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History of Jet Engine Development
Reaction Principle Jet Propulsion Springer
Springer
Jet Propulsion Principle (Newtons Third
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Jet Propulsion100 200
Alexandria
(Jet Reaction) Heros AeolipileReactionPrinciple
Heros Aeolipile
.. 1200 ReactionPrinciple (Rocket) (Black Powder) (Saltpeter) (Sulfur)(Charcoal) .. 1230 (Solid Fuel) Chinese Rocket
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Brancas Turbine
.. 1629 Giovanni Branca
BritishMuseum Turbo Supercharger
Newtons Horseless Carriage
.. 1687 (Sir Isaac Newton) Jet Propulsion
Newton Steam Carriage
.. 1900 Dr . Sanford A Moss
Gas Turbine Cornell Steam Turbine BucketWheel .. 1918 General Electric Dr. Moss Turbo Supercharger 1Turbo Supercharger Turbosupercharger
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12 .. 1937 Frank Whittle Moss
Impeller Type Compressor Multi Can Single Stage Turbine Wheel
A. Diagram of Whittles reverse-flow combustion chamber.
B. The first British et aircraft to fl the Gloster E28/39 ex erimental air lane.
Whittle W-1 Turbojet engine Whittle W2/700 Turbine engine
Gloster master The Graman Heinkle He-178, flown on August 27,
Was the first jet aircraft flight.
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.. 1941 Whittle W-1 GlosterModel E28/39 1,000 400
.. 1943 W2 W-1 . Meteor 2 Meteor V1 Pulse Jet 2
Frank Whittle Hans VonOhain Heinkel Company 1,100 Heinkel He-178 27 ..1939
..1941General Electric Company Turbine Turbo SuperchargerGeneral Electric Ge - 1a Engine
Centrifugal Flow 1,650 16,500RPM. Bell Xp - 59 ..1942
The General Electric 1-16
(J-31-Ge-1 military designation)
.. 1948 Turbo Prop Vickers Viscount
.. 1949 Dehavilland
Comet Turbo Jet4 .. 1952 .. 1954
A. Vickers Viscount B. DeHavilland
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.. 1958 Boeing Company Boeing 707 Turbo Jet
Boeing 747Boeing Company Boeing 2707 (Supersonic) 2.8
300
Ge-4
General Electric
68000 4 60000
A. An early Boeing 707 B. Boeing 747
The American SST Design. Boeing 2707-300
.. 1976 Concorde
Olympus Rolls- Royce 2.2 100
The British French Concorde SST.
Business Jet Pratt & Whitney, General Electric, Rolls Royce, Garrett, General Motor-
Allison Lycoming Business Jet
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Types of Jet Engine
(Jet Engine) (Gas Turbine Engine) Turbine Engine Jet Engine
(Nozzle) ( Rocket ) , (Ram Jet), (Pulse Jet)( Gas Turbine Engine ) , ( Turbo/Ram Jet Engine )( Turbo - Rocket Engine )
(Gas Turbine Engine)
(Turbo Jet Engine) ,
(Turbo Fan Engine) ,
(Turbo Prop Engine) (Turbo Shaft Engine)
( Rocket )
Non-Air Breathing Engine (Liquid) (Solid) (Nozzle)
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1.
Solid fuel rocket
( Solid Fuel ) (Oxidizer)
Jato ( Jet Assis- Tance Take Off ) Rato (Rocket Assistance Take Off )
2.
