Transcript Document
CHAPTER 2 SHAFT POWER CYCLES
• There are two main types of power cycles; • 1.
Shaft power cycles :
power plants.
Marine and Land based • 2.
Aircraft propulsion cycles:
upon forward speed & altitude.
Performance depends Chapter2 Shaft Power Cycles 2
CHAPTER 2
SHAFT POWER CYCLES I Ideal Cycles
Ideal Cycles
The analysis is based on the :
•
perfection of individual components
• w
,
h
depend upon
r
and T max
w : Specific power output
h
r : Pressure ratio T : Cycle efficiency max : Max. cycle Temperature
Chapter2 Shaft Power Cycles 4
Ideal Cycles - Assumptions a)
b) Compression and expansion processes are
isentropic
The
change of Kinetic Energy
of the working fluid between the inlet and outlet of each component is negligible.
Chapter2 Shaft Power Cycles 5
Ideal Cycles - Assumptions c)
d) No
pressure losses
in the inlet ducting, combustion chambers, heat exchangers, intercoolers, exhaust ducting and ducts connecting the components.
The composition of the
working fluid
does not change and it is a
prefect gas
with
constant specific heats
Chapter2 Shaft Power Cycles 6
e) f)
Ideal Cycles - Assumptions :
The
mass flow rate
of gas is
constant Heat transfer
in the
Heat Exchanger
is complete; so in conjunction with
(d)+(e),
temperature rise on the cold side is equal to the temperature drop on the hot side.
•
(d,e)
indicates that the
combustion chamber
is such that it is as if heated by an external heat source.
Chapter2 Shaft Power Cycles 7
SIMPLE Gas
Turbine
CYCLE
• The ideal cycle for a simple Gas Turbine is the
BRAYTON
cycle.
(or JOULE) •
Fig. 2.1 Simple Gas Turbine
Chapter2 Shaft Power Cycles 8
SIMPLE Gas Turbine CYCLE
Steady flow energy equation: q = h II where : h I + 1/2 ( v II 2 - v I 2 ) + w q = heat transfer per unit mass flow.
w = work per unit mass flow.
w 12 = - (h 2 - h 1 ) = c p (T 2 – T 1 )
q
23 = (h 3 - h 2 ) = c p (T 3 - T 2 ) w 34 = (h 3 - h 4 ) = c p (T 3 - T 4 ) Chapter2 Shaft Power Cycles 9
SIMPLE Gas Turbine CYCLE The efficiency of the cycle is then :
h net work output heat supplied 3
T
4 ) 3
T
2 ) 2
T
1 ) Chapter2 Shaft Power Cycles 10
SIMPLE Gas Turbine CYCLE The cycle temperatures can be related to the pressure ratio r p ; r p = p 2 /p 1 = p 3 /p 4 For isentropic compression and expansion; p/
r
= RT ; p/
r g
= const.
T 2 /T 1 = r p
(g1)/g
and T 3 /T 4 = r p
(g1)/g Chapter2 Shaft Power Cycles 11
The Efficiency of the Simple Gas Turbine Cycle
h net work output heat supplied
C p
(
T
3
T
4 )
C p
(
T
2
T
1 )
C p
(
T
3
T
2 ) h
C p T
3 ( 1
T
4
/T
3 )
C p T
2 ( 1
T
1 /
T
2 )
C p
(
T
3
T
2 )
c
r p
(γ 1) / γ
T
2 /
T
1
T
3 /
T
4 h
T
3 ( 1 1
/c
)
T
2 ( 1 1 /
c
) (
T
3
T
2 ) ( 1 1 /
c
) Chapter2 Shaft Power Cycles 12
The Efficiency of the Simple Gas Turbine Cycle
Then the cycle efficiency is; where; h g g 1
c
r p
( g g 1 ) ( 2.1
) 1
c
Chapter2 Shaft Power Cycles 13
SIMPLE Gas Turbine CYCLE The specific work output w , depends upon the size of the plant for a given power.
It is found to be a function of not only pressure ratio, but also of maximum cycle temperature T 3 . Thus;
w
= c p (T 3 -T 4 ) - c p (T 2 -T 1 ) can be expressed as;
w
T
3 1 1
T
1 1
r p
( g 1) / g
r p
( g 1) / g 1
c t
c
1)
( 2.2 ) The specific work output is a function of " t " (T 3 /T 1 ) and "r p " ;
w = w
(t, r
p
).
