Download - U5AEA18 PROPULSION -II
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U5AEA18PROPULSION -II
Mr. SYED ALAY HASHIMAssistant Professor
Department of Aeronautical EngineeringVEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY
ChennaiINDIA
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I to V
UNIT
POWER POINT PRESENTATION
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TURBINE VELOCITY TRIANGLE
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BLADE EFFICIENCY
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STAGE WISE WORK GENERATION
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THERMODYNAMIC PLOT
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DEGREE OF REACTION
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TURBINE BLADE COOLING
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RAMJET
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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.
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SUPERSONIC INLET OPERATION
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SCRAM JET
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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)
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PERFORMANCE PLOT
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TURBO RAMJETS
RAM ROCKET
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THRUST CHAMBER
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ROCKET PARAMETERS
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NOZZLE DESIGN PARAMETERS
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NOZZLE CONFIGURATIONS
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ROCKET ENGINE SYSTEM (PRESSURE & PUMP FEED)
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LIQUID PROPELLANT
LIQUID FUELS1. Hydrocarbon Fuels2. Liquid Hydrogen (H2)3. Hydrazine (N2H4)4. Unsymmetrical
Dimethyl hydrazine [(CH3)2NNH2]
5. Monomethylhydrazine (CH3NHNH2)
LIQUID OXIDIZERS1. Liquid Oxygen (02)2. Hydrogen Peroxide
(H202)3. Nitric Acid (HNO3)4. Nitrogen Tetroxide
(N204)
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THRUST CHAMBER DETAILS
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PROPELLANT INJECTOR
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INJECTOR FACE
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HYBRID ROCKET SYSTEM
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SOLID PROPELLANT INGREDIENTS
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SOLID PROPELLANT OXIDIZERS
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SOLID PROPELLANT GRAIN DESIGN
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SOLID PROPELLANT COMBUSTION
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TYPES OF ELECTRICAL ROCKET1. 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.
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ELECTRICAL ROCKETS
ARC-JET ROCKET
ION ROCKET
MAGNETOPLASMA ROCKET
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SOLAR SAIL
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THANK YOU