u3aea04 elements of aeronautics mr. syed alay hashim assistant professor department of aeronautical...
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U3AEA04ELEMENTS OF AERONAUTICS
Mr. SYED ALAY HASHIMAssistant Professor
Department of Aeronautical EngineeringVEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY
ChennaiINDIA
I to V
UNIT
POWER POINT PRESENTATION
AIRCRAFT COMPONENTS
TYPES OF WING
1. Monoplane
2. Biplane
3. Tandem wing
4. Triplane
5. Quadruplane
6. Multiplane
7. Canard wing
SWEEP WING
Leading edge extensions of various kinds
AIRCRAFT HISTORICAL RECORDS
IntroductionAEROSPACE ENGINES
• Comprehend the basic components of gas turbine engines and their basic operations
• Comprehend the thermodynamic processes occurring in a gas turbine engines
• Comprehend the support systems associated with gas turbine engines
GAS TURBINE CYCLE
Single stage Ideal gas turbine cycle
Two stage turbine cycle
Gas Turbine Cycle
Gas Turbine Cycle
Two stage Compressor and Turbine cycle
Jet Propulsion Cycle
In practical or actual cycle Entropy is not constant
Jet EngineBasic Components
Compressor
• Supplies high pressure air for combustion process• centrifugal flow and Axial flow
• Centrifugal Compressor• Adv: simple design, good for low compression ratios (5:1), strong• Disadvantage: Difficult to stage, less efficient, high frontal area
CompressorAxial flow • Good for high compression ratios (20:1)• Most commonly used
Turbine
• Convert the kinetic energy into expansion work• It is used to drive the compressor as well as propeller shaft
Comparison of Gas Turbine and Piston Engine
Classification of Engine
Jet Engines Reciprocating Engines(Propulsive thrust is produced by jet)
Air Breathing Engine Non-Air Breathing Engine
(Using atm air to produced Power)
Engine
Gas Turbine Engine Non-Gas Turbine Engine
Turbojet Turboprop Turbofan Turbo-shaft
Ramjet Scramjet Pulsejet
(Presents of Fuel and absents of Air instead of Air + Oxidizer. Hypersonic
vehicles, Operating Mach No : 15 to 20)
(Available moving parts likeCompressor and Turbine)
(No moving parts)
Rocket Engine(No moving parts)
Turbojet
Chemical energy is converted into mechanical energy 100% Thrust produced by Nozzle Operating Mach No: 1 to 2 Supersonic Aircraft (1 to 5)
Turbofan
20 to 40% of Thrust produced by Nozzle 60 to 80% of Thrust produced by Fan Operating Mach No: 0.4 to 0.8 High Subsonic Aircraft (0.3 to 0.8)
Turboprop
20 to 25% of Thrust produced by Nozzle 75 to 80% of Thrust produced by Propeller Operating Mach No: 0.4 to 0.65 Subsonic Aircraft (0.1 to 0.8)
Turbo Shaft
High pressure turbine is used to rotate HP & LP Compressor
Low pressure turbine is used to rotate output Shaft
No Thrust produced in the exit turbine gas
Turbo Shaft
Kinetic energy is converted to Shaft power 100% Thrust produced by Shaft Operating Mach No: 0.4 to 0.8 High speed Subsonic helicopter (0.3 to 0.8)
Pulse Jet
Made up of few moving parts Valved engines use a mechanical valve to control the flow of expanding exhaust,
forcing the hot gas to go out the back of the engine through the tailpipe Starting the engine usually requires forced air and an ignition method such as a
spark plug for the fuel-air mix. It can operate statically
Rocket Engines
A rocket is a machine that develops thrust by the rapid expulsion of matter A rocket is called a launch vehicle when it is used to launch a satellite or other
payload into space Rocket engines are reaction engines The highest exhaust velocities It is used in missile
Passenger airplanes
Sl. No. Description Less Moderate High
1 Specific fuel consumption Turbofan Turboprop Turbojet
2 Noise Level Turbofan Turboprop Turbojet
3 Operating Mach No Turboprop Turbofan Turbojet
4 Take off Thrust Turbojet Turbofan Turboprop
5 Altitude Turboprop Turbofan Turbojet
6 Load Carrying capacity Turbojet Turboprop Turbofan
7 Specific Impulse Turbojet Turboprop Turbofan
Thrust Equation
Total Thrust = Momentum Thrust + Pressure Thrust
mi=mj (mass flow rate) Inlet pressure = Exit pressure Thrust force is the forward motion of engine
Factors Affecting Thrust
PRESSURE
TEMPERATURE
DENSITY
HUMIDITY
ALTITUDE
FORWARD VELOCITY
Methods of Thrust Augmentation
After burning High thrust for short duration It is used only in take-off (or) for high climbing rates Additional fuel is burning in the tail pipe between the turbine and exhaust
nozzle It is increased the jet velocity
Oxidizer-Fuel Mixture Increase the mass flow rate Evaporative cooling which produces higher pressure and higher mass flow
rate Increase the compressor pressure ratio due to reduced compressor air flow
Water and menthol or alcohol Mixture
After burner
Oxidizer-Fuel Mixture
Evaporative cooling which produces higher pressure and higher mass flow rate
Advantages of Gas turbine Engines
• Weight reduction of 70%• Simplicity• Reduced manning requirements• Quicker response time• Faster Acceleration/deceleration• Modular replacement• Less vibrations• More economical
Disadvantages of Gas Turbine Engines
• Many parts under high stress• High pitched noise• Needs large quantities of air• Large quantities of hot exhaust (target)• Cannot be repaired in place
TYPES OF FUSELAGE STRUCTURE
FUSELAGE DESIGN
WING STRUCTURE
Thank you