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标题: CFM56-5B TRAINING MANUAL BASIC ENGINE [打印本页]

作者: 帅哥 时间: 2009-2-12 13:34:26 标题: CFM56-5B TRAINING MANUAL BASIC ENGINE

This CFMI publication is for Training Purposes Only. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. For authorized maintenance practices and specifications, consult pertinent maintenance publications. The information (including technical data) contained in this document is the property of CFM International (GE and SNECMA). It is disclosed in confidence, and the technical data therein is exported under a U.S. Government license. Therefore, None of the information may be disclosed to other than the recipient. In addition, the technical data therein and the direct product of those data, may not be diverted, transferred, re-exported or disclosed in any manner not provided for by the license without prior written approval of both the U.S. Government and CFM International.

作者: 帅哥 时间: 2009-2-12 13:36:18

Chapter Section Page Table of Contents 1 to 2 Lexis 1 to 8 Intro 1 to 8 72-00-00 Engine General 1 to 10 72-20-00 Fan Section 1 to 24 72-00-02 Core Engine Major Module 1 to 4 72-30-00 High Pressure Compressor Section 1 to 6 72-40-00 Combustion Section 1 to 6 72-50-00 Turbine Section 1 to 12 72-60-00 Accessory Drive Section 1 to 12

作者: 帅哥 时间: 2009-2-12 13:37:21

ABBREVIATIONS & ACRONYMS A A/C AIRCRAFT AC ALTERNATING CURRENT ACARS AIRCRAFT COMMUNICATION ADDRESSING & REPORTING SYSTEM ACMS AIRCRAFT CONDITION MONITORING SYSTEM ACS AIRCRAFT CONTROL SYSTEM ADC AIR DATA COMPUTER ADEPT AIRLINE DATA ENGINE PERFORMANCE TREND ADIRU AIR DATA AND INERTIAL REFERENCE UNIT AGB ACCESSORY GEARBOX AIDS AIRCRAFT INTEGRATED DATA SYSTEM ALF AFT LOOKING FORWARD ALT ALTITUDE AMB AMBIENT AMM AIRCRAFT MAINTENANCE MANUAL AOG AIRCRAFT ON GROUND APU AUXILIARY POWER UNIT ARINC AERONAUTICAL RADIO, INC. (SPECIFICATION) ATA AIR TRANSPORT ASSOCIATION ATHR AUTO THRUST ATO ABORTED TAKE-OFF B BITE BUILT-IN TEST EQUIPMENT BMC BLEED MONITORING COMPUTER

作者: 帅哥 时间: 2009-2-12 13:38:08

BSI BORESCOPE INSPECTION BSV BURNER STAGING VALVE BVCS BLEED VALVE CONTROL SOLENOID C CBP (HP) COMPRESSOR BLEED PRESSURE CCDL CROSS CHANNEL DATA LINK CCFG COMPACT CONSTANT FREQUENCY GENERATOR CCU COMPUTER CONTROL UNIT CCW COUNTER CLOCKWISE CDP (HP) COMPRESSOR DISCHARGE PRESSURE CFDIU CENTRALIZED FAULT DISPLAY INTERFACE UNIT CFDS CENTRALIZED FAULT DISPLAY SYSTEM CFMI JOINT GE/SNECMA COMPANY (CFM INTERNATIONAL) Ch A channel A Ch B channel B CMC CENTRALIZED MAINTENANCE COMPUTER CMM COMPONENT MAINTENANCE MANUAL CG CENTER OF GRAVITY cm.g CENTIMETER x GRAMS CHATV CHANNEL ACTIVE CFDIU CENTRALIZED FAULT DISPLAY INTERFACE UNIT CFDS CENTRALIZED FAULT & DISPLAY SYSTEM CIP(HP) COMPRESSOR INLET PRESSURE

作者: 帅哥 时间: 2009-2-12 13:38:51

CIT(HP) COMPRESSOR INLET TEMPERATURE CODEP HIGH TEMPERATURE COATING CPU CENTRAL PROCESSING UNIT CRT CATHODE RAY TUBE CSD CONSTANT SPEED DRIVE CSI CYCLES SINCE INSTALLATION CSN CYCLES SINCE NEW Cu.Ni.In COPPER.NICKEL.INDIUM CW CLOCKWISE D DAC DOUBLE ANNULAR COMBUSTOR DC DIRECT CURRENT DCU DATA CONVERSION UNIT DISC DISCRETE DIU DIGITAL INTERFACE UNIT DMC DISPLAY MONITORING COMPUTER DMU DATA MANAGEMENT UNIT DPU DIGITAL PROCESSING MODULE DRT DE-RATED TAKE-OFF E EBU ENGINE BUILDUP UNIT ECAM ELECTRONIC CENTRALIZED AIRCRAFT MONITORING ECS ENVIRONMENTAL CONTROL SYSTEM ECU ELECTRONIC CONTROL UNIT

