Chapter_9_lecture_new Gas Power Cycle.pdf

Chapter 9
GAS POWER
CYCLES
Dr Salmiaton
Dr. Tinia Idaty Mohd. Ghazi

2
Objectives
• Evaluate the performance of gas power cycles for which the
working fluid remains a gas throughout the entire cycle.
• Develop simplifying assumptions applicable to gas power
cycles.
• Review the operation of reciprocating engines.
• Analyze both closed and open gas power cycles.
• Solve problems based on the Otto, Diesel, Stirling, and
Ericsson cycles.
• Solve problems based on the Brayton cycle; the Brayton cycle
with regeneration; and the Brayton cycle with intercooling,
reheating, and regeneration.

3
BASIC CONSIDERATIONS IN THE ANALYSIS
OF POWER CYCLES
Modeling is a
powerful
engineering tool
that provides great
insight and
simplicity at the
expense of some
loss in accuracy.
The analysis of many
complex processes can be
reduced to a manageable
level by utilizing some
idealizations.
Most power-producing devices operate on cycles.
Ideal cycle: A cycle that resembles the actual cycle
closely but is made up totally of internally reversible
processes.
Reversible cycles such as Carnot cycle have the
highest thermal efficiency of all heat engines
operating between the same temperature levels.
Unlike ideal cycles, they are totally reversible, and
unsuitable as a realistic model.
Thermal efficiency of heat engines

4
The idealizations and simplifications in the
analysis of power cycles:
1. The cycle does not involve any friction.
Therefore, the working fluid does not
experience any pressure drop as it flows in
pipes or devices such as heat exchangers.
2. All expansion and compression processes
take place in a quasi-equilibrium manner.
3. The pipes connecting the various
components of a system are well
insulated, and heat transfer through them
is negligible.
On both P-v and T-s
diagrams, the area
enclosed by the
process curve
represents the net work
of the cycle = net heat
transfer for the cycle.
On a T-s diagram, the ratio of
the area enclosed by the cyclic
curve to the area under the
heat-addition process curve
represents the thermal
efficiency of the cycle. Any
modification that increases the
ratio of these two areas will also
increase the thermal efficiency
of the cycle.

5
THE CARNOT CYCLE AND ITS
VALUE IN ENGINEERING
P-v and T-s diagrams of
a Carnot cycle.
A steady-flow Carnot engine.
The Carnot cycle is composed of four totally
reversible processes: isothermal heat addition,
isentropic expansion, isothermal heat rejection, and
isentropic compression.
For both ideal and actual cycles: Thermal
efficiency increases with an increase in the average
temperature at which heat is supplied to the system
or with a decrease in the average temperature at
which heat is rejected from the system.

6
AIR-STANDARD ASSUMPTIONS
The combustion process is replaced by
a heat-addition process in ideal cycles.
Air-standard assumptions:
1. The working fluid is air, which
continuously circulates in a closed loop
and always behaves as an ideal gas.
2. All the processes that make up the
cycle are internally reversible.
3. The combustion process is replaced by
a heat-addition process from an
external source.
4. The exhaust process is replaced by a
heat-rejection process that restores the
working fluid to its initial state.
Cold-air-standard assumptions: When the working fluid is considered to
be air with constant specific heats at room temperature (25°C).
Air-standard cycle: A cycle for which the air-standard assumptions are
applicable.

7
AN OVERVIEW OF RECIPROCATING ENGINES
Nomenclature for reciprocating engines.
• Spark-ignition (SI) engines
• Compression-ignition (CI) engines
Compression ratio
Mean effective
pressure

8
OTTO CYCLE: THE IDEAL CYCLE FOR
SPARK-IGNITION ENGINES
Actual and ideal cycles in spark-ignition engines and their P-v diagrams.

