1. VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY
U5AEA18 PROPULSION -II
Mr. SYED ALAY HASHIM
Assistant Professor
Department of Aeronautical Engineering
VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY
Chennai
INDIA

2. POWER POINT PRESENTATION
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

13. SCRAM JET

14. 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)

15. PERFORMANCE PLOT

16. TURBO RAMJETS
RAM ROCKET

17. THRUST CHAMBER

18. ROCKET PARAMETERS

19. NOZZLE DESIGN PARAMETERS

20. NOZZLE CONFIGURATIONS

21. ROCKET ENGINE SYSTEM (PRESSURE & PUMP FEED)

23. 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)

24. THRUST CHAMBER DETAILS

25. PROPELLANT INJECTOR

26. INJECTOR FACE

27. HYBRID ROCKET SYSTEM .

28. SOLID PROPELLANT INGREDIENTS

29. SOLID PROPELLANT OXIDIZERS

30. SOLID PROPELLANT GRAIN DESIGN

31. SOLID PROPELLANT COMBUSTION

32. 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.

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

34. SOLAR SAIL

35. THANK YOU