Download - ADVANCED GAS TURBINE THEORY
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AE 60022AE 40030
ADVANCED GAS TURBINE THEORY
Dr. Chetan S. Mistry
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Lecture-1ADVANCED GAS TURBINE THEORY
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Dr. Chetan S. Mistry
1. General propulsion systems,2. Theory of intakes and exhaust systems,
thrust reversers,3. Jet engine noise and methods of noise
reduction,4. Cycle analysis of one and two spool
engines,5. Equilibrium running of gas turbine engines,6. Design and off-design performance,
Component matching, Transient behaviour,7. Design consideration of axial flow
multistage machines, stream line curvaturemethod, radial equilibrium equation
1. Introduction to Jet Propulsion systems2. Types of aircraft engines3. Jet engine Thermal Cycle analysis4. Two spool and Three spool configurations5. Engine Installation & Theory of Intakes6. Exhaust nozzles7. After burners and Thrust reverser8. Design considerations for axial flow
turbomachines9. Design and off-design performance10.Component matching
AE 60022 / AE 40030 ADVANCED GAS TURBINE THEORY
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Dr. Chetan S. Mistry
Course Pre-requisites
Introduction to Aerospace Propulsion,
or
A course in Engineering Thermodynamics
Additionally :
A course in Fluid Mechanics and Gas dynamicswould be helpful
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Work Ethics• DO participate and ask questions. For order in class, raise your hand when
asking a question.• BRING all specified ENGINEERING equipment like Notebook, Calculator,
Gas table.• HAND IN all Assignments ON TIME! Failure to do so may result in
consequences…YOU KNOW..• SHOW CARE and concern for each other. Help one another in homework.
BUT NO COPYING OF ENTIRE ASSIGNMENTS!• Design projects--- Group work• IF you are LATE in class Do not take permission….. Take your seat without
disturbing whole class.• Attendance---- Be Physically and Mentally present.
Dr. Chetan S. Mistry
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Dr. Chetan S. Mistry
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Course Code Course Name
Teaching Scheme
Examination Scheme
Hours Component Weightage
Hours / Week C SEE MS
CE
+
Att.
ESL T P
AE60022
AE 40030ADVANCED GAS TURBINE THEORY
3 ‐ 0 3 3 0.20 0.30 0.50
Course Evaluation
Dr. Chetan S. Mistry
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1. Introduction to Propulsion systems2. Types of aircraft engines3. Jet engine Thermal Cycle analysis4. Two spool and Three spool configurations5. Engine Installation &Theory of Intakes6. Exhaust nozzles7. After burners and Thrust reverser8. Design considerations for axial flow
turbomachines9. Design and off-design performance10.Component matching
Dr. Chetan S. Mistry
Weekly -3 Lectures
4 Lectures
7 Lectures
8 Lectures
8 Lectures
6 Lectures
7 Lectures
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Dr. Chetan S. Mistry
0. Class notes / Lecture notes1. Saravanamuttoo, H.I.H., Rogers G.F.C., Cohen H.; Gas Turbine Theory, 2001, Pearson2. El-Sayed Ahmed, Aircraft Propulsion and gas Turbine Engines , 2008, T&F,CRC press.3. Saeed Farokhi, Aircraft Propulsion, 2009, John Wiley & Sons, Inc.4. Kaluse Hunecke , Jet Engines-Fundamentals of theory, design and Operation, Motor books
International5. Hill Philip, Peterson Carl, Mechanics and Thermodynamics of Propulsion, 1992, Addison
Wesly6. Mattingly J D , Elements of Propulsion – Gas Turbines and Rockets, 2006, AIAA Education
series.7. Mattingly J D , Aircraft engine design, 2006, AIAA Education series.8. Gordon C. Oates, Aircraft Propulsion Systems Technology and Design, 1989, AIAA
Education series.9. Roy Bhaskar, Aircraft Propulsion, 2008, Elsevier (India)
Text/References
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Dr. Chetan S. Mistry
Aerospace Engines
Reciprocating engines
Air breathing Engines
Non-Air breathing Engines
Jet propulsion engines
ScramjetRamjet Pulsejet Gas turbineor
Jet engine
Turbo ramjet Turbo rocket
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Dr. Chetan S. Mistry
Jet Engines
Turbojet Turboprop Turboshaft Turbofan Ducted fanEngine
UnductedPropfan
Non A/B With A/B Propeller/ RotorOn Compressor shaft
Propeller/ RotorDriven by free Turbine
Single propeller fan
Counter rotating propeller fan
NextSlide
Industrial turbine
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Dr. Chetan S. Mistry
Turbofan Engines
Forward fan Aft fan
Mixed flowHigh Bypass
ratioLow Bypass
ratio
Non afterburning Afterburning
Geared fan
Ungeared fan
Single spool
Two spool
Three spool
Unmixed flow
Non A/B With A/B
Advancedducted fan
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Dr. Chetan S. Mistry
Evolution of aero engines.
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Lecture-2ADVANCED GAS TURBINE THEORY
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Turbojet Engine
After burner Number of spools
With After burner
Without After burner
Single spool Two spool
Axial flow compressor
Centrifugal compressor
Axial-Centrifugalcompressor
Dr. Chetan S. Mistry
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Single spool Turbojet Engine
Diff
user
Turb
ine Nozzle
Com
pres
sor
CC
Dr. Chetan S. MistryJ85‐GE‐17A turbojet engine from General Electric (1970)
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Dr. Chetan S. Mistry
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Dr. Chetan S. Mistry
Westinghouse J34Single spool Turbojet Engine
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Double spool Turbojet Engine
Dr. Chetan S. Mistry
Single spool Turbojet Engine
MIG23 afterburner
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Why afterburner ?
• After burning (reheat) method which augmenting the basic thrust of engine.
• Increasing thrust without adding extra weight or complexity
• Improve aircraft takeoff, climb and combat performance for supersonic aircraft.
time
Alti
tude
Withoutafterburning
Withafterburning
Dr. Chetan S. Mistry
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Dr. Chetan S. Mistry
Turbojet Engine
• Use of high exhaust gas velocity increases the Thrust developed by the engine.
• Simplicity of design,
• Efficient at supersonic speed.
• Improvement in efficiency.• SFC• Power at supersonic flight.• Noise
????
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Lecture-3ADVANCED GAS TURBINE THEORY
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Dr. Chetan S. Mistry
Turbofan Engines
Forward fan Aft fan
Mixed flowHigh Bypass
ratioLow Bypass
ratio
Non afterburning Afterburning
Geared fan
Ungeared fan
Single spool
Two spool
Three spool
Unmixed flow
Non A/B With A/B
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Optional: Afterburner, Convergent or Con/Di Nozzle
Compressors TurbinesCombustionChamber Nozzle/Exhaust
Inlet
•At nozzle exit, fluid flow at primary and secondary nozzle are mixed.
Single-spool Turbofan engine
Dr. Chetan S. Mistry
core
fan
Hot
Cold
mm
mm
airflowPrimary airflow Bypass ratio Bypass
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Two spool turbofan - Low bypass ratio
HPCompressors
LP TurbinesBurner
Divergent NozzleAir Intake
HP Turbine
LPCompressors
Dr. Chetan S. Mistry
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Dr. Chetan S. Mistry
GE Honda HF120 Aero Engine
Maximum Thrust:takeoff thrust: 2,050 lbf (9.1 kN)OPR: 24BR: 2.9SFC: <0.7 lb/lbf/h (20 g/kN/s)T‐to‐W: >5