作者: 帅哥 时间: 2009-2-12 13:39:21

EFH ENGINE FLIGHT HOURS EFIS ELECTRONIC FLIGHT INSTRUMENT SYSTEM EGT EXHAUST GAS TEMPERATURE EICAS ENGINE INDICATING AND CREW ALERTING SYSTEM EIS ELECTRONIC INSTRUMENT SYSTEM EIU ENGINE INTERFACE UNIT EMF ELECTROMOTIVE FORCE EMI ELECTRO MAGNETIC INTERFERENCE EMU ENGINE MAINTENANCE UNIT EPROM ERASABLE PROGRAMMABLE READ-ONLY MEMORY ESN ENGINE SERIAL NUMBER EVMU ENGINE VIBRATION MONITORING UNIT EWD ENGINE WARNING DISPLAY F FAA FEDERAL AVIATION AGENCY FADEC FULL AUTHORITY DIGITAL ENGINE CONTROL FAR FUEL/AIR RATIO FDRS FLIGHT DATA RECORDING SYSTEM FEIM FIELD ENGINEERING INVESTIGATION MEMO FFCCV FAN FRAME/COMPRESSOR CASE VERTICAL (VIBRATION SENSOR)

作者: 帅哥 时间: 2009-2-12 13:39:52

FI FLIGHT IDLE (F/I) FLA FORWARD LOOKING AFT FLX TO FLEXIBLE TAKE-OFF FMGC FLIGHT MANAGEMENT AND GUIDANCE COMPUTER FMS FLIGHT MANAGEMENT SYSTEM FMV FUEL METERING VALVE FOD FOREIGN OBJECT DAMAGE FPA FRONT PANEL ASSEMBLY FPI FLUORESCENT PENETRANT INSPECTION FRV FUEL RETURN VALVE FWC FLIGHT WARNING COMPUTER FWD FORWARD G GE GENERAL ELECTRIC GEM GROUND-BASED ENGINE MONITORING GI GROUND IDLE (G/I) g.in GRAM x INCHES GMT GREENWICH MEAN TIME GSE GROUND SUPPORT EQUIPMENT H HCF HIGH CYCLE FATIGUE HCU HYDRAULIC CONTROL UNIT HDS HORIZONTAL DRIVE SHAFT HMU HYDROMECHANICAL UNIT HP HIGH PRESSURE HPC HIGH PRESSURE COMPRESSOR HPCR HIGH PRESSURE COMPRESSOR ROTOR

作者: 帅哥 时间: 2009-2-12 13:40:33

HPSOV HIGH PRESSURE SHUTOFF VALVE HPT HIGH PRESSURE TURBINE HPTC HIGH PRESSURE TURBINE CLEARANCE HPTCC HIGH PRESSURE TURBINE CLEARANCE CONTROL HPTCCV HIGH PRESSURE TURBINE CLEARANCE CONTROL VALVE HPTR HIGH PRESSURE TURBINE ROTOR Hz HERTZ (CYCLES PER SECOND) I IDG INTEGRATED DRIVE GENERATOR ID PLUG IDENTIFICATION PLUG IFSD IN FLIGHT SHUT DOWN IGB INLET GEARBOX IGN IGNITION IGV INLET GUIDE VANE in. INCH I/O INPUT/OUTPUT IOM INPUT OUTPUT MODULE IR INFRA RED K K X 1000 L lbs. POUNDS, WEIGHT LCF LOW CYCLE FATIGUE LE (L/E) LEADING EDGE L/H LEFT HAND

