

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Chapter Two
Literature survey
2.1 Introduction
Gas turbine have been used for in recent time in very large numbers and in
different places in the world and in places that the peak load is high in summer
and with high temperatures the gas turbine power net decreases so there is two
main solution for this problem used in hot areas like south united states of
America and Arab gulf region is the fogging systemand mechanical chillers vapor
compression and vapor absorption and this methods was use to gain the highest
power possibleand to be at low investment cost. And this is a table that shows
the changedensity with the temperature rises the density is decrease and that
causes the mass flow rate to decease also and net power
Density and specific weight of air at standard atmospheric pressure - SI Units:
Temperature
- t -
(oC)
Density
- ρ -
(kg/m3)
Specific
Weight
- γ -
(N/m3)
-40 1.514 14.85
-20 1.395 13.68
0 1.293 12.67
5 1.269 12.45

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Temperature
- t -
(oC)
Density
- ρ -
(kg/m3)
Specific
Weight
- γ -
(N/m3)
10 1.247 12.23
15 1.225 12.01
20 1.204 11.81
25 1.184 11.61
30 1.165 11.43
40 1.127 11.05
50 1.109 10.88
60 1.060 10.40
70 1.029 10.09
80 0.9996 9.803
90 0.9721 9.533
100 0.9461 9.278
200 0.7461 7.317
300 0.6159 6.040
400 0.5243 5.142
500 0.4565 4.477

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Temperature
- t -
(oC)
Density
- ρ -
(kg/m3)
Specific
Weight
- γ -
(N/m3)
1000 0.2772 2.719
Density and specific weight change due to temperature (2.1)

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2.2 previous studies
There is too many studies on cooling inlet air and study the effect of cooled air on
turbine performanceparameters and power consumption for the systemand
increasing in the power
Like (1) MeeFog™ System. That shows In this table energy increase
Fogging power increasing in types of gas turbine(2.3)
In (2)MitsubishiHeavyIndustries TechnicalReview Vol. 47 No. 4 (December
2010)
The study shows that

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Effect of air temperature on power output(2.1)
And this table shows different on each method
Comparison shows the performance of each inlet cooling method (2.4)

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and in (3) Gas Turbine Inlet Air Cooling SystemPresented by Bob Omidvar it show the
effect also of cooling and power of each and the relative humidity of air enters the
turbine
(2.5)
Generally the gas turbine works on the same volumetric flow rate any
increase in the temperature the mass flow rate will decrease and power
output nearly in every temperature change the power increase or decrease
about 0

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Chapter three
Modeling of gas turbine

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3.3 inlet air cooling model
3.3.1 Fogging system
The fogging systemusethe water to cool the inlet air enters the compressor by
adding a moisturecontent to the air and cool the air by adiabatic process by
increasing the relative humidity (ɸ) as figure below.
(3.2)
The relative humidity is supposed to reach 100%, by pumps that compress to
about 100 bar.
(3.3)

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ṁw cpw (tw3-tw1)=ṁair hvap (Ѡ3- Ѡ1) (15)
pumps power=V ( ᴧP ) /η isent (16)
3.3.2 vapour compressioncycle
In this cycle the cooled or chilled water came fromevaporator exchange heat with
the inlet air enters to the gas turbine beforethe compressor and in this state the
dry and wet bulb temperature decreases and the relative humidity may be change
also if the temperature go down the dew point.in this cycle we useelectricity to
run the compressor and pumps and fan
(3.4) cycle diagram
And this is the vapour compression components

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(3.6)
And the equations as figure abovewill be
Q condenser(Qc)=ṁref* (h3-h5) (17)
Q evaporator=ṁref (h2-h6) (18)
W compressor=ṁref (h3-h2) (19)
The evaporator chilled water that cooled inlet air to the turbine,and the
condenser load is water that chilled to the cooling tower
Water pumps power = V ᴧp
Cooling tower propeller power = v ᴧp
3.3.3 Vapor absorptionsystem
This cycle also cool a chilled water that exchange heat with the inlet air enters the
turbine in the evaporator also the dry and wet blub temperatures decrease and
humidity but in this cycle the electricity used only to drive pumps and the heat
needed in the generator taken fromexhaust gasses that havea high temperature
(570) in this model the work will be on nh3-h20 solutions
Ref: refrigerant

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(3.7) absorption diagram and components
Condenser
m1 = m2 = m
Qc = m (h7 – h8) (20)
Expansion value
m2 = m4 = m
h2 = h4 (as process is isenthalpic) KJ/kg
Evaporator