Solid fuel rocket
2-3 V-2
(Alcohol) 52000 Space Shuttle
(Liquid Hydrogen)400000 3
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German V-2 rocket
Space shuttle and
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( Ram Jet )
Diagram of Ramjet Engine
Cutaway view of Ramjet Engine
Athodyd (Aero Thermo Dynamic Duct)
300
Ram JetHypersonic (4 Mach)
( Pulse Jet )
-( Shutter Type Valves ) ( Igniter ) ( Tail Pipe )
Pulse Jet
Pulse Jet
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(Gas Turbine Engine)Jet Engine Reaction Engine
500 /
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1. ThrustProducing Engine (Turbo Jet) (Turbo Fan)2. Torque Producing Engine
(Turbo Prop) (Turbo Shaft)
( Turbo Jet Tngine )Frank Whittle
Impeller , Annular Combustor , ( Single Stage Turbine ) ( Compressor ) , ( Combustor ) (Turbine )
( Igniter ) ( Tail Pipe )
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( Turbofan Engine ) Fan
Multibladed Ducted Propeller 2 ( N1 ) ( Free Turbine )
( N2 ) Fan
Turbo Fan Blade Exhaust Nozzle Convergent Duct Fan Front Fan Fan Aft. Fan
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3 Bypass Ratio Fan CoreEngine
1. Low Bypass Turbofan Engine Bypass Fan Fan Fan ( Fan Discharge ) Fan Short Fan Duct Long Fan Duct Converging Discharge Nozzle
Bypass Fan ( Fully Duct Fan Engine) ( Bypass Ratio ) 1 : 12. Medium Or Intermediate Bypass Turbofan Engine BypassFan Bypass 2 : 1 3 : 1Fan Fan Low Bypass EngineFig 2-17
3. High Bypass Turbo Fan Engine Bypass Fan Bypass Ratio 4 : 1 Fan High Bypass Turbo FanJt9d Bypass Ratio 5 : 1 80% 20 % Core Engine
Jt3d
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Fig2-17
4. Ultra High Bypass Turbo Fan Engine Fan Bypass Ratio Ultra High Bypass TurboFan Engine Fig 2-18
( Turbo Shaft Engine )
( Turbo Shaft Engine ) ,
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Turbine 2 Free Turbine Power Out Put Free Power Turbine Type Turbo Shaft Engine
Fig 2-13
Turbine Free Turbine Gas Generator Turbine Free Turbine ( Power Turbine ) Gas Generator Turbine FreeTurbine ( Power Turbine ) 1 3
( Turbo Prop Engine )
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( Reduction Gear System ) Turbine Turbine
Compressor Free Turbine Free Turbine Power Turbine Free Turbine
Compressor Turbine
5 - 25 %
/ ( Turbo / Ram Jet Engine )/ 3
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ig---
After Burner
/ / Variable Intake Variable Nozzle Intake Guide Vane - AfterBurner 3 Intake Guide Vane
F
- ( Turbo - Rocket Engine )- / - - Multi StageTurbine
Turbine
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Fig ---
rinciple Of Physics
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P
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( Force ) ( Vector ) ( Newton ) 1 2 1
= - / 2
F = P A
F = P = /
A =
( Work )
W = FD
W = - F = D =
( Power ) 1 =
P = FD
T
P = -/ -/ F = D = T =
( Horse Power ) 33,000 -1 550 -1
( Velocity )
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( Acceleration ) 1
A = V2 - V1
T
A = / 2
V1 = / V2 = / T =
( Energy ) ( Kinetic Energy = Ek ) ( Potential Energy = Ep )
Newton ( Newton S Law Of Motion )
1
2 F = M A
F = M = A = / 2
3 Action = Reaction
( Mass And Weight )
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- ( Mass ) - ( Weight )
( Bernoulli S Principle ) ( Venturi ) ( ) ( )
(Divergent ) ( Kinetic Energy ) (Potential Energy )( Kinetic Energy ) (Static Pressor )
Static Pressure Ram Pressure B Ram Pressure C RamPressure
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Diffuser
( Diffuser And Diffusion )
(Subsonic) (Supersonic)
(Subsonic Diffuser)
( Divergent Duct )
(Supersonic Diffuser) ( Convergent Duct )
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( Sonic Chocking ) (Convergent Duct) ( Mach 1 ) (Shock Wave)
Choke Nozzle
(Exhaust Nozzle)
2 Otto Cycle
, , ,
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Brayton Cucle ( Constant Pressure Cycle )
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-- ( Intake ) , (Compression ) , (Combustion ) , (Expansion ) ,( Exhaust ) ( AmbientPressure ) 1 2 ( Brayton Cycle ) 4 5 ( Convergent ExhaustSystem ) ( Thrust )
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( Thrust Calculations )
2 (Gross Thrust) (Net Thrust)
( Gross Thrust ) (Test Cell ) Gt = W ( Vj - Vp )
G
Gt = Gross Thrust , W = Mass Airflow , / Vp = Air Intake Velocity , / Vj = Air Exhaust Velocity ,
/
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G = Constant For Acceiertion Due To Gravity , / 2
Gt = W - Vj
G
( Net Thrust ) Nt = W ( Vj - Vp )
G
Nt = Net Thrust , W = Mass Airflow , / Vp = Air Intake Velocity , / Vj = Air Exhaust Velocity ,
/ G = Constant For Acceiertion Due To Gravity ,
/ 2
( Fan Engine Thrust ) Gt = Gt ( Engine ) + Gt (Fan )
Gt = W ( Vj - Vp ) + W ( Vj - Vp )
G G
Gt = W X Vj + W X Vj
G G
( Thrust Horse Power ) Thp = Nt X Aircraft Speed ( Miles For Hour )
375 Mile - Pound Per Hour
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375 - / 1 33,000 - 1
1,980,000 - 1 5,280 1 375 - / 375 / 1 1
Equivalent Shaft Horse Power Equivalent ShaftHorse Power Eshp.
