advanced gas turbine theory

AE 60022AE 40030

ADVANCED GAS TURBINE THEORY

Dr. Chetan S. Mistry

Lecture-1ADVANCED GAS TURBINE THEORY


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


Course Pre-requisites

Introduction to Aerospace Propulsion,

or

A course in Engineering Thermodynamics

Additionally :

A course in Fluid Mechanics and Gas dynamicswould be helpful

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.


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


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


Weekly -3 Lectures

4 Lectures

7 Lectures

8 Lectures

8 Lectures

6 Lectures

7 Lectures


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


Aerospace Engines

Reciprocating engines

Air breathing Engines

Non-Air breathing Engines

Jet propulsion engines

ScramjetRamjet Pulsejet Gas turbineor

Jet engine

Turbo ramjet Turbo rocket


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


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


Evolution of aero engines.

Turbojet Engine

After burner Number of spools

With After burner

Without After burner

Single spool Two spool

Axial flow compressor

Centrifugal compressor

Axial-Centrifugalcompressor


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)


Westinghouse J34Single spool Turbojet Engine

Double spool Turbojet Engine


Single spool Turbojet Engine

MIG23 afterburner

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



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

????


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

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


core

fan

Hot

Cold

mm

mm

airflowPrimary airflow Bypass ratio Bypass

Two spool turbofan - Low bypass ratio

HPCompressors

LP TurbinesBurner

Divergent NozzleAir Intake

HP Turbine

LPCompressors



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

advanced gas turbine theory

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