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m4 = m5 = m
Qe = m(h5 – h4) KJ/min
Or
Qe = (h5 – h4) KJ/kg vapour (21)
Circulation ratio
f = m9/m1
m9 = m1 + m10
m9X9 = m1 + m10X10
Using above two equations we get
m10 = 1- X9 / X9 – X10
m10 = 1- X10 / X9 – X10
m1 = m9X9 – m10X10 (22)
f = m9/m1
Absorber
Qa = mh5 + mfh12 – (1+f)mh7 (23)
Solution pump
m7 = m8 = mWS
wp = (1+f )mVsolution(pc - pe) KJ/min (24)
where Vsolution = 7.2 x 10-3 m3/kg
Liquid-liquid solution heat exchanger
m2 = m3
m4 = m5
QHX = (1 + f )m(h9 – h8) = mf (h10 – h11) (25)
Generator
m9 = m1 + m10
Heat input to generator is
Qg = m1h1 + m10 h10 - m9h9 (26)
And finally using the above equations systems performance is measured in terms
of coefficient of performance and COP is the ratio of desired effect to the net
energy input to the system
Mathematically,
COP = QE / (wp + Qg) (27)
And we will make the concentration of nh3 in h20 constant at
x7=x8=x9=0.39
x10=x11=x12=0.318

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(3.8) temperature enthalpy diagram used for ammonia water solutions

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Chapter four
Results and Discussion
Pressureratio =11.8
Turbine inlet temperature =1104 c
Turbine exit temperature= 534 c
Air mass flow rate = 138 kg/s
Generator out put =39.6 MW
WBT= 9.6 c
Atm pressure=1.013 bar
Relative humidity =50%
Po (ambient)= po3,inlet to the compressor
Compressor isentropic efficiency =0.85
ɣ air = 1.401 at 15c and 1.4 at 40 c
from the modeling of gas turbine and at T=15,p=1.013 bar,relative
humidity = 50%
Po4= 11.935 bar
TO3=15+273=288 K
To4=635.5 k
Cpair.avg= 1.1987 joule/gram.k
Cpa air.avg: specific heat of dry air at a constant pressure and average
temperature between inlet and outlet sides of compressor.
Power compressor= 57 483.6 kw
Heat added in c.c(combustion chamber):
To5= 1377 k

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Tavg.cc=1006.25
Cpg.avg=1.2108 kj/kg.k
Q c.c= 123 897.5 kj/s
mf = 2.548 kg/s
mgas= mair + mfuel
mg= 140.548 kg/s
Cp gas = 1.2311
WT= 98 626 .7 kw
Wnet = WT-WC
Wnet= 41 143. 1 KW
(ηgenerator)=0.962
Electrical power output= 39 590 kw
S.F.C= 0.233 KG/KW.H
H.R=heat rate
H.R= 11 411.4 kj
(ηthermal)= 0.3019 or 30.19%
This is the turbine performance at high temperature without any
cooling
Performance at dry temperature = 27c and relative humidity 100% for
fogging system calculations:
Po4= 11.953 bar
To3 =300 k
To4= 662.37 k

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Density of air at 27 c and ɸ=100% from psychrometric chart or table =
1.156 kg/𝑚3
(m air/p air)at 15 c=(m air/p air ) at 27c
M air= 130.22 kg/s
Cpair.avg= 1.209 kj/kg.k
Wc=57 076 kw
To5= 1377k
Cp in c.c=1.23 kj/kg.k
Q c.c= 115 188.5 kj/s
M fuel= 2.369 kg/s
M gas =132.58 kg/s
Cpgas for turbine=1.2311 kj/kg.k
Wt= 93 034.9 kw
Wnet= 35 958 kw
(ηgenerator= 0.962)
Elec Power output=34 592.46
S.F.C= 0.237 kg/kw.h
H.R=12 127.76 kj/s
.ηthermal= 0.296 or 29.68%
Performane of gas turbine at temperature 40 c and relative humidity
28%
To3= 313 k
To4= 688.8 k

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Cpa=1.221
Density of air at 40c= 1.127 kg/𝑚3
So, mass flow rate of air =126.96 kg/s
Wc=58 260.4 kw
Heat added in (c.c)=Qc.c
Cpg..avg=1.218 kj/kg.k
Qc.c= 106 460 kj/s
mfuel= 2.18 kg/s
mgas=129.149 kg/s
Wt=90 627.9 kw
Wnet= 32 367.6 kw
Elec power = 31 137 kw
S.F.C=0.243 kg/kw.h
HR=12 463 kj/s
.ηthermal= 0.2889 or 28.89%
The elec net power difference between 40c and 15c = 39.6-31.15=8.447MW
The elecnet power difference between 27c and 15c is 39.6-34.59=5.01 MW
Now we find the power consumptionfor the fogging system and this system
uses only pumps to compresswater and don’t uses other auxiliaries.
H vap(water)=2940 kj/kg
Ѡ2 after fogging= 0.18 kg water/ kg of dry air (for ɸ=100%)

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Ѡ1 before fogging = 0.12 kg water/ kg of dry air(at 40 c and ɸ= 27 %)
Q= (130.2)(2940)(0.18-0.12)
Q fogging= 22970.8 kj/s
m water added to air = (change in Ѡ) (m air)
m water = 130.2 x 0.06
= 0.78132kg/s
V water = 0.00078132 𝑚3
/sec
.ηisent= 0.9
Pump power =(0.00078132)(10000)/0.9
= 8.6813 kw
We see that this system take a very small amount of electricity.