Chapter2 Shaft Power Cycles 14
SIMPLE Gas Turbine CYCLE FIG. 2.2Efficiency and specific work output - simple cycle Fig. 2.2 Efficiency and specific work output - Simple Cycle
Chapter2 Shaft Power Cycles 15
SIMPLE Gas Turbine CYCLE T 3 :
Maximum Cycle Temperature,
t = T 3 /T 1
imposed by the metallurgical limit.
=
3.5 -4
t =
5-5.5 for long life industrial plants, for aircraft engines with cooled turbine blades.
From the T-S diagram, it is clear that when r p = 1 or r p = (T 3 /T 1 ) (g/g1)
w
= 0 Thus in between there is a maximum (or minimum) value for w Chapter2 Shaft Power Cycles 16
SIMPLE Gas Turbine CYCLE
For any given value of "t" (T 3 /T 1 ), the
optimum
value of r p for
maximum specific work output
calculated by differentiating eqn. 2.2 wrt. r p equating to zero.
can be ( g/g1) and
r
The result is;
opt
( g 1 )/ g
T
3 /
T
1 Since
r opt
i.e.
r opt
( g 1 ) / g
T
2 /
T
1
T
3 /
T
4
t
( 2.3 ) Chapter2 Shaft Power Cycles 17
SIMPLE Gas Turbine CYCLE
This is equivalent to;
T T
1 2
T T
3 4 So,
w
temperatures are equal.
T
3
T
2
T
4
T
1 is maximum when compressor and turbine outlet For all values of r p between 1 and T 4 > T 2 r opt = [ (T 3 /T 1 ) ( g/2 (g1 ) ) ] and a
heat exchanger
can be incorporated to reduce the heat transfer from the external source and so increase the efficiency.
Chapter2 Shaft Power Cycles 18
Heat Exchanger Cycle
Fig. 2.3 Simple cycle with heat - exchange
Chapter2 Shaft Power Cycles 19
Heat Exchanger Cycle
The cycle efficiency h is; h 3
T
4 ) 3
T
5 ) 2
T
1 ) with ideal HE
T 5 = T 4
with the help of isentropic relations; h
r p
( g 1 )/ g
T
3
T
1
t c
Chapter2 Shaft Power Cycles ( 2.4) 20
Heat Exchanger Cycle Fig 2.4 Efficiency of a simple cycle with heat-exchange for r p = 1 :
h
= 1- 1/t which is Carnot efficiency.
as T 3 increases, t increases and then
h
increases
Chapter2 Shaft Power Cycles 21
Heat Exchanger Cycle
Specific work output does not change with HE thus is the same as the simple cycle.
To obtain an appreciable improvement in h ideal cycles.
by HE in
a)
a value of r p < r opt
then work output is maximum.
b)
It is not necessary to use a higher cycle pressure ratio as T max of the cycle is increased.
(a)
is true for actual cycles whereas (
b)
requires modification Chapter2 Shaft Power Cycles 22
Reheat Cycle
Fig. 2.5 Reheat cycle
• A substantial
increase in specific work output
can be obtained by splitting the expansion and reheating the gas between
low-pressure
and
high-pressure
turbines.
Chapter2 Shaft Power Cycles 23
Reheat Cycle
•
Since the vertical distance between any pair of constant pressure lines increase with the increasing entropy
• •
(T 3 - T 4 ) + (T 5 thus : - T 6 ) > (T 3
w reheat
>
w
simple - T 4 )
• • w
34 +
w
56 = C p (T 3 - T 4 ) + C p (T 5 - T 6 ) = C p (T 3 - T 4 ) + C p (T 3 - T 6 )
• w
t = C p T 3 (1-T 4 / T 3 ) + C p T 3 (1-T 6 /T 5 )
Chapter2 Shaft Power Cycles 24
Reheat Cycle
since
T
4
T
3 (
P P
3 4 ) ( g 1 )/ g • Denoting
N
g g 1 • then P 4 = P 5
w T
3
T
6
T
5 (
P
6 ) (
P
5 g 1 )/ g (
P P
4 6 ) ( g 1 )/ g 1
P
4
P
3
N
1
P P
4 6
N
Chapter2 Shaft Power Cycles 25
Reheat Cycle
• To find P4 for maximum work output; • The result is;
P
4
P P
6 • Hence, P 3 /P 4 = P 4 /P 6 • for
maximum work output
the
optimum splitting
is an
equal
one.