( Static Condition ) 2.6 Dynamoneter Equivalent Shaft Horse PowerEshp. = Shp + Gt
2.6
True Air Speed ( Net Thrust ) Net Thrust Net Thrust True Air Speed 300 / Vc. ( Velocity Change ) Increase Ram
Ram Jet 610 / ( Net Thrust ) ( Gross Thrust )Exhaust Jet Velocity Vp = Vj State Of Unity .
( Drag ) JetEfficiency Thrust Horse Poweer
( Factor Effecting Engine Thrust )1. ( Temperature )
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2. ( Altitude ) 14.7 20,000 6.75 30,000 4.36
. Flight Spectrum 36,000 36,000
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14.7 / 20,000 6.75 / 30,000 4.36 /
32,000 -69.7 ( -56.5 ) ( Air Speed ) ( Vj - Vp ) ( Vp )
( Ram Effect )
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Ehhaust Gas ( FuelConsumption ) Fuel Control Unit
1. 2. Compressor Turbine 3. Mass Air Flow ( ) Drag
4. ( Expansion Rate Of Exhaust Gas ) Turbine ( Engine Rating )1. Maximum Rated Thrust 5 Power Control Lever Max 100% Max Thruus Military Thrust 15 ( Permissable Duration In Flight )2. Militay Rate Thrust Power Control Lever
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3. Normal Rate Thrust
Power Control Lever Normal 80 - 90 % Max Rate Thrust 4. Idle Rate Thrust Power Control Lever Idle ( ) 45 - 50 % MaxRate Thrust ( Much Number )
( Sonic Velocity ) 1 ( Thrust Specific Fuel Consumption ) TsfcTsfc = Wf
Fu
Tsfc = Thrust Specific Fuel Consumption
Wf = Fuel Flow Lbs / HrFu = Net Thrust Lbs
, , ( Compressor Section ) , ( Combustion Section ) , ( Turbine Section )
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1. ( Air Inlet Duct )
2. ( Compressor Section )3. ( Combustion Section )4. ( Turbine Section )5. (Exhaust Section )6. ( Accessory Section )7. , , ,
( Airinlet Duct )( CompressorRatio ) ( Distortion Free ) Compressor Stall
3 1. ( The Compressor Speed - R.P.M. )2. ( The Foward Speed Of Air Craft )3. ( The Density Of Ambient Air )
6 - 10 Air Scoop 1. Ram Recovery Total Pressure Recovery
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2. -
( ) , , 2 - ( Single Entrance Duct )- ( Divide Entrance Duct )
Compressor Stall
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( Single Entrance Duct )
1
( Divided Entrance Duct ) ( Wing Root ) ( Scoop Type )
Scoop Scoop Scoop
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( 1 Mach = 760 Mph. )
( Diffuser ) ( Divergent Duct )
(Convergent & Divergent Duct C & D Duct ) Convergent Duct ( 1 Mach ) ( Divergent Duct ) Mach Number
2 1. ( Variable - Geometry Inlet Duct ) ( Movable Strike ) Ramp Wedge ( Convergent And Divergent ) By - Pass
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2. ( Shock Wave ) , , ( Shock Wave ) ( Restriction ) ( Small Obstruction )
Shock Method Variable Geometry Method Chock Wave Buzz Shock Wave Buzz Shock Wave
Buzz
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Bellmouth Compressor Inlet
Bell Mouth Duct Guide Vanes Bell
Mouth , Bell Mouth BellMouth
( Turboprop Compressor Inlet ) Streamline Spinner (Concial )
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( Compressor - Inlet Screen ) , ,
Steel Titanium
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( Compressor Section )
Supercharger
( Centrifugal FlowCompressor ) Stage
1. , ( Cabin Pressurization } Heating AndCooling )
2. ( Deicing And Anti-Icing Equipment )3. ( Pneumatic Starting Of Engine )4. ( Auxiliary Drive Unit , A.D.U. )5. Survo ( Control Booster Servo )6. ( Power For Running Instruments )( Location ) -
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- ( Compressor Type ) 2 1. ( Centrifugal Flow Compressor )
2. ( Axial Flow Compressor )( Centrifugal Flow Compressor )1. ( Impeller ) ( Aluminum Alloy ) , ( Heat - Treated) , ( Smooted )
2. ( Diffuser ) (Convergent Duct ) Diffuser Impeller ( Compressor Manifold )
( Compressor Manifold ) Diffuser 3.