9
Schematic of a two-stroke
reciprocating engine.
The two-stroke engines are
generally less efficient than
their four-stroke
counterparts but they are
relatively simple and
inexpensive, and they have
high power-to-weight and
power-to-volume ratios.
T-s diagram of the
ideal Otto cycle.
Four-stroke cycle
1 cycle = 4 stroke = 2 revolution
Two-stroke cycle
1 cycle = 2 stroke = 1 revolution
Two-stroke Diesel engine

10
Thermal efficiency of the ideal
Otto cycle as a function of
compression ratio (k = 1.4).
The thermal efficiency of the Otto
cycle increases with the specific heat
ratio k of the working fluid.
In SI engines, the
compression
ratio is limited by
autoignition or
engine knock.
No work involved during qin
and qout since v constant
Processes 1-2 & 3-4 isentropic; v2 = v3 & v4= v1
At cold-air-standard
assumption

11
Example 1: An ideal Otto cycle has a compression ratio of 8. At the beginning of the
compression process, air is at 100 kPa and 17oC, and 800 kJ/kg of heat is
transferred to air during the constant-volume heat –addition process. Assuming
air as ideal gas with variable specific heats with temperature, calculate:
(a) Maximum temperature and pressure that occur during the cycle,
(b) Net work output
(c) Thermal efficiency
(d) Mean effective pressure for the cycle

12
DIESEL CYCLE: THE IDEAL CYCLE
FOR COMPRESSION-IGNITION ENGINES
In diesel engines, the spark plug is replaced
by a fuel injector, and only air is compressed
during the compression process.
In diesel engines, only air is compressed during the
compression stroke, eliminating the possibility of
autoignition (engine knock). Therefore, diesel engines
can be designed to operate at much higher compression
ratios than SI engines, typically between 12 and 24.
• 1-2 isentropic
compression
• 2-3 constant-
pressure heat
addition
• 3-4 isentropic
expansion
• 4-1 constant-
volume heat
rejection.

13
Thermal
efficiency of
the ideal Diesel
cycle as a
function of
compression
and cutoff
ratios (k=1.4).
Cutoff
ratio
for the same compression ratio

14
Example 2: An ideal Diesel cycle with air as the working fluid has a compression ratio
of 18 and a cut off ratio of 2. At the beginning of the compression process, the
working fluid is at 100 kPa, 27oC, and 1917 cm3. Utilizing the cold-air-standard
assumptions, calculate:
(a) Temperature and pressure of air at the end of each process,
(b) Net work output and thermal efficiency
(c) Mean effective pressure for the cycle

15
STIRLING AND ERICSSON CYCLES
A regenerator is a device that
borrows energy from the working
fluid during one part of the cycle
and pays it back (without
interest) during another part.
Stirling cycle
• 1-2 T = constant expansion (heat addition from the external source)
• 2-3 v = constant regeneration (internal heat transfer from the working fluid to the
regenerator)
• 3-4 T = constant compression (heat rejection to the external sink)
• 4-1 v = constant regeneration (internal heat transfer from the regenerator back to
the working fluid)

16
The execution of the Stirling cycle. A steady-flow Ericsson engine.
The Ericsson cycle is very much like the
Stirling cycle, except that the two constant-
volume processes are replaced by two
constant-pressure processes.
Both the Stirling and Ericsson cycles are
totally reversible, as is the Carnot cycle,
and thus:
The Stirling and Ericsson cycles
give a message: Regeneration
can increase efficiency.

