engine jt8d boeing 737-200
DESCRIPTION
ENGINE JT8D COURSE, BOEING 737-200, a special thanks to NECTALI MESSALA YOVERA for the diapositives.TRANSCRIPT
JT8D ENGINE
GENERALIDADES
DESCRIPCION Y OPERACIÓN
FUNCIONAMIENTO DEL MOTOR
LOCALIZACION Y DETALLES COMPONENTES.
PRACTICAS DE MANTENIMIENTO
DESCARTE DE FALLAS
DESIGNATION OF THE ENGINE JT8D
J = Motor de Reacción (JET)
T = Turbo ventilador ( turbofan)
8 = Modelo Básico de Ducto
Completo
D = Motor que opera sin
Inyección de agua.
-17 = N° de Modificaciones
HISTORY OF THE JT8D
EL JT8D ES UN MOTOR DE FLUJO AXIAL DE DOBLE
FLUJO TOTALMENTE DUCTEADO. EL PROYECTO DEL
MOTOR TURBOFAN FUE INICIADO EN ABRIL DE 1960.
- FEBRERO 1963 JT8D-1 CERTIFICADO A 14,000 LBS. DE EMPUJE
ENTRANDO EN SERVICIO EN 1964.
- ABRIL 1963 JT8D-5 CERTIFICADO A 12,000 LBS DE EMPUJE.
- MARZO 1966 JT8D-7 CERTIFICADO A 14,000 LBS DE EMPUJE.
- MAYO 1967 JT8D-9 CERTIFICADO A 14,500 LBS DE EMPUJE.
- SETIEMBRE 1968 JT8D-11 CERTIFICADO A 15,000 LBS DE EMPUJE.
- ABRIL 1971 JT8D-15 CERTIFICADO A 15,500 LBS DE EMPUJE.
- FEBRERO 1974 JT8D- 17 CERTIFICADO A 16,000 LBS DE EMPUJE.
- ABRIL 1976 JT8D-17R CERTIFICADO A 16,400 LBS DE EMPUJE
17,400 LBS DE EMPUJE.
GENERAL ZONE DIAGRAM (MM 12-31-1)
GENERAL ZONE DIAGRAM (MM 12-31-1)
ENGINE SAFETY PRECAUTIONS
ENGINE SAFETY PRECAUTIONS
ENGINE SAFETY PRECAUTIONS
LEFT ENGINE COWLING
RIGHT ENGINE COWLING
HUSH KIT MODIFICATION
HUSH KIT MODIFICATION
POWERPLANT ATTACHMENT POINT
POWERPLANT – FORWARD ENGINE MOUNT
POWERPLANT – AFTER ENGINE MOUNT
POWERPLANT - LEFT SIDE VIEW
POWERPLANT - RIGHT SIDE VIEW
POWERPLANT - ENGINE GENERAL
TECHNICAL SPECIFICATIONS
GENERAL STATIONS
MAJOR JT8D DESIGN FEATURES
DIRECTIONAL REFERENCES
VIEWED FROM REAR
ENGINE FLANGES AND STATIONS
BEARING LOCATIONS
PRATT AND WHITNEY JT8D ENGINE
ENGINE RIGHT SIDE
ENGINE LEFT SIDE
ENGINE BUILD GROUPS AND SECTION
ENGINE FRONT VIEW AND ACCESSORY DRIVE CASE
ENGINE FAN INLET GROUP
ENGINE FAN INLET MASTER VANE
FRONT COMPRESSOR GROUP
COMPRESSOR INTERMEDIATE GROUP
HIGH PRESSURE COMPRESSOR
ROTORS QTY
R7 60
R8 58
R9 60
R10 64
R11 70
R12 80
R13 74
DIFFUSER GROUP
FUEL INLET TUBES AND MANIFOLD
REDUCED EMISSION TYPE FUEL NOZZLE
AND SUPPORT
COMBUSTION CHAMBERS
DIFFUSER OUTER FAN DUCT GROUP
FAN DISCHARGE SECTION
REAR COMPRESSOR DRIVE TURBINE GROUP
46 95 79 77
LOW PRESSURE TURBINE
TURBINE SHAFT
BEARING 4 1/2
BLADES
EXHAUST CASE GROUP
TURBINE SHAFT
BEARING 4 1/2
PILOTS FWD OVERHEAD PANEL – P5