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1. ( Single Entry Or Single Face )2. ( Double Entry Or Double Face ) ( Plenumchamber ) ( Inlet Duct ) Ram ( Impeller) Double Entry Apu. Jet Start
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( Single Entry ) Double Entry ( Impeller ) 2 2
Single Entry - Two Stage
15 : 1
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Stage 10 : 1 15 : 1 2 1.
2. 1.3 3. ( Impeller ) ( Diffuser ) 4. ( Impeller ) 2 ( Start System )1. ( Impeller )
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2. 2 Stage
( Axial Flow Compressor )25 : 1 1Stage Stage ( Rotor Blade ) (Stator Vane )(Stator Vane)Divergent ( Rotor Blade ) Convergent Stage 1.25 : 1 Stage Stage
(TaperDesign) Stage 25% ,
1. (Stator Vanes ) Rotor Blade ( Stator Vane ) ( Divergent Duct ) Stator Vane Steel Split Ring , Shround Segment ( Compressor Case ) 10 - 16 Stages
Stator Vane
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- Stage Stage -
Stator Vane Inlet Guide Vanes ( Fixed ) (Variable ) Inlet Guide Vanes Rotor Stage 1 Stator Vane Exit Guide Vanes Straigh - Tening Vanes
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2. (Rotor Blades ) Air Foil RotorDisk ( Rotor Blade ) ( Convergent Duct ) Stainless Steel Rotor Disk Bulb-Type Fir-Tree Type Root
Screws , Peening , Locking Wire , Pins Or KeysMid Span Shround Or Mid Span Damper ( Compressor Blade Tips ) Blade Profile Rotor Blade Compressor Case Rotor Blade Bearing
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2 1. Solid Spool Compressor 6 - 16 Stage Variable Inlet Guide Vanes Stator Vanes 2-3 ( Variable Stator Vanes ) Compressor Stall2. Split Spool Compressor Compressor 2 - 3 ( Two Spool ,Dual Spool , Twin Spool Triple Spool ) Compressor Turbine Turbine 2 Two Spool ,Dual Spool Twin Spool 2 ( Low Pessor Compressor ) N 1 Turbine ( Low PressorTurbine ) Free Turbine Turbine Turbine ( High Pressor Compressor ) N
2 Turbine
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Speed Bias
N2( Intermediate Pressor ) N
3 ( High Pressos )
Drag Turbine
1. ( High Peak Efficiencies ) Stage
urbo Fan Turbo Jet
2. Ram Effect 3. T
Turbo Prop Stage 4.
1. ( Bleed Air )
2. Stator Vane Rotor Blade Air Foil
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.
or )
Reverse - Flow
nnular Combustor
3. ( Tapper ) Rotor Disk 4
( Split Spool )
( Combination Compressor ) ( Axial - Centrifugal Flow Compress A
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ompre
, , Exhaust Or Inlet
C ssor Stall
Stage Stage Stage
(Blade Stall) Compressor Stall
Rumble , Chuggjne , Choo-Chooing Or Buzzing Egt
Compressor Stall1.
4.
Stall
2.
