Transcript Propulsion - 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
I to V
UNIT
POWER POINT PRESENTATION
TURBINE VELOCITY TRIANGLE
BLADE EFFICIENCY
STAGE WISE WORK GENERATION
THERMODYNAMIC PLOT
DEGREE OF REACTION
TURBINE BLADE COOLING
RAMJET
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.
SUPERSONIC INLET OPERATION
SCRAM JET
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)
PERFORMANCE PLOT
TURBO RAMJETS
RAM ROCKET
THRUST CHAMBER
ROCKET PARAMETERS
NOZZLE DESIGN PARAMETERS
NOZZLE CONFIGURATIONS
ROCKET ENGINE SYSTEM (PRESSURE & PUMP FEED)
LIQUID PROPELLANT
LIQUID FUELS
1. Hydrocarbon Fuels
2. Liquid Hydrogen (H2)
3. Hydrazine (N2H4)
4. Unsymmetrical
Dimethyl hydrazine
[(CH3)2NNH2]
5. Monomethylhydrazin
e (CH3NHNH2)
LIQUID OXIDIZERS
1. Liquid Oxygen (02)
2. Hydrogen Peroxide
(H202)
3. Nitric Acid (HNO3)
4. Nitrogen Tetroxide
(N204)
THRUST CHAMBER DETAILS
PROPELLANT INJECTOR
INJECTOR FACE
HYBRID ROCKET SYSTEM
.
SOLID PROPELLANT INGREDIENTS
SOLID PROPELLANT OXIDIZERS
SOLID PROPELLANT GRAIN DESIGN
SOLID PROPELLANT COMBUSTION
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.
ELECTRICAL ROCKETS
ION ROCKET
ARC-JET ROCKET
MAGNETOPLASMA ROCKET
SOLAR SAIL
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