34
(3.1) psychrometric chart shows fogging process

35
Cooling load calculation from the high temperature to 15 c dry bulb
temperature to optimize the bestinlet condition for gas turbine to get the
bestpower
At 40 c and ɸ=25%
Dew point temperature= 16.25 c
Wetbulb temperature = 23.4 c
Enthalpy of air = 69.9 kj /kg of dry air
Specific volume = 0.9023 𝑚3
/kg
At 15 c and relative humidity = 100% from psychrometric chart show
cooling process
H air= 42.00 kj/kg of dry air
Q cooling = m air (h2- h1)
= 138 (69.9-42)= 3850.2 kw cooling coolrequired

36
(3.2) psychrometric chart shows cooling process

37
For the vapor compressioncycle chiller system The refrigerant used is r-
134 a
This cycle is a two stages means two cycles of water the first one runs
between evaporator and inlet air to turbine (cooling coil) and the second
one is between the condenser and and cooling tower (open) .
Each cycle use pump to run the water and there is propellerat the cooling
tower
(3.1)
Cooling load = m water Cp water (T2-T1)
T2:water temperature after leaving cooling coil
T1: water temperature before entering cooling coil
3850.2= m water (4.18)(7-(-3))
M water = 91.95 kg/s

38
Depending on the water temperature on both sides we set the condenser
pressure and the evaporator pressure
P condenser= 10 bar
P evaporator = 1.06 bar
The cycle is set to be ideal with no sub cooling or super heating
And the compressionis isentropic
Q load = m ref (h2-h6)
3850.2 m ref (388-255)
m ref = 28.94 kg /s
W comp = 1070.78kw
Water pump power = (91.95/1000)(1.8)
Pressure for this cycle is nearly 1.8 bat
Pressure for cooling tower cycle is 2.3 bar
W pump= 9.195 kw
M ref (h3-h5)= m water cp water (33 - 27)
28.94 (425-255)= m water 4.18 (6)
M water 195.836
For the cooling tower
M air = 27.88 kg/s
V air = 27.88 𝑚3
/s
Second water pump power= V water x pressure cooling tower/η
Pump power= 50 kw
Propellerpower = V air P/η propeller
= 30.9
Total power= 1 160.8 kw

40
For vapor absorption cycle for
In this system we have water cycle for condenserwith cooling tower and
water cycle for absorberand cooling tower and water cycle for evaporator
closed with air inlet and hot water cycle for generator heat adding
Generator temperature 50-130 C
Condenser temperature 20-400C
Absorbertemperature 20-400C
Heat exchanger effectiveness 0.5-1
Generator pressure=condenserpressure 10 bar
Evaporator pressure = absorberpressure 3.6 bar
Temperature leaving dephlagmator 50 c
And by energy balance for evaporator we find that the refrigerant mass flow rate
(ammonia) =
3850.2= m ammonia (h5- h4)=(91.95)(4.18)(10)
M ref= 3.2 kg/s
(3.1)
Qgen=(3.2 x 1650)+(54.31 x 290)-(230 x 57.42)
= 7823.3 kj/s
For water cycle with generator Qgen = m water Cp water (T out -T in)
7 823.3 = m water (4.18)(30)
M water = 62 kg/s
State
point
Pressure(
bar)
Tempera
ture (0C)
Concentr
ation of
ammonia
per kg of
mixture
Enthalpy
(KJ/kg)
Flow rate
(kg/s)
1 10 50 1 1650 3.2
2 10 25 1 400 3.2
4 3.6 -5 1 400 3.2
5 3.6 10 1 1600 3.2
7 3.6 32 0.39 17 57.42
8 10 32 0.39 17.73 57.42
9 10 75 0.39 230 57.42
10 10 90 0.318 290 54.31
11 10 40 0.318 57.34 54.31
12 3.6 40 0.318 57.34 54.31

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Pumping power for water= (62/1000) (1.8)/η=12.4 kw
Q absorber= 7 257.86 kj/s
Solution pump power = (1+17.94)(57.42)(0.00720(100)(10-3.6)
=83.53 kw
Q Condenser = (3.2)(1650-400)=4000KJ/S
Q condenser= m water cp water (Tout- Tin)
M water =47.8 kg/s
Pumping power = 12 kw
Q condenser= m air 2940 (Ѡ2-Ѡ1)
4000= m air 2940(0.06)
M air = 22.6 kg/s
Propellerpower = 22.6/1 (1000)/0.9 =24.4 kw
Total power = 24.4+12+83.53+12.4= 132.3 kw
As we can see from this system it need only for a 131 kw of power but it
need a high amount of waste heat Q generator and in the calculation of
costof each system in these tables
(3.2)

