IRJET - Performance Evaluation and Parametric Study of Basic and Reheated Cooled Gas Turbine Cycle: Exergy Analysis

International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056
Volume: 07 Issue: 02 | Feb 2020 www.irjet.net p-ISSN: 2395-0072
© 2020, IRJET | Impact Factor value: 7.34 | ISO 9001:2008 Certified Journal | Page 2710
Performance Evaluation and Parametric Study of Basic and Reheated
Cooled Gas Turbine Cycle: Exergy Analysis
Shivam Mishra 1, Mithilesh Kumar Sahu 2
1Assistant Professor, Mechanical Engg. Department, GL Bajaj ITM, Mathura, INDIA
2Assistant Professor, Mechanical Engg. Department, GVPCE (Autonomous), Madhurawada, INDIA
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Abstract - Present energy scenario depicts a continuous
increase in gap between energy demand and energy supply
with increasing electricity cost. Owing to increase in fuel
prices electricity manufacturing companies have to adopt
an energy conversion practice that must have higher
performance side with lowest possible investment. Among
the various techniques available, gas turbine with complex
configuration for enhancing performance is the one. Cooled
gas turbines allow manufacturers to go for higher turbine
inlet temperature as allowable blade material temperature
is 1150K only. Gas turbine blade cooling overcomes the
metallurgical constraints that don’t allow the turbine inlet
temperature (TIT) to increase beyond a particular
temperature, hence gas turbine blade cooling become a
revolutionary area of research. In this regard present work
deals with the thermodynamic analysis of basic gas turbine
(BGT) and reheated gas turbine (RHGT) cycle incorporating
air film blade cooling technique. The results of performance
evaluation shows that exergy efficiency of the basic cooled
gas turbine cycle is better as compared to the reheat cycle
for the case TIT = 1800 K & rpc = 30 while parametric study
shows that coolant mass flow rate increases for both the
configuration with increase in TIT while exergy efficiency
curve of both the cycle shows falling nature with an increase
in TIT at a fixed compressor pressure ratio.
Key Words: Air film cooling, Blade cooling, Exergy
analysis, Exergy efficiency, Parametric study, Plant Specific
work Thermodynamic analysis, Reheated gas turbine
1. INTRODUCTION
Cooling of gas turbine blades has been a prime area of
research since decades. According to report of
International Energy Agency (Energy Outlook 2008) [1]
the Global demand of energy has been forecasted to
increase approximately 1.6 % per year for upcoming
period of approximately 30 years. The regulation norms
for cutting down the greenhouse gases emissions have
forced the power producing units to adopt environment
friendly (low emission) power producing techniques in
the area of gas turbine and combined cycle. Various such
techniques have been developed over the years, of which
one is gas turbine blade cooling. Gas turbine blade cooling
system now allows gas turbines operations at higher blade
temperatures i.e. beyond the temperature constrained by
metallurgical limits. The blade cooling includes blowing of
compressed air from the internal passages of the blades
over it. Authors have published numerous research
articles in gas turbine blade cooling with thermodynamic
as well as thermoeconomic analysis [2-11]. Mithilesh
Kumar Sahu et al. [2-4] have thermodynamically analysed
the cooled gas turbine cycles based on energy and exergy
analysis. Anupam Kumari et al. [5] have reported the
exergoenvironmental analysis of intercooled gas turbine
cycles with emission characterization and also stated that
the cooled gas turbines are more environment friendly
compared to uncooled gas turbines and other thermal
power plants.
Mithilesh Kumar Sahu and Sanjay [6-11] have
thermoeconomically analysed the complex cooled gas
turbines with film air cooling technique and also reported
the effect of film cooling on various thermoeconomic and
thermodynamic performance parameters. A comparative
analysis was carried out by Louis et al. [12] on open and
closed loop cooling methods by using the mathematical
model. The mathematical model uses the air and steam as
cooling medium. Louis et al. [12] reported that the
difference of temperature between turbine inlet
temperature and blade material temperature majorly
affect the gas turbine performance parameters. Chuan and
Louis et al. [13] extends the work and developed a
mathematical model which determines the coolant mass
flow rate requirement for particular gas turbine output.