17
Example 3: An ideal Stirling cycle operates with 1 kg of air between thermal energy
reservoirs at 27oC and 527oC. The maximum cycle pressure is 2000 kPa and the
minimum cycle pressure is 100 kPa. Calculate:
(a) Cycle’s thermal efficiency, and
(b) Net work produced each time the cycle is executed

18
BRAYTON CYCLE: THE IDEAL CYCLE FOR
GAS-TURBINE ENGINES
An open-cycle gas-turbine engine. A closed-cycle gas-turbine engine.
The combustion process is replaced by a constant-pressure heat-addition
process from an external source, and the exhaust process is replaced by a
constant-pressure heat-rejection process to the ambient air.
1-2 Isentropic compression (in a compressor)
2-3 Constant-pressure heat addition
3-4 Isentropic expansion (in a turbine)
4-1 Constant-pressure heat rejection

19
T-s and P-v diagrams for
the ideal Brayton cycle.
Pressure
ratio
Thermal
efficiency of the
ideal Brayton
cycle as a
function of the
pressure ratio.
Processes 1-2 and 3-4
isentropic,
P2=P3 and P4=P1

20
For fixed values of Tmin and Tmax, the net
work of the Brayton cycle first increases
with the pressure ratio, then reaches a
maximum at rp = (Tmax/Tmin)k/[2(k - 1)], and
finally decreases.
The fraction of the turbine work used to drive
the compressor is called the back work ratio à
high back work ratio requires larger turbine to
provide additional power to compressor.
The two major application areas of gas-
turbine engines are aircraft propulsion
and electric power generation.
The highest temperature in the cycle (end of
combustion process – state 3) is limited by
the maximum temperature that the turbine
blades can withstand. This also limits the
pressure ratios that can be used in the cycle.
Common rp of gas turbine = 11-16
The air in gas turbines supplies the
necessary oxidant for the combustion of the
fuel, and it serves as a coolant to keep the
temperature of various components within
safe limits. An air–fuel ratio of 50 or above is
not uncommon.

21
Development of Gas Turbines – to increase cycle efficiency
1. Increase the turbine inlet (or firing) temperatures (new material, coating, cooling,
etc.)
2. Increase the efficiencies of turbomachinery components (improve design turbines,
compressors):
3. Add modifications to the basic cycle (intercooling, regeneration or recuperation, and
reheating).
Deviation of Actual Gas-
Turbine Cycles from Idealized
Ones
The deviation of an actual gas-
turbine cycle from the ideal Brayton
cycle as a result of irreversibilities.
Reasons: Irreversibilities in turbine and
compressors, pressure drops, heat losses
Isentropic efficiencies of the compressor
and turbine

22
Example 4: Air enters the compressor of a gas-turbine engine at 300 K and 100 kPa,
where it is compressed to 700 kPa and 580 K. Heat is transferred to air in the
amount of 950 kJ/kg before it enters the turbine. For a turbine efficiency of 86%,
calculate:
(a) Fraction of turbine work output used to drive the compressor,
(b) Thermal efficiency
Assume variable specific heats for air

23
THE BRAYTON CYCLE WITH
REGENERATION
A gas-turbine engine with regenerator.
T-s diagram of a Brayton
cycle with regeneration.
In gas-turbine engines, the temperature of the exhaust
gas leaving the turbine is often considerably higher than
the temperature of the air leaving the compressor.
Therefore, the high-pressure air leaving the compressor
can be heated by the hot exhaust gases in a counter-flow
heat exchanger (a regenerator or a recuperator).
The thermal efficiency of the Brayton cycle increases as a
result of regeneration since less fuel is used for the same
work output.
Note: only recommended
when Texhaust from turbine
is higher than Texit from
compressor

24
T-s diagram of a Brayton
cycle with regeneration.
Effectiveness
of regenerator
Effectiveness under cold-
air standard assumptions
Under cold-air
standard assumptions
Thermal
efficiency of
the ideal
Brayton cycle
with and
without
regeneration.
The thermal efficiency
depends on the ratio of the
minimum to maximum
temperatures as well as the
pressure ratio.
Regeneration is most
effective at lower pressure
ratios and low minimum-to-
maximum temperature ratios.
Assuming ΔKE = ΔPE = 0;
regenerator = well insulated

25
THE BRAYTON CYCLE WITH
INTERCOOLING, REHEATING,
AND REGENERATION
A gas-turbine engine with two-stage compression with intercooling, two-stage
expansion with reheating, and regeneration and its T-s diagram.
For minimizing work input to
compressor and maximizing
work output from turbine:

26
Comparison of
work inputs to
a single-stage
compressor
(1AC) and a
two-stage
compressor
with
intercooling
(1ABD).
Multistage compression with intercooling: The work required to compress a gas between two
specified pressures can be decreased by carrying out the compression process in stages and
cooling the gas in between. This keeps the specific volume as low as possible.
Multistage expansion with reheating keeps the specific volume of the working fluid as high as
possible during an expansion process, thus maximizing work output.
Intercooling and reheating always decreases the thermal efficiency unless they are accompanied
by regeneration. Intercooling reduce average T when heat is added; Reheating increase average T
when heat is rejected.
As the number of compression and expansion
stages increases, the gas-turbine cycle with
intercooling, reheating, and regeneration
approaches the Ericsson cycle & thermal
efficiency approaches Carnot efficiency.

27
Example 5: Consider an ideal gas-turbine cycle with two stages of compression and
two stages of expansion. The pressure ratio across each stage of the compressor
and turbine is 3. The air enters each stage of compressor at 300 K and each stage
of the turbine at 1200 K. Calculate:
(a) Back work ratio,
(b) Thermal efficiency when no regenerator is used, and
(c) Thermal efficiency when a regenerator with 75% effectiveness is used.
Assume air is ideal gas with variable specific heats for air

28
IDEAL JET-PROPULSION CYCLES
In jet engines, the high-
temperature and high-
pressure gases leaving the
turbine are accelerated in a
nozzle to provide thrust.
Gas-turbine engines are widely used to power aircraft because they are light and
compact and have a high power-to-weight ratio.
Aircraft gas turbines operate on an open cycle called a jet-propulsion cycle.
The ideal jet-propulsion cycle differs from the simple ideal Brayton cycle in that the
gases are not expanded to the ambient pressure in the turbine. Instead, they are
expanded to a pressure such that the power produced by the turbine is just
sufficient to drive the compressor and the auxiliary equipment.
The net work output of a jet-propulsion cycle is zero. The gases that exit the turbine
at a relatively high pressure are subsequently accelerated in a nozzle to provide the
thrust to propel the aircraft.
Aircraft are propelled by accelerating a fluid in the opposite direction to motion. This
is accomplished by either slightly accelerating a large mass of fluid (propeller-
driven engine) or greatly accelerating a small mass of fluid (jet or turbojet engine)
or both (turboprop engine).

29
Basic components of a turbojet engine and the T-s diagram for the ideal turbojet cycle.
Propulsive power is
the thrust acting on the
aircraft through a
distance per unit time.
Propulsive efficiency
Propulsive power
Thrust (propulsive force)

30
Modifications to Turbojet Engines
Energy supplied to an aircraft
(from the burning of a fuel)
manifests itself in various forms.
A turbofan engine.
The first airplanes built were all propeller-
driven, with propellers powered by engines
essentially identical to automobile engines.
Both propeller-driven engines and jet-
propulsion-driven engines have their own
strengths and limitations, and several attempts
have been made to combine the desirable
characteristics of both in one engine.
Two such modifications are the propjet engine
and the turbofan engine.
The most widely used
engine in aircraft
propulsion is the
turbofan (or fanjet)
engine wherein a large
fan driven by the
turbine forces a
considerable amount
of air through a duct
(cowl) surrounding the
engine.

31
A modern jet engine
used to power Boeing
777 aircraft. This is a
Pratt & Whitney
PW4084 turbofan
capable of producing
374 kN of thrust. It is
4.87 m long, has a 2.84
m diameter fan, and it
weighs 6800 kg.
A turboprop engine. A ramjet engine.
Various engine types:
Turbofan, Propjet, Ramjet, Sacramjet, Rocket

Chapter_9_lecture_new Gas Power Cycle.pdf

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