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U5AEA18 PROPULSION -II

U5AEA18 PROPULSION -II. 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. TURBINE VELOCITY TRIANGLE. BLADE EFFICIENCY. STAGE WISE WORK GENERATION.

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U5AEA18 PROPULSION -II

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  1. U5AEA18PROPULSION -II 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. TURBINE VELOCITY TRIANGLE

  4. BLADE EFFICIENCY

  5. STAGE WISE WORK GENERATION

  6. THERMODYNAMIC PLOT

  7. DEGREE OF REACTION

  8. TURBINE BLADE COOLING

  9. RAMJET

  10. RAMJET A ramjet, sometimes referred to as a flying stovepipe, or an athodyd which is an abbreviation of Aero thermodynamic duct, is a form of air breathing jet engine using the engine's forward motion to compress incoming air, without a rotary compressor. Ramjets cannot produce thrust at zero airspeed, thus they cannot move an aircraft from a standstill. Ramjets therefore require assisted take off like JATO to accelerate it to a speed where it begins to produce thrust. Ramjets work most efficiently at supersonic speeds around Mach 3. This type of engine can operate up to speeds of Mach 6.

  11. SUPERSONIC INLET OPERATION

  12. SCRAM JET

  13. A scramjet (supersonic combustion ramjet) is a variant of a ramjet air breathing jet engine in which combustion takes place in supersonic airflow. As in ramjets, a scramjet relies on high vehicle speed to forcefully compress and decelerate the incoming air before combustion (hence ramjet), but whereas a ramjet decelerates the air to subsonic velocities before combustion, airflow in a scramjet is supersonic throughout the entire engine. This allows the scramjet to operate efficiently at extremely high speeds: theoretical projections place the top speed of a scramjet between Mach 12 (9,100 mph; 15,000 km/h) and Mach 24 (18,000 mph; 29,000 km/h)

  14. PERFORMANCE PLOT

  15. TURBO RAMJETS RAM ROCKET

  16. THRUST CHAMBER

  17. ROCKET PARAMETERS

  18. NOZZLE DESIGN PARAMETERS

  19. NOZZLE CONFIGURATIONS

  20. ROCKET ENGINE SYSTEM (PRESSURE & PUMP FEED)

  21. LIQUID PROPELLANT LIQUID FUELS • Hydrocarbon Fuels • Liquid Hydrogen (H2) • Hydrazine (N2H4) • Unsymmetrical Dimethyl hydrazine [(CH3)2NNH2] • Monomethylhydrazine (CH3NHNH2) LIQUID OXIDIZERS • Liquid Oxygen (02) • Hydrogen Peroxide (H202) • Nitric Acid (HNO3) • Nitrogen Tetroxide (N204)

  22. THRUST CHAMBER DETAILS

  23. PROPELLANT INJECTOR

  24. INJECTOR FACE

  25. HYBRID ROCKET SYSTEM .

  26. SOLID PROPELLANT INGREDIENTS

  27. SOLID PROPELLANT OXIDIZERS

  28. SOLID PROPELLANT GRAIN DESIGN

  29. SOLID PROPELLANT COMBUSTION

  30. TYPES OF ELECTRICAL ROCKET 1. Electrothermal- Propellant is heated electrically and expanded thermodynamically; i.e., the gas is accelerated to supersonic speeds through a nozzle, as in the chemical rocket. 2. Electrostatic- Acceleration is achieved by the interaction of electrostatic fields on non-neutral or charged propellant particles such as atomic ions, droplets, or colloids. 3. Electromagnetic- Acceleration is achieved by the interaction of electric and magnetic fields within a plasma. Moderately dense plasmas are hightemperature or nonequilibrium gases, electrically neutral and reasonably good conductors of electricity.

  31. ELECTRICAL ROCKETS ION ROCKET MAGNETOPLASMA ROCKET ARC-JET ROCKET

  32. SOLAR SAIL

  33. THANK YOU

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