Chapter2 Shaft Power Cycles 26
Reheat Cycle
• Specific work output of the cycle is then;
w
= C p (T 3 - T 4 ) + C p (T 5 - T 6 ) - C p (T 2 - T 1 ) • • Thus:
w
1
T
3
T
1
T
4
T
1
T T
1 5
T
6
T
1
T
2
T
1
w
1 2
t
1 2
t c
1 • Then the efficiency; h
2
t
2
t c
Chapter2 Shaft Power Cycles
t c
( 2.5 )
t
/
t
/
c c
t c
c
( 2.6) 27
Reheat Cycle
•
Effect of Reheat : increase in specific output and decrease in efficiency.
Fig. 2.6
Work output vs. r in a Reheat Cycle
•
EXERCISE : For a simple Reheat Cycle, prove that specific work output is maximum when
(g1/g)
=(T 3 /T 1 ) 2/3 = t 2/3 .
Chapter2 Shaft Power Cycles
r p
28
Cycle with Reheat & Heat Exchange
• The reduction in efficiency due to reheat can be overcomed by adding heat exchanger.
• The high exhaust gas temperature is now fully utilized in the HE and the increase in work output is no longer offset by the increase in heat supplied.
Fig. 2.7
Reheat cycle with Heat Exchange
Chapter2 Shaft Power Cycles 29
Reheat cycle with Heat - Exchange Fig. 2.8 Efficiency - reheat cycle with heat - exchange
Chapter2 Shaft Power Cycles 30
Cycle With Reheat & Heat Exchange
The reduction in efficiency due to reheat can be overcomed by adding a heat exchanger. The higher exhaust gas temperature is now fully utilized in the HE and the increase in work output is no longer offset by the increase in heat supplied.
HE 1 2 f 3 7 4 f 5 6 6 Chapter2 Shaft Power Cycles 31
T
Cycle With Reheat & Heat Exchange 3 5 2 1 7 HE 4 8 6
s Chapter2 Shaft Power Cycles 32
Cycle With Reheat, Intercooling & Heat Exchange
Intercooler 1 LPC 9 2 HE f 3 5 4 HPC LPT 10 Chapter2 Shaft Power Cycles 6 f 7 HPT 8 33
Cycle With Reheat, Intercooling & Heat Exchange
T
5 7 4 2 1 9 HE 6 10 8 3
s Chapter2 Shaft Power Cycles 34
CHAPTER 2
SHAFT POWER CYCLES II Actual Cycles
ACTUAL CYCLES
•
The performance of real cycles differ from that of ideal cycles for the following reasons : a) Change in Kinetic Energy
between inlet and outlet of each component can not necessarily be ignored.
• • •
b)
Compression and expansion are actually
irreversible
and therefore involves an increase in entropy
c)
Fluid
friction
causes pressure losses in components and associated ducts.
d) HE
can not be ideal, terminal temperature difference is inevitable Chapter2 Shaft Power Cycles 36
ACTUAL CYCLES
• e) Slightly more work than that required for the compression process will be necessary to overcome bearing and • f) windage friction in the transmission between compressor and turbine and to drive ancillary components such as fuel and oil pumps.
( h
mech
)
C p
and g changes throughout the cycle.
C p = f(T) h= f(T)
and chemical composition.
• g) Combustion is not complete ( h
comb )
Chapter2 Shaft Power Cycles 37
ACTUAL CYCLES
• The efficiency of any machine (which absorbs or produces work), is normally expressed in terms of the ratio of actual to ideal work transfers • For a compressor; h
c
w w
h o
h o
h ideal
h actual
• For a perfect gas;
h = C p T ,
• This relation is sufficiently accurate for real gasses under conditions encountered in a GT if a mean C p range of temperature is used over the relevant Chapter2 Shaft Power Cycles 38
Compressor and Turbine Efficiencies
• Then for compressors; h
c
T
02
T
01
T
02
T
01 ( 2.7 ) • Similarly for turbines the isentropic efficiency defined as; h
t
w w
T
03
T
03
T
04
T
04 ( 2.8 ) Chapter2 Shaft Power Cycles 39
ACTUAL CYCLES
• For
compressors
: from equation 2.7
(
T
02
T
01 )
T
01 h
c
(
P
02
P
01 ) ( g 1) / g 1 • Similarly for
turbines
; (
T
03
T
04 ) h
t T
03
P
03 1 /
P
04 ) ( g 1) / g ] Chapter2 Shaft Power Cycles ( 2.9 ) ( 2.10 ) 40
Compressor & Turbine Efficiencies
• Since • Thus h h
c s
T
h
c
T
T s
( 2.11 ) • Since the vertical distance between a pair of constant pressure lines on the T-S diagram increases as entropy increases, S T s ’> T’ h
s >
h
c
( for compressors ) Chapter2 Shaft Power Cycles 41
Compressor and Turbine Efficiencies
• Now consider an axial flow compressor consisting of a number of successive stages. • If the blade design is similar in successive blade rows it is reasonable to assume that the isentropic efficiency of a single stage h s remains the same through the compressor.