作者: 帅哥 时间: 2009-2-12 13:42:55

LP LOW PRESSURE LPC LOW PRESSURE COMPRESSOR LPT LOW PRESSURE TURBINE LPTC LOW PRESSURE TURBINE CLEARANCE LPTCC LOW PRESSURE TURBINE CLEARANCE CONTROL LPTR LOW PRESSURE TURBINE ROTOR LRU LINE REPLACEABLE UNIT LVDT LINEAR VARIABLE DIFFERENTIAL TRANSFORMER M MO AIRCRAFT SPEED MACH NUMBER MCD MASTER CHIP DETECTOR MCL MAXIMUM CLIMB MCDU MULTIPURPOSE CONTROL AND DISPLAY UNIT MCL MAXIMUM CLIMB MCT MAXIMUM CONTINUOUS THRUST MDDU MULTIPURPOSE DISK DRIVE UNIT mm. MILLIMETERS MMEL MAIN MINIMUM EQUIPMENT LIST MTBF MEAN TIME BETWEEN FAILURES MTBR MEAN TIME BETWEEN REMOVALS N N1 (NL) LOW PRESSURE ROTOR ROTATIONAL SPEED

作者: 帅哥 时间: 2009-2-12 13:43:12

N1ACT ACTUAL N1 N1DMD DEMANDED N1 N1CMD COMMANDED N1 N2 (NH) HP ROTOR ROTATIONAL SPEED N2ACT ACTUAL N2 NVM NON VOLATILE MEMORY O OAT OUTSIDE AIR TEMPERATURE OGV OUTLET GUIDE VANE OSG OVERSPEED GOVERNOR P P0 AMBIENT STATIC PRESSURE P25 HPC INLET TOTAL AIR TEMPERATURE PCU PRESSURE CONVERTER UNIT PLA POWER LEVER ANGLE PMC POWER MANAGEMENT CONTROL PMUX PROPULSION MULTIPLEXER PS12 FAN INLET STATIC AIR PRESSURE PS13 FAN OUTLET STATIC AIR PRESSURE PS3HP COMPRESSOR DISCHARGE STATIC AIR PRESSURE psi POUNDS PER SQUARE INCH psia POUNDS PER SQUARE INCHABSOLUTE psid POUNDS PER SQUARE INCH DIFFERENTIAL psig POUNDS PER SQUARE INCH GAUGE

作者: 帅哥 时间: 2009-2-12 13:43:44

PSM POWER SUPPLY MODULE PSS (ECU) PRESSURE SUB-SYSTEM PSU POWER SUPPLY UNIT PT TOTAL PRESSURE PT2 FAN INLET TOTAL AIR PRESSURE (PRIMARY FLOW) Q QAD QUICK ATTACH DETACH QTY QUANTITY R RAM RANDOM ACCESS MEMORY RDS RADIAL DRIVE SHAFT R/H RIGHT HAND RPM REVOLUTIONS PER MINUTE RTD RESISTIVE THERMAL DEVICE RTV ROOM TEMPERATURE VULCANIZING (MATERIAL) RVDT ROTARY VARIABLE DIFFERENTIAL TRANSFORMER S SAC SINGLE ANNULAR COMBUSTOR SAV STARTER AIR VALVE SB SERVICE BULLETIN SCU SIGNAL CONDITIONING UNIT SD SYSTEM DISPLAY SDAC SYSTEM DATA ACQUISITION CONCENTRATOR SDI SOURCE/DESTINATION IDENTIFIER (BITS) (CF ARINC SPEC)

作者: 帅哥 时间: 2009-2-12 13:44:07

SDU SOLENOID DRIVER UNIT SER SERVICE EVALUATION REQUEST SFC SPECIFIC FUEL CONSUMPTION SG SPECIFIC GRAVITY SLS SEA LEVEL STANDARD (CONDITIONS : 29.92 in. Hg/59 F) SMM STATUS MATRIX SMP SOFTWARE MANAGEMENT PLAN S/N SERIAL NUMBER SNECMA SOCIETE NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION SOAP SPECTROMETRIC OIL ANALYSIS PROGRAM SOL SOLENOID SOV SHUT-OFF VALVE S/R SERVICE REQUEST S/V SHOP VISIT SVR SHOP VISIT RATE SW SOFTWARE T T12 FAN INLET TOTAL AIR TEMPERATURE T25 HPC INLET AIR TEMPERATURE T3 HP COMPRESSOR DISCHARGE AIR TEMPERATURE T49.5 EXHAUST GAS TEMPERATURE T5 LPT DISCHARGE TOTAL AIR TEMPERATURE

