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U3AEA04 ELEMENTS OF AERONAUTICS

U3AEA04 ELEMENTS OF AERONAUTICS. Mr. SYED ALAY HASHIM Assistant Professor Department of Aeronautical Engineering VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY Chennai INDIA. I to V UNIT POWER POINT PRESENTATION. AIRCRAFT COMPONENTS. TYPES OF WING. Monoplane Biplane Tandem wing

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U3AEA04 ELEMENTS OF AERONAUTICS

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  1. U3AEA04ELEMENTS OF AERONAUTICS Mr. SYED ALAY HASHIM Assistant Professor Department of Aeronautical Engineering VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY Chennai INDIA

  2. I to V UNIT POWER POINT PRESENTATION

  3. AIRCRAFT COMPONENTS

  4. TYPES OF WING • Monoplane • Biplane • Tandem wing • Triplane  • Quadruplane  • Multiplane  • Canard wing

  5. SWEEP WING

  6. Leading edge extensions of various kinds

  7. AIRCRAFT HISTORICAL RECORDS

  8. 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

  9. Gas Turbine Cycle Single stage Ideal gas turbine cycle Gas Turbine Cycle Two stage turbine cycle

  10. Gas Turbine Cycle Two stage Compressor and Turbine cycle

  11. Jet Propulsion Cycle In practical or actual cycle Entropy is not constant

  12. Jet EngineBasic Components

  13. 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

  14. Compressor • Axial flow • Good for high compression ratios (20:1) • Most commonly used

  15. Turbine • Convert the kinetic energy into expansion work • It is used to drive the compressor as well as • propeller shaft

  16. Comparison of Gas Turbine and Piston Engine

  17. Classification of Engine Engine Air Breathing Engine Non-Air Breathing Engine (Using atm air to produced Power) (Presents of Fuel and absents of Air instead of Air + Oxidizer. Hypersonic vehicles, Operating Mach No : 15 to 20) Jet Engines Reciprocating Engines (Propulsive thrust is produced by jet) Rocket Engine (No moving parts) Gas Turbine Engine Non-Gas Turbine Engine (No moving parts) (Available moving parts like Compressor and Turbine) Ramjet Scramjet Pulsejet Turbojet Turboprop Turbofan Turbo-shaft

  18. Turbojet • Chemical energy is converted into mechanical energy • 100% Thrust produced by Nozzle • Operating Mach No: 1 to 2 • Supersonic Aircraft (1 to 5)

  19. 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)

  20. 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)

  21. 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

  22. 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)

  23. 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

  24. 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

  25. Passenger airplanes

  26. 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

  27. Factors Affecting Thrust • PRESSURE • TEMPERATURE • DENSITY • HUMIDITY • ALTITUDE • FORWARD VELOCITY

  28. 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

  29. After burner

  30. Oxidizer-Fuel Mixture • Evaporative cooling which produces higher pressure and higher mass flow rate

  31. 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

  32. 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

  33. TYPES OF FUSELAGE STRUCTURE

  34. FUSELAGE DESIGN

  35. WING STRUCTURE

  36. Thank you

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