They also performed the comparative study on various
inlet air cooling systems on and reported the effect of
same on combined cycle performance. El-Masri [14]
developed an Interactive computer code, named GASCAN
by mathematical modelling of various gas turbine
components describing cooled GT performance. Brieshet
et al. [15] have suggested the possibility of thermal
efficiency to be 60%. The author suggested the closed loop
steam cooling as the best alternative. A detailed
comparative study of advanced combined cycle
alternatives with bottoming cycle has been carried out by
Bolland [16]. Young and Wilcock [17] described the basic
thermodynamics of an air film cooled gas turbine model.
The author suggested that these cycles include varying
composition of gas mixtures and hence a realistic
modelling of the components must be done. He further
advocates the importance of cooling losses while
estimating the performance of a cooled cycle. Sanjay et al.
[18] reported the component wise thermodynamic
modelling of advanced combined cycle for the assessment
of enhanced performance. The result illustrates that
increase in the TIT has a positive effect over the overall

plant efficiency i.e. efficiency is increased with respect to
the reference cycle. Sanjay [19] investigated a parametric
study to outline the energetic and exergetic performance
of combined cycle. The article highlights that with
increasing TIT and rpc values, the exergy destruction
values decreases. Sanjay et al. [20] carried out a detailed
energy and exergy analysis for reheat gas steam combined
cycle and observed the superiority of closed-loop-steam-
cooling over air-film cooling. The author further reveals
that the reheat gas-steam combined cycle shows an
enhance thermal efficiency and plant specific output with
closed-loop-steam-cooling in comparison to basic gas-
steam combined cycle with air film cooling. Alok and
Sanjay [21] carried out a detailed study investigating
thermodynamic assessment of the performance of gas
turbine and combined cycle incorporating inlet cooling
techniques. The article focuses the comparative study of
impact of two different inlet air cooling methods namely
vapour compression and vapour absorption. The author
advocates the use of vapour compression cooling method
in combined cycle for higher plant performance. A detailed
report over thermodynamic performance of combined
cycle power plant has been submitted incorporating seven
different methods of blade cooling in a technical paper by
Sanjay et al. [22]. A cogeneration cycle based on gas
turbine has been taken for study by Sanjay et al. [23]. The
author investigated the effect of different gas turbine
blade cooling on the discussed cycle. The maximum power
to heat ratio has been observed for steam cooled internal
convection while minimum has been observed for internal
convection cooling taking air as the coolant. A. K.
Mohapatra and Sanjay [24] studied the parametric study
of variation in performance parameter such as TIT,
compressor pressure ratio on a cooled gas turbine plant
with two inlet air cooling techniques. The authors suggest
that integration of two techniques have a positive effect
over the plant performance. Anupam Kumari and Sanjay
[25] studied the effect of parameters affecting the
exergetic and emission characteristics of gas turbine
cycles. The author advocates that intercooled
configuration should be preferred over basic one as it
delivers higher specific power output and plant efficiency.
The emission performance of IcGT is better than basic
cooled gas turbine cycle.
The present paper deals with the exergetic performance
evaluation of reheated cooled gas turbine cycle with basic
cooled gas turbine cycle incorporating air film cooling
technique. Film cooling is the widely accepted cooling
technology where the surface of the blade gets covered
with a thin film of air which acts as a thermal barrier and
separates the blade surface to make a direct contact with
hot gases coming out of combustion chamber [26].
2. SYSTEM CONFIGURATIONS
The schematic diagram of basic and reheated gas turbine
based power plant is shown in Figure 1 and Figure 2 and
depicts the conventional way of gas turbine operation with
blade cooling. The novelty of this work is consideration of
blade cooling in the performance evaluation of aforesaid
cycles. As real gas turbine engines works on blade cooling
principles hence this work provides significant scientific
merit to the research field.