• Then the overall temperature rise;
s
T s
h
s
1 h
s
T s
Chapter2 Shaft Power Cycles 42
stages i.e. with the increase of pressure ratio.
• A physical explanation is that the increase in temperature due to friction in one stage results in more work being required in the next stage. • A similar argument can be used to show that for a turbine h
t >
h
st .
Fig. 2.9 Definition of Isentropic and Small Stage Efficiencies
Chapter2 Shaft Power Cycles 43
Polytropic Efficiency
• Isentropic efficiency of an elemental stage in the process such that it is constant throughout the whole process.
• For a compression process • But for an
isentropic process, η
c = dT'/dT = const.
( g 1) / g
const
.
• in differential form
dT
1
dp
dT' = η
c dT
T
• integrating between
1 & 2
(inlet & outlet) h
c
( g g 1) ln(
P
2 ln(
T
2
p
P
1 )
T
1 ) Chapter2 Shaft Power Cycles ( 2.12 ) 44
Polytropic Efficiency
• So h
c
can be computed from measured values of
P
inlet an outlet of the compressor, as; and
T
at the
T
2
T
1 (
P
2
P
1 ) ( g • Finally the relation between h
c &
1) /( gh
c
) h
c
; ( 2.13 ) h
c
2 /
T T
2 / 1 1 1 1 (
P P
2 / 1 ) ( g (
P P
2 / 1 ) ( g 1) / g 1) / gh
c
1 1 ( 2.14 ) Chapter2 Shaft Power Cycles 45
Polytropic Efficiency
• Similar relations can be obtained for turbines since , h
t
dT dT
• It can be shown that for an expansion between turbine
inlet 3
and
outlet 4;
T
3
T
4
P
(
P
4 3 ) h
t
( g 1) / g ( 2.15 ) h
t
1 ) h
t
( g 1) / g
P P
3 / 4 1 ( g 1) / g )
P P
3 / 4 Chapter2 Shaft Power Cycles ( 2.16 ) 46
Polytropic Efficiency Fig. 2.10 Variation of turbine and compressor isentropic efficiency with pressure ratio for polytropic efficiency of 85 %
Chapter2 Shaft Power Cycles 47
Polytropic Efficiency
• In practice, as with h
c
and h
t
, it is normal to define the polytropic efficiencies in terms of
stagnation
temperatures and pressures.
• where
T
02
T
01
n
1
n
T
01 [(
P
02
P
01 g gh
c
1 ) (
n
1) /
n
1]
T
03
T
04
T
03
P
03 / 1
P
04 ) (
n
1) /
n
] where
n
1 h
t n
g g 1 • Here
n
is the coefficient for a polytropic process.
( 2.17 ) ( 2.18 ) 48
Pressure Losses
Fig. 2.11 Pressure losses
• • •
P b P ha P hg
= Pressure loss in Combustion Chamber = Frictional pressure loss on the air side of HE = Frictional pressure loss on the gas side of HE Chapter2 Shaft Power Cycles 49
Pressure Losses
• Pressure losses cause a decrease in the available turbine pressure ratio.
• P o3 • P o4 = P = P a o2 - P + P hg b - P ha • It is better to take P hg & P b delivery pressure; Then; as fixed proportions of compressor
P
03
P
02 1
P b P
02
P ha P
02 Chapter2 Shaft Power Cycles 50
HEAT EXCHANGER EFFECTIVENESS
• Turbine exhaust gasses reject heat at the rate of: m t C p46 (T 04 -T 06 ) • Compressor delivery receives heat at a rate of: m c C p25 (T 05 -T 02 ) • If m c = m t Then C p46 (T 04 -T 06 ) = C p25 (T 05 -T 02 ) Chapter2 Shaft Power Cycles 51
HEAT EXCHANGER EFFECTIVENESS
• One possible measure of performance is the ratio of the actual energy received by the cold air to the maximum possible value. Thus; • HE effectiveness = C p25 (T 05 -T 02 ) / C p24 (T 04 -T 02 ) • over the mean temperature ranges if C p25 = C p24 HE effectiveness = ( T 05 -T 02 ) /(T 04 -T 02 ) • Most generally : HE effectiveness = m c C p25 ( T 05 -T 02 )
/
m t C p24 (T 04 -T 02 ) Chapter2 Shaft Power Cycles 52
MECHANICAL LOSSES
• In all Gas Turbines, the power necessary to drive the compressor is direct, so any loss that occurs is due to bearing friction and windage ; • this amounts to about 1 % • If the transmission efficiency is h m , then
• w
ct
= C p12 (T 02 -T 01 )/ h m ( h m = 99 % ) • Any power used to drive auxillary components such as fuel and oil pumps, gearing losses are ussually accounted for by subtracting from the net output.