FORWARD PANEL P-5
FORWARD PANEL P-5
FORWARD PANEL P-5
APU CONTROLS AND INDICATION
ENGINE CONTROLS PANEL P-2
FLIGHT DECK ENGINE CONTROLS
PANEL DETRÁS DEL ASIENTO DEL PRIMER OFICIAL – P6
PANEL DETRÁS DEL ASIENTO DEL CAPITAN – P18
INDICACION DE LUCES EN PANEL P5
STATION HEIGHT
A AIRCONDITIONING 528 3’ 4”
B APU OIL TANK 1121 12”
C EXT. POWER – AC 232 5’ 4”
D ENGINE 1 OIL TANK 616 3’ 5”
E ENGINE 2 OIL TANK 616 3’ 1”
F HYDRAULIC RESERVOIR 664 4’ 5”
G OVERWING FUELING 755 9’ 4”
H OXYGEN 390 6’ 3”
J PNEUMATIC CONNECTION 540 3’ 8”
K POTABLE WATER 390 6’ 4”
L PRESSURE FUELING 679 8’
M TOILET PANEL , AFT. 996 7’
N TOILET PANEL, FWD 270 5’ 10”
O ACM OIL FILL 575 4’ 2”
P EXT. POWER – DC 380 4’ 3”
R CSD OIL FILL 625 3’ 3”
S STARTER 630 3’ 3”
T THRUST REVERSER ISOLATION 540 4’ 2”
SERVICING POINTS
ENGINE OIL SYSTEM
ATA - 79
ENGINE CONTROLS PANEL P-2
ENGINE CONTROLS PANEL P-2
OIL SYSTEM LIMITS
Normal Oil Pressure : 40 to 55 psi.
Temperature :
120º C, JT8D-1, -7, -9 ( Continuous)
157º C, JT8D-1, -7, -9 ( Transient)
130º C, JT8D-11, -15, -17 ( Continuous)
165º C, JT8D-11, -15, -17 ( Transient)
Breather:
8.0 inch Hg, maximum, JT8D-1, -7, -9
8.5 inch Hg, maximum, JT8D-11, -15, -17
Consumption (per hour)
½ pint to 1 quart normal (0.5 to 1 liter)
2 quarts – recommend that cause be investigated
ENGINE OIL SYSTEM EXTERNAL COMPONENTS
ENGINE OIL SYSTEM COMPONENTS
OIL TANK
EXPANSION SPACE: 1.3 US gallosx
“HOT” TANK
TANK DRAIN VALVE
ENGINE OIL QUANTITY TEST
MAIN OIL PUMP
MAIN OIL STRAINER INSTALLATION
DE PAPEL
c/20 Hrs.
DE METAL
c/150-200 Hrs.
CLEANABLE
PRESS DROP: 5 PSI
CLEANABLE
PRESS DROP: 7-9 PSI
DISPOSABLE
PRESS DROP: 3-4 PSI
ENGINE OIL SYSTEM
LOW OIL PRESSURE WARNING SYSTEM
LOW OIL PRESSURE WARNING SYSTEM
OIL FILTER BYPASS WARNING SYSTEM
BEARING LOCATIONS
TYPICAL CARBON AND LABYRINTH SEALS
TYPICAL LABYRINTH SEALS
TYPICAL CARBON SEALS
TYPICAL ANTIFRICTION BEARINGS
MAIN BEARING
ROLLER BEARINGS – Support rotating
Parts radially, they absorb angular loads ;
They do not prevent axial movement.
BALL BEARINGS – Hold rotating parts in
axial and radial alignment. They absorb
both thrust (axial) and angular loads
ENGINE LUBRICATION SYSTEM
LUBRICATION SYSTEM INDICATORS
ENGINE OIL PRESSURE ADJUSTMENT ( MM 71-09-100 )
GEARBOX ROTARY BRETHER IMPELLER
ENGINE
FUEL SYSTEM
ATA - 73
PROPORCIONA LA CANTIDAD DE COMBUSTIBLE ADECUADO
PARA LA RELACIÓN DE COMBUSTIÓN COMPLETA PARA TODOS
LOS REQUERIMIENTOS DE OPERACIÓN DEL MOTOR.