作者: 帅哥 时间: 2009-2-12 13:45:16

TAT TOTAL AIR TEMPERATURE TBD TO BE DETERMINED TBV TRANSIENT BLEED VALVE T/E TRAILING EDGE T/C THERMOCOUPLE TC (T Case) HPT CASE TEMPERATURE TCC TURBINE CLEARANCE CONTROL TCJ TEMPERATURE COLD JUNCTION TECU ELECTRONIC CONTROL UNIT INTERNAL TEMPERATURE TEO ENGINE OIL TEMPERATURE TGB TRANSFER GEARBOX Ti TITANIUM TLA THRUST LEVER ANGLE TM TORQUE MOTOR TMC TORQUE MOTOR CURRENT TO/GA TAKE OFF/GO AROUND T/O TAKE OFF T oil OIL TEMPERATURE TPU TRANSIENT PROTECTION UNIT T/R THRUST REVERSER TRA THROTTLE RESOLVER ANGLE TRDV THRUST REVERSER DIRECTIONAL VALVE TRF TURBINE REAR FRAME TRPV THRUST REVERSER PRESSURIZING VALVE

作者: 帅哥 时间: 2009-2-12 13:45:49

TRSOV THRUST REVERSER SHUTOFF VALVE TSI TIME SINCE INSTALLATION (HOURS) TSN TIME SINCE NEW (HOURS) TTL TRANSISTOR TRANSISTOR LOGIC U UER UNSCHEDULED ENGINE REMOVAL V VAC VOLTAGE, ALTERNATING CURRENT VBV VARIABLE BLEED VALVE VDC VOLTAGE, DIRECT CURRENT VDT VARIABLE DIFFERENTIAL TRANSFORMER VRT VARIABLE RESISTANCE TRANSDUCER VSV VARIABLE STATOR VANE W WDM WATCHDOG MONITOR WFM WEIGHT OF FUEL METERED WOW WEIGHT ON WHEEL

作者: 帅哥 时间: 2009-2-12 13:48:40

ENGLISH/METRIC CONVERSIONS METRIC/ENGLISH CONVERSIONS 1 mile= 1.609 km 1 km = 0.621 mile 1 ft = 0.3048 m or 30.48 cm 1 m = 3.281 ft. or 39.37 in. 1 in. = 0.0254 m or 2.54 cm 1 cm = 0.3937 in. 1 mil. = 25.4 10-6 m or 25.4mm 1 mm = 39.37 mils. 1 in.2 = 6.45 cm² 1 m² = 10.76 sq. ft. 1 cm² = 0.155 sq.in. 1 USG = 3.785 l ( dm³ ) 1 in.3 = 16.39 cm³ 1 m³ = 35.31 cu. ft. 1 dm³ = 0.264 US gallon 1 cm³ = 0.061 cu.in. 1 lb = 0.454 kg 1 kg =2.205 lbs 1 psi = 6.890 kPa or 6.89 x 10-2 bar 1 Pa = 1.45 x 10-4 psi 1 kPa = 0.145 psi or 0.01 bar 1 bar = 14.5 psi °F = 1.8 x °C + 32 °C = ( °F - 32 ) /1.8

作者: 帅哥 时间: 2009-2-12 13:51:33

INTRODUCTION TO THE CFM56 FAMILY The CFM56 engine, a high by-pass, dual rotor, axial flow turbofan, was designed in the mid 70’s. It is a product of CFMI. CFM International is a company jointly owned by GENERAL ELECTRIC (GE) of the USA, and SOCIETE NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION (SNECMA) of France. CFMI, with the full backing of parent companies holding equal shares, has a dual function : - Overall program management, on behalf of both GE and SNECMA - Single interface with customers for marketing and product support

作者: 帅哥 时间: 2009-2-12 13:56:41

CFM INTERNATIONAL ORGANIZATION

作者: 帅哥 时间: 2009-2-19 10:07:44

Engine Applications
The following chart shows the various engine models for
the Airbus A319-A320-A321 aircraft.
The engine used on these aircraft is the CFM56-5B,
which has several different thrust ratings ranging from
22000 to 33000 lbs.

作者: 帅哥 时间: 2009-3-20 14:36:31

CFM56-5B MAIN CHARACTERISTICS

Type of engine Turbo fan
Arrangement Two spool axial flow
Rotation Clockwise (ALF)
Compressors
- Low Pressure:
Fan Stage 1
Booster Stages 2 to 5
- High Pressure:
HP Compressor Stages 1 to 9
Combustion chamber Annular SAC (option DAC)
Turbines
- HP Turbine Single stage
- LP Turbine Four stages
Weight 2381 kg (5249 lbs)
Overall dimensions
- Length 2.94m (115.86 ins)
- Height 2.14m (83.65 ins)
- Width 1.97m (77.88 ins)