Chapter2 Shaft Power Cycles 53
Variation of Specific Heat
C p / C v = C p - C v = R C p = g R/( g -1 ) = g
R
/( g - 1 )M
for air
C pa = 1.005 kJ/kg K , g a =1.4
for combustion gasses
C pg g g = 1.148 kJ/kgK , =1.333
R air = 0.287 kJ/kg-K C p changes with
T
, but the change with
p
is negligible Chapter2 Shaft Power Cycles 54
Fuel/Air Ratio, Combustion Efficiency and Cycle Efficiency
• •
Combustion problem in GT is to calculate the Fuel/Air (F/A) ratio = "f" required to transform unit mass of air at T 02 and f kg of fuel at the fuel temperature T f to ( 1 + f ) kg of products at T 03 .
(
m h i i
03
h a
02
fh f
) 0
Since the process is adiabatic, the energy equation is simply;
(
m h i i
03
h a
02
fh f
) 0 •
where m i h i = mass of product i per unit mass of air = its specific enthalpy
Chapter2 Shaft Power Cycles 55
Fuel/Air Ratio, Combustion Efficiency and Cycle Efficiency
•
Making use of the enthalpy of reaction unit mass of fuel at a reference temperature of 25 o C H 25 as
(1
= - ( net calorific value) = Q net,p ; the equation can be expanded
pg
(
T
03 298) 25
C pa
(298
T
02 )
fC pf
(298
T f
) 0
C pg = Specific heat of products over the temperature range 298K
T 03 H 25 = Enthalpy of reaction (lower heating value) a negative quantity = [-43100 kJ/kg]
Chapter2 Shaft Power Cycles 56
Fuel/Air Ratio, Combustion Efficiency and Cycle Efficiency
• • •
Therefore, for a given fuel and the values of T 02 can be calculated. & T 03 ; "f" A chart is given in the book to determine the "f" for a given combustion temperature rise (T 03 -T 02 ) for various T 02 's. A convenient method of allowing for combustion losses is to introduce a combustion efficiency defined by
h b Chapter2 Shaft Power Cycles 57
Fuel/Air Ratio, Combustion Efficiency and Cycle Efficiency
• •
For an air mass flow ma ; total fuel consumption is f*m a .
The specific fuel consumption;
sfc
a N a
3600.
f w N
[ kg/kW-h ]
• w
N = specific net work output in kW/( kg/s ) of air flow
Chapter2 Shaft Power Cycles 58
Fuel/Air Ratio, Combustion Efficiency and Cycle Efficiency
•
Then the cycle efficiency is
h
f a N
3600 •
where Q net,p = net calorific value = -H 25
Chapter2 Shaft Power Cycles 59
CHAPTER 2
SHAFT POWER CYCLES III Comparative Performance of Practical Cycles
1.
Simple GT Cycle Fig. 2.12 Cycle efficiency and specific output of simple gas turbine With component losses : h (T 03 , r p ) for each cycle max. temperature T 03 , h has a peak value at a paticular r p
.
Chapter2 Shaft Power Cycles 61
1.
Simple GT Cycle
• • • • • •
Optimum press ratio for maximum efficiency differs from that for maximum specific work output.
But
h
(r p ) is quite flat around the peak so. the lowest r p will give an accepted performance is chosen.
which As T 03 increases higher r p is advantageous As T 03 increases η increases. Therefore component losses compared to net work output gets less important.
As T 03 increases
w
s increases appreciably. This is important for aircaft GT since SIZE of GT is smaller for a given power.
*Increasing T a ;
w
net and efficiency
h
both decreases.
Chapter2 Shaft Power Cycles 62
2.Heat Exchange Cycle
•
Fig. 2.13 Heat - exchange cycle HE slightly reduces
w
s But effects
h
due to additional pressure losses.
(increases) and reduces the optimum press ratio for
h
max .