LOS COMPONENTES SON:
BOMBA DE COMBUSTIBLE.
CALENTADOR DE COMBUSTIBLE.
UNIDAD DE CONTROL DE COMBUSTIBLE.
TRANSMISOR DE FLUJO.
ENFRIADOR ACEITE-COMBUSTIBLE.
VALVULA DE PRESURIZACIÓN Y DESCARGA.
DISTRIBUIDORES E INYECTORES.
FUEL SYSTEM
FUEL SYSTEM COMPONENTS - LEFT SIDE
FUEL SYSTEM COMPONENTS - RIGHT SIDE
FUEL SYSTEM OVERVIEW
ENGINE FUEL SYSTEM
ENGINE FUEL SYSTEM DIAGRAM
FUEL SYSTEM
FUEL CONTROL UNIT
Ñ
JT8D - SIMPLIFIED FUEL CONTROL
JT8D – FUEL PUMP
FUEL HEAT SYSTEM
ENGINE FUEL OVERHEAD PANEL P5-2
ENGINE FUEL DEICING SYSTEM SCHEMATIC
PRESSURIZING AND DUMP VALVE
PRESSURIZING AND DUMP VALVE
TYPICAL FUEL NOZZLES AND SUPPORTS
FUEL NOZZLES AND SUPPORTS
ENGINE INDICATING
ATA - 77
ENGINE PRESSURE RATIO CIRCUIT (EPR)
ENGINE PRESSURE RATIO CIRCUIT (EPR)
ENGINE PRESSURE RATIO CIRCUIT (EPR)
ENGINE RPM INDICATING SYSTEMS
EXHAUST GAS TEMPERATURE CIRCUIT
EXHAUST GAS TEMPERATURE INDICATOR
FUEL FLOW INDICATING SYSTEM
VIBRATION INDICATING SYSTEM
40 CPS
ENGINE CONTROLS
ATA - 76
ENGINE CONTROL SYSTEM
FLIGHT DECK ENGINE CONTROLS
ENGINE MOUNTED CONTROLS
STARTING
ATA - 80
ENGINE STARTING SYSTEM
ENGINE STARTING SYSTEM
ENGINE START VALVE / STARTER
PNEUMATIC START
PNEUMATIC START
PNEUMATIC STARTER
ENGINE START CIRCUIT
ENGINE START CIRCUIT
IGNITION
ATA - 74
IGNITION SYSTEM COMPONENTS
IGNITION SYSTEM COMPONENTS
POWER PLANT
AIR
ATA - 75
ABBREVIATIONS
P = Pressure psi, Kg/cm2
Ps = Static Pressure
Pd = Dynamic Pressure
Pt = Total Pressure = ( Ps+Pd )
Pam = Ambient Pressure
Po. = International Standard Day pressure at sea
level 29,92” HgA, 14.7 psia, 760mm HgA,
1013.2 Millibars HgA.
To. = International Standard Day Temperature at
sea level 59 degrees F, 15 degrees C.
EPR = Engine Pressure Ratio
= Turbine Discharge Total Pressure
Compresssor Inlet Total Pressure
TYPICAL ANTI-ICING CONTROL AND INDICATION
ENGINE AND NOSE COWL ANTI-ICING
ANTISURGE BLEED SYSTEM CONFIGURATIONS
START BLEED / ANTISURGE SYSTEM
ANTISURGE BLEED SYSTEM
PRESSURE RATIO BLEED CONTROL
BLEED SYSTEM SCHEMATIC - CLOSED
BLEED SYSTEM SCHEMATIC - OPEN
BLEED CONTROL START VALVE
ANTISURGE BLEED SYSTEM COMPONENTS
EXHAUST
ATA - 78
THRUST REVERSER CONTROL SYSTEM
THRUST REVERSER ELECTRICAL / HYDRAULIC SCHEMATIC
REVERSER UNLOCKED LIGHT
REVERSER UNLOCKED LIGHT OFF
THRUST REVERSER ISOLATION VALVE / PRESSURE SWITCH
QUIZ