作者: 帅哥 时间: 2009-3-20 14:42:46

CFM-56-5B

作者: 帅哥 时间: 2009-3-20 14:44:48

ENGINE GENERAL CONCEPT
The CFM56-5B engine is a high by-pass, dual rotor, axial
flow turbofan. It is supported by the wing pylon and
streamlined by cowlings.
Air is sucked into the intake by the fan blades and split
into two flow paths, the Primary and the Secondary.
The primary airflow passes through the inner portion of
the fan blades and is directed into a booster (LPC).
The airflow then enters a High Pressure Compressor
(HPC) and goes to a combustor. Mixed with fuel and
ignited, the gas flow provides energy to a High Pressure
Turbine (HPT) and a Low Pressure Turbine (LPT).
The secondary airflow passes through the outer portion
of the fan blades, the Outlet Guide Vanes (OGV’s) and
exits through the nacelle discharge duct, producing
approximately 80 % of the total thrust. It also plays a role
in the thrust reverser system.

作者: 帅哥 时间: 2009-3-20 14:46:23

aircraft pylon
飞机外挂架

作者: 帅哥 时间: 2009-3-20 14:52:55

design and operation

作者: 帅哥 时间: 2009-3-20 14:56:47

ENGINE GENERAL CONCEPT

The CFM56-5B engine uses a maintenance concept
called ‘On Condition Maintenance’. This means that the
engine has no periodic overhaul schedules and can
remain installed under the wing until something important
occurs, or when lifetime limits of parts are reached.
For this reason, to monitor and maintain the health of the
engine, different tools are available, which are :
- Engine performance trend monitoring
- Borescope inspection
- Lubrication particles analysis
- Spectrometric Oil Analysis Program (S.O.A.P)
- Engine vibration monitoring system

borescope 管道镜

spectrometric 光谱测定的,度谱的,分光仪的,光谱仪的

作者: 帅哥 时间: 2009-3-20 14:58:55

on condition monitoring

作者: 帅哥 时间: 2009-3-20 15:00:05

ENGINE GENERAL CONCEPT

The CFM56-5B engine consists of two independent
rotating systems :
- The low pressure system rotational speed is
designated N1.
- The high pressure system rotational speed is
designated N2.
The engine rotors are supported by 5 bearings, identified
in manuals as numbers 1 thru 5, where No. 1 is the most
forward and No. 5 the most aft. These bearings are
housed in 2 dry sump cavities provided by the fan and
turbine frames.
Engine structural rigidity is obtained with short lengths
between two main structures (frames).
The accessory drive system uses energy from the high
pressure compressor rotor to drive the engine and
aircraft accessories. It also plays a major role in starting.

作者: 帅哥 时间: 2009-3-20 15:03:47

general engine concept

作者: 帅哥 时间: 2009-3-20 15:05:10

ENGINE GENERAL CONCEPT

The CFM56-5B is a modular concept design engine. It
has 17 different modules that are enclosed within three
major modules and an accessory drive module.
The 4 modules are :
- The Fan Major Module
- The Core Engine Major Module
- The Low Pressure Turbine Major Module
- The Accessory Drive Module

作者: 帅哥 时间: 2009-3-20 15:07:20

modular design

作者: 帅哥 时间: 2009-3-20 15:08:39

FAN SECTION
The fan section is at the front of the engine and,
downstream from the air inlet cowl, the section includes
the fan and booster module and fan frame module.
The purposes of the fan and booster are :
- to accelerate air overboard to generate thrust.
- to increase the pressure of the air directed to the
High Pressure Compressor (HPC).
After entering the air inlet cowl, the total engine airflow
passes through the fan rotor, which increases the air’s
kinetic energy.
Most of the airflow is ducted overboard producing
approximately 80 % of the total thrust. The remainder is
directed through the booster, where it is pressurized
before entering the HPC.

作者: 帅哥 时间: 2009-3-20 15:10:23

FAN SECTION
The fan section is at the front of the engine and,
downstream from the air inlet cowl, the section includes
the fan and booster module and fan frame module.
The purposes of the fan and booster are :
- to accelerate air overboard to generate thrust.
- to increase the pressure of the air directed to the
High Pressure Compressor (HPC).
After entering the air inlet cowl, the total engine airflow
passes through the fan rotor, which increases the air’s
kinetic energy.
Most of the airflow is ducted overboard producing
approximately 80 % of the total thrust. The remainder is
directed through the booster, where it is pressurized
before entering the HPC.