Chapter2 Shaft Power Cycles 64
Chapter2 Shaft Power Cycles 65
3.Heat Exchange Cycle with Reheat or Intercooling Fig. 2.15 Cycle with Heat-Exchange and Reheat
Chapter2 Shaft Power Cycles 66
3.Heat Exchange Cycle with Reheat or Intercooling
• • • •
With HE, addition of REHEAT improves the specific work output considerably without loss of efficiency. The gain in efficiency due to Reheat obtained with the ideal cycle is not realized in practice * partly because of the additional pressure loss in the reheat chamber and the inefficiency of the expansion process, * but primarily because the effectiveness of the HE quite low and the additional energy in the exhaust gas is not wholly recovered.
Chapter2 Shaft Power Cycles 67
3.Heat Exchange Cycle with Reheat or Intercooling
• • • • •
Reheat has not been widely used in practice because the additional "CC" and the associated control problems Can off-set the advantage gained from the decrease in size of the main components consequent upon the increase in specific output.
Intercooling, although increases specific output and cycle efficiency; intercoolers tend to be bulky and if they require cooling water, the self contained nature of the GT is lost.
In practice most GT utilize either a higher pressure ratio simple cycle or a low pressure ratio HE cycle. The other additions to the cycles mentioned do not nominally show sufficient advantage to offset the increased complexity and capital cost.
Chapter2 Shaft Power Cycles 68
Cogas Cycles and Cogeneration Schemes
• • •
In the exhaust gases from a GT there is still an ample amount of energy. This energy could be utlized.
•
The only limitation is the exhaust temperature (Stack Temp.) should not be reduced much below 170 o C to avoid dewpoint corrosion problems due to the sulphur content of the fuel. The exhaust heat could be used in various ways. It could be wholly, used to produce steam in a waste heat boiler for a steam turbine to angment the shaft power produced, it is called as COGAS-"Combined Gas/Steam Cycle Power, "plant
Chapter2 Shaft Power Cycles 69
Cogas Cycles and Cogeneration Schemes
• •
Alternatively the exhaust heat maybe used to produce hot water or steam for same chemical process, for district or factory heating, for a distillation plant, (for and absorption refrigerator in water chilling or air conditioning plant). The shaft power there will normally be used to produce electricity This system is refered to as a COGENERATION or TOTAL ENERGY PLANT.
Chapter2 Shaft Power Cycles 70
Cogas Cycles
71
Cogas Cycles
•
For any given T 03 of GT r c increases
T 04 (exhaust) decreases. Thus the heat available to the steam cycle decreases.
h gas (fall in boiler) steam outlet) =
h (rise between feedwater inlet and
T terminal ≥ 20°C &
T pinchpt ≥20°C if the boiler is to be of economic size.
Chapter2 Shaft Power Cycles 72
•
Cogas Cycles
A reduction in T 4 ;
P steam decrease that can be used for steam cycle.
•
In the combined plant, therefore, selection of a higher compressor pressure ratio to improve the gas turbine efficiency may lead to a fall in steam cycle efficiency and no net gain in overall thermal efficiency.
•
In practice, however, a higher pressure ratio is accompanied by a higher turbine inlet temperature and the most advanced combined cycles use high pressure ratio gas turbines.
Chapter2 Shaft Power Cycles 73
Cogas Cycles
•
Most COGAS plants are produced by adding a suitable exhaust heated Rankine Cycle conditions which matches best to GasTurbine.
• •
COGAS plants for large base load generating stations
h
overall is not the ultimate citerion. The cost of electricity sold is ultimate and this also depends on the capital cost of the plant.
•
Due to the abundancy of choices it is very difficult to optimize these cycles. These have efficiencies 43-50 %
Chapter2 Shaft Power Cycles 74
Cogeneration Plant
•
Fig. 2.16 Cogeneration plant This one is suitable for applications in which the required ratio of heat
75
Cogeneration Plant
•
When only power required,then waste heat boiler is completely bypassed.
•
When max. heat/power ratio is required the HE is bypassed and supplemantary fuel is burnt in the boiler.
•
The overall efficiency may be defined as
h
= [( net work + useful heat output ) / unit air mass flow ] / [ f.Q
net,p ]
• • • •
Useful heat output per unit air mass flow is C p [ T in - 443 ] For high values of Q/HP r c has little effect on
h
r c choosen to give
w
max ,hence minimum capital cost. Heat exchanger useful for small Q/Power ratios.
Chapter2 Shaft Power Cycles 76