Figure 1: Schematic diagram of basic gas turbine cycle
with air film blade cooling
Figure 2: Schematic diagram of reheated gas turbine cycle
with air film blade cooling
3. MODELLING AND GOVERNING EQUATIONS
3.1 Air/gas Model [27]
(1)
,
(
)- (2)
∫ ( ) (3)
∫ ( ) (4)
( ) (5)
(6)
3.2 Compressor Model [7]
(7)

* ,( ) -+ (8)
̇ ̇ ∑ ̇ ̇ (9)
3.3 Combustion Chamber Model [7]
̇ ̇ ̇ (10)
̇ ̇ ̇ (11)
̇
, ̇ ̇ -
, -
(12)
̇ ̇ ̇ (13)
( ) (14)
3.4 Cooled Gas Turbine Model [7]
Air Film cooling:-Figure 3 depicts the main stream hot
gases and coolant air passage. From figure it can be seen
that how coolant air is emerging out from the cooling holes
and creates a film which restricts the direct contact of hot
main stream gases with the blade surface. This leads to
increase in life span of the blade as well as air film cooling
has its own advantage of mixing with mainstream gases
and giving the edge of higher mass flow rates for expansion
compared to closed loop cooling technics.
Figure 3: Model of air film cooling of turbine blade
̇
̇
( )
( )
( )
(15)
( ) (16)
The temperature and pressure of gas turbine exhaust
stream and power output is given by the relation:
* , ( ) -+ (17)
̇ ( ̇ ∑ ̇ ̇ ) (18)
̇ ̇ ̇ (19)
4. RESULT AND DISCUSSION
A MATLAB code [28] has been developed to simulate the
performance of proposed gas turbine cycle configurations.
To simulate the gas turbine performance some key design
and operating parameters need to be specified and the
same has been detailed in Table 1. The simulation results
have been discussed with the help of various illustrating
graphs.
Table 1: Key parameters for analysis of proposed cycle [7,
9, 18 and 20]
Components Design/Operating
parameters
Adopted
value
Unit
Gas Properties ( )
∫ ( )
kJ/kgK
kJ/kg
Compressor ηAC
ηmech
rpc
88
98.5
20-30
%
%
-
Combustion
Chamber
ηCC
ploss
LHV
pfuel line
99.5
2.0% of pentry
42.0
1.5*pcc
%
bar
MJ/kg
bar
Turbine ηGT
pexhaust
Tb
TIT
90
1.08
1150
1500-1800
%
bar
K
K
Figure 4: Effect of TIT and rpc on coolant mass fraction
and plant specific work for BGT cycle
Figure 4 depicts the variation of plant specific work output
of basic gas turbine cycle with coolant mass fraction at
different TIT and rpc. It can be clearly seen that coolant
mass flow rate increases, as the compressor pressure ratio
increases at a fixed TIT value while plant specific work
output decreases at the same parameters. The increase in
coolant requirement is driven by the fact that as we move
on for higher rpc it also results increase in temperature of
coolant air available at compressor bleed points and of
course higher rpc needs more compressor work which
ultimately results decrease in plant specific work. Coolant
mass fraction and plant specific work both shows an
increasing trend for fixed rpc value with increasing TIT
values. The rising tendencies of curve for both parameters
are in line with the concept of heat transfer (for higher
temperature more amount of coolant required) and
thermodynamics (energy at higher temperature has more
potential).

and plant specific work for RHGT cycle
Figure 5 represents a variation of coolant mass fraction
with plant specific output of reheated cooled gas turbine
with varying TIT and rpc values. The graph predicts the
similar trend with the previous literatures as the values of
TIT is increased from 1500K to 1800K keeping rpc value
constant, the coolant mass fraction value increases because
higher TIT causes more amount of coolant to be bled from
compressor for the cooling of stages while the plant
specific work output initially increases sharply and again
starts decreasing after a certain TIT value. The diagram
further describes that as rpc values are increased along a
fixed TIT value the coolant mass fraction ratio shows slight
increment in the coolant mass fraction up to an rpc while
again it shows decline behaviour. It occurs because of
increase in rpc value causes more number of turbine stages
to be cooled. The diagram describes that on increasing the
rpc value along a fixed TIT values the plant specific work
output increases for RHGT cycle.