3. 5. Compressor Stall
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Compressor Stall Surge
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. Compressor Stall ( Angle Of Attack And Compressor Stall )
Compressor Stall Compressor Stall Stall Stall Stall Hung Stall
Egt . Stall Surge Compressor Stall
Surge The Design Point
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Steady - State Operating Line Compressor Stall Steady -
State Line Stall Zone Stall Margin Compressor Stall
( Diffuser Section )
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Cold Section ( Fuel Nozzle ) Air
Bleed Port Main Frame
( Combustion Section )
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( Combustion Section ) 25 % PrimaryAir 15 : 1 75 % Secondary Air
Through Flow Reverse Flow
Annular
Secondary Air
75%
Primary Air
25%
Secondary Air
75%
Dilution Section Transition SectionDome Section
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1. 15 : 12.
3. 1. ( Combustion Casing ) Stanless Steel ( Port ) ( Fuel
Nozzle ) , ( Igniter Plug )2. ( Inner Liner ) Stanless Stell Titanium 3 2.1 ( Dome Section ) ( FuelNozzle Furrule ) Swirl Cup Swirl Vanes ( IgniterPlug )
Primary Air 25 % 15 : 12.2 ( Dilution Section ) ( Louver Holes ) Seciondary Air 75 % 2.3 ( Transition Section ) 3. ( Ignition System ) Exiter Unit Igniter Plug
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4. ( Fuel Injection System ) ( Fuel Control Unit )
5. ( Fuel Drainage System ) Hot Start
3 1. Can Type Centrifugal Flow Axial Flow Can Type ( Outer Casing Housing ) (Combustion Chamber Liner Inner Liner )Can Type 8 -14 Multiple Can Inter Connector Frame Propagation Tube Can
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2. Annular Type ( Inner Liner ) , Outer Casing
Inner Casing Basket Type Annular Through Flow Annular Reverse Air Flow
Turbo Prop TurboShaft
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3. Can-Annular Cannular Type Outer Casing Inner Liner
Inter Connector Liner
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( Turbine Section )( Heat Energy ) ( Kinetic
Energy ) ( Mechanical Energy )
( Turbine Stator ) , ( Turbine Rotor ) ( Turbine Casing )
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Turbine Stator Stator Vanes Turbine Stator Turbine Rotor
Turbine Rotor Turbine Stator
Turbine Stator Stg.1 , Turbine Nozzle
Turbine Rotor
hround Nozzle
e Outer Shround Segment Stress Wappingf The Vane
Vane , Turbine Guide Vane Nozzle DiaphragmTurbine Nozzle Turbine Nozzle Inner Shround Outer S
Vane Vane Turbine Vane Shround 2 Loose Fitting Vane Shround Vane Weilding Van
O
Turbine Rotor ( Turbine Shaft ) ( Turbine Wheel )
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ine Wheel Fir Tree
ine
Turbine Blade ( Shround Turbine Blade )
( Turbine Shaft ) SplCoupling
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Turbine Rotor Convergent Duct urbofan Turbojet
Turbine Rotor
2
1. Reaction Turbine Turbine Nozzle TurbineRotor Turbine Nozzle Vane T
2. Impulse Turbine turbine Nozzle Convergent Nozzle Turbine Rotor Turboprop Turboshaft
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Combination ( Reaction - Imlulse Turbine )Turbine Royor Reaction Impulse
urbine Casing
T Turbine Rotor Turbine Stator Bearing
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( Exhaust Section ) ( Thrust )
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1. Exhause Cone Outer Cone ( Outer Shell ) Inner Cone Strust Fin 3 - 4 Strust Fin Fairing Straightening Vane Exhaust Cone Solid Jet Outer Cone Inner Cone Divergent Duct OuterCone Stainless Steel Thermocouple ( Exhaust Gas Teperature )2. Tail Pipe Exhaust Duct Tail Pipe ExhaustGas
Blanket Heat Shround Stainless SteelFiber Glass 3. Exhaust Nozzle Tail Pipe 2
1. Converging Design (Sub- Sonic GasVelocity )
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2. Converging -Diverging Design ( SuppersonicGas Velocity ) Convergent - Divergent Exhaust Nozzle
1 Convergent - Divergent C & D Duct
Thrust Reverser )
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(Thrust Reverse ) Drive Brake Wing Spoiller ( Air Borne )
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2 Mechanical - BlockageType Aerodynamic Blockage Type1. Mechanical - Blockage Type
Camshell Actuators 2. Aerodynamic Blockage Type Exhaust Duct Mechanical Blockage And Aerodynamic Blockage Type Reverser Fan Reverse Clamshell Reversr Casade Vane
Camshell 60