Basic Gasturbine

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    1

    History of Jet Engine Development

    Reaction Principle Jet Propulsion Springer

    Springer

    Jet Propulsion Principle (Newtons Third

    1

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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

    2

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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

    3

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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.

    4

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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

    5

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    6

    .. 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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    2

    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)

    7

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    8

    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

    23

    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

    9

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    (Gas Turbine Engine)Jet Engine Reaction Engine

    500 /

    10

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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 )

    11

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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

    12

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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

    13

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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 ) ,

    14

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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 )

    15

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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

    16

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    17

    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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    18

    Fig ---

    rinciple Of Physics

    3

    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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    20

    ( 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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    22

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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

    , , ,

    24

    24

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    Brayton Cucle ( Constant Pressure Cycle )

    25

    25

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    -- ( Intake ) , (Compression ) , (Combustion ) , (Expansion ) ,( Exhaust ) ( AmbientPressure ) 1 2 ( Brayton Cycle ) 4 5 ( Convergent ExhaustSystem ) ( Thrust )

    26

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    26

    ( 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 ,

    /

    27

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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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    29

    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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    27

    2. ( Altitude ) 14.7 20,000 6.75 30,000 4.36

    . Flight Spectrum 36,000 36,000

    30

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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 )

    31

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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

    32

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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

    35

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    ( Single Entrance Duct )

    1

    ( Divided Entrance Duct ) ( Wing Root ) ( Scoop Type )

    Scoop Scoop Scoop

    36

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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

    37

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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

    38

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    Bellmouth Compressor Inlet

    Bell Mouth Duct Guide Vanes Bell

    Mouth , Bell Mouth BellMouth

    ( Turboprop Compressor Inlet ) Streamline Spinner (Concial )

    39

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    ( Compressor - Inlet Screen ) , ,

    Steel Titanium

    40

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    41

    ( 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.

    42

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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

    43

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    ( Single Entry ) Double Entry ( Impeller ) 2 2

    Single Entry - Two Stage

    15 : 1

    44

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    Stage 10 : 1 15 : 1 2 1.

    2. 1.3 3. ( Impeller ) ( Diffuser ) 4. ( Impeller ) 2 ( Start System )1. ( Impeller )

    45

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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

    46

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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

    47

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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

    48

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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

    49

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    50

    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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    51

    .

    or )

    Reverse - Flow

    nnular Combustor

    3. ( Tapper ) Rotor Disk 4

    ( Split Spool )

    ( Combination Compressor ) ( Axial - Centrifugal Flow Compress A

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    52

    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

    53

    . 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 )

    54

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    Cold Section ( Fuel Nozzle ) Air

    Bleed Port Main Frame

    ( Combustion Section )

    55

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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

    56

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    57

    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

    58

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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

    59

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    3. Can-Annular Cannular Type Outer Casing Inner Liner

    Inter Connector Liner

    60

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    ( Turbine Section )( Heat Energy ) ( Kinetic

    Energy ) ( Mechanical Energy )

    ( Turbine Stator ) , ( Turbine Rotor ) ( Turbine Casing )

    61

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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 )

    62

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    ine Wheel Fir Tree

    ine

    Turbine Blade ( Shround Turbine Blade )

    ( Turbine Shaft ) SplCoupling

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    64

    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 )

    66

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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 )

    67

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    2. Converging -Diverging Design ( SuppersonicGas Velocity ) Convergent - Divergent Exhaust Nozzle

    1 Convergent - Divergent C & D Duct

    Thrust Reverser )

    68

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    (Thrust Reverse ) Drive Brake Wing Spoiller ( Air Borne )

    69

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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