In Figure 6 behaviour of coolant mass fraction with second
law plant efficiency for the basic cooled gas turbine cycle is
depicted. It is observed from Figure 6 that as TIT values
increase from 1500K to 1800K at the same rpc, the curve of
coolant mass fraction shows an increase trend while the
exergy efficiency of the cycle decreases at the same
parameters. The graph further describes the behaviour of
increasing rpc values over fixed TIT values which further
shows an increase in both coolant mass fraction as well as
exergy efficiency due to the reasons explained earlier
and exergy efficiency for BGT cycle
Figure 7: Effect of operating parameters on coolant
mass fraction and exergy efficiency for RHGT cycle
Figure 7 describes the performance behaviour of coolant
mass fraction of reheated cooled gas turbine cycle with
second law efficiency (exergy efficiency). Figure depicts
that coolant mass fraction and exergy efficiency both
shows increasing trend with increase in rpc while keeping
a fixed value of TIT. It is due to the fact that higher rpc
results increase in coolant air temperature as well as it
also results saving in mass flow rate of fuel required for
combustion. An increase in TIT value at a fixed rpc shows
an increase in coolant mass fraction (higher temperature
as well as more number of stages required cooling) while
the value of exergy efficiency decreases on increasing the
TIT (increase in fuel mass flow rate).

Figure 8: Comparative analysis of BGT and RHGT for
coolant mass fraction with TIT variation (fixed rpc)
In Figure 8, the variation of coolant mass fraction with the
TIT values for both basic and reheat cooled gas turbine
cycle at a fixed value of rpc=30 has been illustrated. The
values of coolant mass fraction is increased along with the
increase in TIT in both basic and reheat cooled gas turbine
cycle because higher TIT causes higher coolant mass
fraction for more number of stages to get cooled. The
coolant requirement for the both basic and reheat gas
turbine cycle increases with rise in TIT but the trend
followed in basic cooled gas turbine is little gradual while
for cooled reheated gas turbine it follows a little sharp
trend.
Figures 9 explain the behaviour of exergetic performance
and specific work of basic and reheat configurations of gas
turbine cycle. The column chart clearly indicates that
exergy efficiency of basic gas turbine is better as compared
to reheat cycle for same operating conditions. The
combustion chamber (CC) is the main source of exergy
destruction and as in reheat cycle fuel required is also
higher that is the reason for lesser exergy efficiency in
case of reheat cycle. The column chart also compares the
plant specific work output of both the cycles which is
greater in case of RHGT cycle. In reheat cycle expansion
takes in two stages of turbine, which results higher
specific work output compare to BGT cycle for same
operating parameters.
5. CONCLUSIONS
A systematic component modelling followed by exergy
analysis of proposed basic and reheat gas turbine
configurations has been performed. The analysis of
simulated results presented in the previous section with
the help graphs and charts suggests the following
conclusions:
 The coolant mass fraction for both the BGT and RHGT
increases with increase in TIT for fixed compressor
pressure ratio.
 The specific work output of the BGT increases on
increasing the TIT at a fixed rpc while for the RHGT
specific plant work initially increases sharply on
increase in TIT and again it starts decreasing after a
certain TIT.
 The exergy efficiency curve of both the cycle shows
falling nature with an increase in TIT at a fixed
compressor pressure ratio.
 Exergy efficiency of the basic cooled gas turbine cycle is
better as compared to the reheat cycle for the case TIT =
1800K & rpc = 30.
 Plant specific output is found to be more in case of
reheat cycle as compared to basic cooled gas turbine for
TIT = 1800K & rpc = 30, as in reheat cycle the expansion
takes place in two steps.
Figure 9: Comparative analysis of BGT and RHGT cycle for
same operating conditions
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IRJET - Performance Evaluation and Parametric Study of Basic and Reheated Cooled Gas Turbine Cycle: Exergy Analysis

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IRJET - Performance Evaluation and Parametric Study of Basic and Reheated Cooled Gas Turbine Cycle: Exergy Analysis