This is an topic which related to aeronautical and aerospace field This topic will help you to go through propulsion in an aircrafts engine and rocket engine #propulsion#aeronautics

1. INTRODUTION OF
AIRCRAFT PROPULSION
BY
- RAHUL

2. CLASSIFICATION OF AIRCRAFT ENGINES
 Turbine – powered
1. Turbo prop
2. Turbo shaft
Reaction engines
1. Jet
a ) Turbo jet
b ) Turbo fan
2 . Pulse jet
3 . Rocket

3. TURBOPROP

4. TURBO PROPELLER
 It has an additional gear box attached in front to drive the propeller.
 This engine uses almost all the exhaust gas to run the propeller and very less thrust
will be produced.
 Means thrust from the exhaust is only 10%
 The other 90% of energy is extracted by turbines that drives the compressor and
second turbine which drives the propeller.
 Modern engines have propeller with smaller diameter but large number of blades.
 20 to 25% of Thrust produced by Nozzle

5.  75 to 80% of thrust produced by propellor
 Operating Mach No: 0.4 to 0.65
 Subsonic Aircraft (0.1 to 0.8 )

6. TURBO JET ENGINE
DEFINITION OF JET ENGINE
• An engine that burns fuel and uses the expanding exhaust gases to turn
a turbine OR produce thrust
WHERE JET ENGINES USED

7. BASIC JET ENGINE

8. PARTS OF TURBO JET
• Housing – The rigid frame that supports and contains the parts needed for operation
as well as the combustion event
• Air inlet and diffuser – The area of the jet where fresh air comes in, the design of the
diffuser straightens and alters the speed of the incoming airs
• Compressor – Compresses the incoming air at a ratio of approximately 30:1
• Burner or combustion chamber – The area of the engine where fuel is ignited
• Exhaust Nozzle – accelerates the engine exhaust to the most efficient and effective
speed for producing thrust
• Turbine – Converts the energy from the heated and expanding exhaust gasses to a
rotating shaft which is used to turn the compressors, or in the case of a turboshaft
engine, power the vehicle

9. COMPRESSOR
• Supplies high pressure air for combustion process
• Centrifugal flow and axial flow
Two type of compressor
1. Axial compressor
2. Centrifugal compressor

10. AXIAL COMPRESSOR
 They may have more than one spool
 Spool is group of compressor stages
 Mean a shaft and one or two turbine stages rotating at the
same speed.
 Low pressure turbine is attached to forward low pressure
compressor.
 Flow will be in axial direction

11. CENTRIFUGAL COMPRESSOR
 Flow will be radial
 Radial flow engines use a centrifugal compressor they
push the air out radially rather than along the axis of the
engine
 Lower efficiency than the axial flow compressor
 It is used in early jet engines.

12. ABOUT TUBOJET
 Chemical energy is converted into mechanical energy
 100% Thrust produced by Nozzle
 Operating Mach No: 1 to 2
 Supersonic Aircraft (1 to 5)

13. TURBOFAN ENGINE
• It has a large fan in the front which sucks the air in, most of the air flows around the
outside core of the engine.
• Fan’s rotational speed is same as low pressure compressor’s rotational speed.
• Only a portion of air from the inlet will be sent to the compressor
• The secondary air leaves separately from primary air and ducted back to mix with
the air from engine core at the back.
• This fan air will account for 80% of total engines thrust.
• Almost all modern commercial aircraft use turbofan engines.

14. • This separation is called bypass
1. cool bypass air flow
2. hot turbine discharge gases

15. ABOUT TURBOFAN
 They are again subdivided into
1. High by pass ratio
2. Low by pass ratio
 It depends on the amount of engine it bypasses the core of engine
 This bypassing will be given as ratio and called as bypass ratio
 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)

16. THANK YOU