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Lecture 1
AER 403: Aircraft Engines Design
and Construction
DrDr. Farouk. Farouk OwisOwis
Associate ProfessorAssociate Professor
Cairo UniversityCairo University Faculty ofFaculty of
EngineeringEngineering
Aerospace Dept.Aerospace Dept.
Aircraft Engines Design and
Construction
Instructor: Dr. Farouk Mohamed Owis
Lectures: 3 Hours Weekly on Thursday [8:30-10bi-weekly] & [10:15-11:45 weekly]
Section: 2 Hour Weekly
Text Book: S. Dixon, Fluid Mechanics and
Thermodynamics of Turbomachines, 1998
(Available in the library)
Instructor: Dr. Farouk Mohamed Owis
Lectures: 3 Hours Weekly on Thursday [8:30-10bi-weekly] & [10:15-11:45 weekly]
Section: 2 Hour Weekly
Text Book: S. Dixon, Fluid Mechanics and
Thermodynamics of Turbomachines, 1998
(Available in the library)
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References
1. N. Cumpsty, Compressor Aerodynamics,
1989 (Available in the library)
2. R. I. Lewis, Turbomachinery Performance
Analysis", 1996 (Available in the library)
3. J.L.Kerrbrock, Aircraft Gas Turbines and
Engines, 19924. P.G.Hill, G.R.Peterson, Mechanics and
Thermodynamics of Propulsion, 1992
(Available in the library)
References Continued
5. J.D.Mattingly, Elements of Gas Turbine
Propulsion, 2006.
6. H. Cohen, G.C.Rogers, H. Saravanamuttoo,Gas Turbine Theory, 1996
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Course Documents
Lectures, Assignments, ImportantAnnouncements, or other course documentswill be posted on the following web site
www.egypteducation.org
Course key:4304
Everyone is recommended to sign up on thisweb site with his real name in order to haveaccess to the course materials, his grades andreceive e-mails about any possible news.
Course Objectives
To distinguish between the capabilities of
different types of Turbomachines.
To be able to conduct design analysis of
axial flow compressors and turbines.
To be able to predict compressor or
turbine off design performance.
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Knowledge and Understanding
1- Basic knowledge of compressor and turbinecascade characteristics.
2- Stage analysis and effects of its parameters oncompressor and turbine design point
performance.3- Analysis of multistage compressors and turbines.
4- Techniques to Estimate off design performance ofcompressors and turbines.
Course Description
Intended Learning Outcomes of Course
Course Contents Introduction to Gas Turbine Engines (2- lectures)
Types of turbomachiones and non-dimensionalanalysis (1- lect.)
Basic equations (2-lect.)
Introduction to turbomachines (Velocity triangles,2-D cascades) 4-lect.
Axial flow compressor stage analysis
Axial flow compressor Performance
Axial flow turbine analysis
Axial flow turbine performance
3-D flow analysis in turbomachines
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Typical Fighter aircraft Jet Engine
Can you start the design process from here?
Of course no.
We start from broad consideration (concepts)
and increase the level of detail layer after layer.
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Introduction to GasTurbine Engines
Part 1: Classification of gas turbine engines
Part 2: Overall GTE Performance
INTRODUCTION TO GTE
Jet engines are classified into two maincategories:
1- Rocket Engines
Fuel and Oxidizer are carried on the vehicleto reach higher altitudes with better efficiency.There are different categories for the rocketengines depending on the type of thepropellants such as chemical rockets, nuclearrockets and electrical propulsion rockets
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2- Gas Turbine Engines
Fuel only is carried on the vehicle that iswhy they are called air breathing engines.Thus GTE can travel much greaterdistances before refueling. It has alsobetter efficiency than rocket engines but ithas more complicated configurations.
INTRODUCTION TO GTE
Part 1: Classification of gas turbine engines
Turboprop GTE: main propulsive power isobtained by a propeller
High and Low Bypass Turbofan GTE:
Air stream into the engine is divided intoseveral streams to enhance the engineefficiency at lower flight speeds. Propulsivepower is obtained by a single (mixedturbofan engine) or multi jets.
Turbojet GTE: propulsive power is obtainedby the jet
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Schematic diagram of gas generator
Schematic diagram of a turbojet (dual
axial compressor and turbine)
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Types of Gas Turbine Engines (GTE)
2 Spool Turbojet Engine with Afterburner (AB)
In the turbofan, a portion of the turbine work is
used to supply power to the fan. Generally the
turbofan engine is more economical and efficient
than the turbojet engine in the subsonic flight.The thrust specific fuel consumption (TSFC, or
fuel mass flow rate per unit thrust) is lower for
turbofans and indicates a more economical
Turbofan Engines
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2 Stream Turbofan Engine
1 Stream Turbofan Engine with AB
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1 Stream Turbofan Engine -Reversed Flow Combustor
Turbofan EnginesTurbofan EnginesTurbofan Engines
A gas generator that drives a propeller is a
turboprop engine. The expansion of gas through
the turbine supplies the energy required to turnthe propeller. The turboshaft engine is similar to
the turboprop except that power is supplied to a
shaft rather than a propeller. The turboshaft
engine is used quite extensively for supplying
power for helicopters.
Turboprop and Turboshaft
Engines
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Direct Drive Turboprop Engine
Free Turbine Turboprop Engine
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The ramjet engine consists of an inlet, a combustion zone, and a
nozzle. The ramjet does not have the compressor and turbine as the
turbojet does. Air enters the inlet where it is compressed and then
enters the combustion zone where it is mixed with the fuel and
burned. The hot gases are then expelled through the nozzle,
developing thrust. The operation of the ramjet depends on the inlet
to decelerate the incoming air to raise the pressure in the
combustion zone. The pressure rise makes it possible for the
ramjet to operate. The higher the velocity of the incoming air, thegreater the pressure rise. It is for this reason that the ramjet
operates best at high supersonic velocities. At subsonic velocities,
the ramjet is inefficient, and to start the ramjet, air at a relatively
higher velocity must enter the inlet
Ramjet Engine
Schematic diagram of a ramjet