43
(3.4)
The VARS is more expensive to install, has considerably lower operating and
maintenance costs than VCRS.
The financial indicator, Internal Rate of Return (IRR) for VARS over VCRS has been calculated
by varying Net Present Value (NPV) with respect to discount rate in the Figure 3 is 88.63 %.
Variation of NPV with respect to Discount Rate(3.4)

44
life cycle costanalysis of waste heat operated vapour absorptionair conditioning
system (VARS) incorporated in a building cogeneration system is presented and
the same is compared with the electric based vapour compressionchiller (VCRS)of
same capacity. Initial costof VARS is high and operating costof VARS is low
when compared with VCRS. LCC is mainly depends upon operating costs. From
the analysis, it was found that the initial costof VARS was 125 % higher than that
of VCRS, while the PWC of operating costof VARS was 78.2%lower compared to
VCRS. The results showed that the life cycle cost(LCC) of waste heat operated
absorption chiller is estimated to be US $1.5 million which is about 71.5 % low
compared to electric powered conventional vapour compression chiller. In
addition, VARS systems will result in GHG reduction of 2.85 x 106 kg/y. The
deviation in the life cycle costof the two systems where analyzed by plotting
suitable graphs (IRR). The result shows that
the waste heat operated VARS would be preferable from the view point of
operating costand maintenance cost.
And for the fogging systems
The capital costfor the fogging is very low compared to chillers but in the fogging
we cant reach the best inlet condition of air in a short term use it will be useful but
in th long term there will be a losses in energy and money waste.

45
Chapter Five
Conclusion and Recommendation
The results and calculationsshow the turbine performance at
three degrees (15,27,40)c the main parameter that effect the
performance is the air density which lower the turbine power
output and the turbine powers on the three degrees also the
results shown the power needed for the cooling system for the
inlet air of the turbine and the turbine change in performance
the conclusionis that for long term uses and here is a long term
so the absorptionchillerswill be the best choice to increase the
power output of the cycle
On 15c the electrical power output of the turbine 39.6
Power required for:
Fogging 8.6 kw
Vapor compression chiller 1 160.8 kw
Vapor Absorptionchiller 132.3 kw
And for the costthe vapor absorptionsystem initial costis higher than the
vapor compressionsystem but the running cost is higher for the vapor
compressionso in long term uses the vapor absorption will be more benefit
than the vapor compression.

46
Refrences
1-1999. ASHRAE Handbook –Applications.
2- LIFE CYCLE COST ANALYSIS OF WASTE HEAT OPERATED ABSORPTION
COOLING SYSTEMS FOR BUILDING HVAC APPLICATIONSV.Murugavel and R.
SaravananRefrigeration and Air conditioning LaboratoryDepartment of
Mechanical Engineering, Anna University,Sardar Patel Road, Chennai 600 025,
India.
3-TABLES OF THE PROPERTIES OFAQUA-AMMONIA SOLUTIONSPart 1 ofThe
Thermodynamics of Absorption Refrigeration BUIIOESS H. JENNINGS, _._.,M.S.Associate Professor
of Mechanical Engineering
4-Mitsubishi Heavy Industries TechnicalReview Vol. 47 No. 4 (December 2010)
5-APPLIED THERMODYNAMICS TUTORIAL No.3 GAS TURBINE POWER CYCLES
©D.J.Dunn
6-effects of air cooling on performance of gas turbine power plant by sally ali
gaeed and alahassan falah(university of technology mechanical eng. Dep. Iraq)
7- Theoritical Analysis of Nh3-H2o Refrigeration System Coupled With Diesel Engine: A
Thermodynamic Study Rahul Singh*1, Dr. Rajesh Kumar2 (*1,2 Department of Mechanical
Engineering, Delhi Technological University Government of NCT of Delhi, Bawana Road,
Delhi-110042, India.)
8-Master ofScience Thesis KTH Schoolof Industrial Engineering and Management Energy Technology
EGI-2014-103MSC EKV1064 Division of Heat & Power SE-100 44 STOCKHOLM Effect of
cooling charge air on the gas turbine performance and feasibility of using
absorption refrigeration in the “Kelanitissa” power station, Sri Lanka
Dinindu R. Kodituwakku
9-MONITORING COMPRESSOREFFICIENCY FOR MAXIMUMPERFORMANCE
Presented at PowerGen 2007By Tina L. Toburen, P.E.

GAS TURBINE POWER PLANTS INLET AIR COOLING

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