作者: 帅哥 时间: 2009-3-20 15:10:37

kinetic energy
动能

作者: 帅哥 时间: 2009-3-20 15:13:53

fan section

作者: 帅哥 时间: 2009-3-20 15:23:29

FAN AND BOOSTER MODULE
The Fan and Booster module consists of :
- a spinner front cone
- a spinner rear cone
- a single stage fan rotor
- a four stage axial booster
The spinner front cone is designed to minimize ice buildup
and is attached to the spinner rear cone.
The spinner rear cone holds the blades axially in position
of the fan disk.
The fan disk supports the mid-span shrouded fan blades
and a booster spool.
The booster spool accommodates booster blade stages,
numbers 2 thru 5.
The booster vane assembly stages, numbers 1 thru 5,
are stacked and mounted on the fan frame.

作者: 帅哥 时间: 2009-3-20 15:25:46

fan and booster design

作者: 帅哥 时间: 2009-3-20 15:31:30

FAN AND BOOSTER MODULE (CONTINUED)
Spinner front cone
Interference fit and single angular mounting positions are
characteristics of the installation of the front and rear
cone onto the fan disk.
The spinner front cone has an offset hole on its rear
flange, identified by an indent mark, to ensure correct
alignment for installation onto the rear cone front flange.
The rear flange has 6 mounting screw locations and 3
threaded inserts, located every 120°, for installation of
jackscrews used in removal procedures.

作者: 帅哥 时间: 2009-3-20 15:41:27

interference fit

过盈

mounting screw
安装螺钉

jackscrew

起重螺丝

作者: 帅哥 时间: 2009-3-20 15:42:39

spinner front cone

作者: 帅哥 时间: 2009-3-20 15:43:08

FAN AND BOOSTER MODULE (CONTINUED)
Spinner rear cone
The front flange of the spinner rear cone has 6 line
replaceable, crimped, self-locking nuts.
The inner rear flange has 12 mounting screw holes, for
installation onto the fan disk, and there are a further 6
threaded holes for the installation of jackscrews used in
rear cone removal procedures.
Both front and rear flanges have an offset hole to ensure
correct installation and they are identified by indent
marks.
The rear cone also has an integrated air seal that is
glued to its inner rear flange.

作者: 帅哥 时间: 2009-3-20 15:50:14

rear cone

作者: 帅哥 时间: 2009-3-20 15:51:44

FAN AND BOOSTER MODULE (CONTINUED)
Spinner rear cone (continued)
The rear cone prevents axial disengagement of spacers
used in the fan blade retention system.
It also supports a series of balancing screws that are
installed on its outer diameter. There are two sets of
balancing screws available and the screws in each set
are identified as either P01 to P07 or, P08 to P14. The
numbers, which are engraved on the screw heads, are
equivalent to various weights.
An indent mark is located in between two balancing
screws for correct installation of the rear cone onto the
fan disk and for identification of fan blade No.1.

作者: 帅哥 时间: 2009-3-20 16:16:55

rear cone

作者: 帅哥 时间: 2009-3-20 16:19:17

FAN AND BOOSTER MODULE (CONTINUED)
Fan disk
The fan disk outer rim has 36 dovetail recesses for the
installation of the fan blades.
The inner front flange has an imprint to identify an offset
hole for rear cone installation.
There are also two identification marks engraved on
either side of blade recesses No.1 and 5.

作者: 帅哥 时间: 2009-3-20 16:20:15

fan disk front flange

作者: 帅哥 时间: 2009-3-20 16:23:57

FAN AND BOOSTER MODULE (CONTINUED)
Fan blades
There are 36 titanium alloy, mid-span shrouded fan
blades.
Each blade has a dovetail base that slides into a recess
on the fan disk outer rim.
A retainer lug, machined at the rear end of the blade
root, engages the forward flange of the booster spool
and limits axial movements.
A spacer, installed underneath each blade, limits the
radial movement.

作者: 帅哥 时间: 2009-3-20 16:24:29

fan blades

作者: 帅哥 时间: 2009-3-20 16:26:24

FAN AND BOOSTER MODULE (CONTINUED)
Fan blades (continued)
Each blade has specific indications engraved on the
bottom of the root :
- Part number
- Serial number
- Momentum weight
- Manufacturer code
The fan blade root faces have an anti-friction plasma
coating (Cu-Ni-In) and a top coat of cured molybdenumbase
film varnsh, which acts as a lubricant.
Lubrication of blade roots is further improved by the
application of solid molybdenum-base lubricant before
installation on the fan disk.
The mid-span shroud contact surfaces have a tungstencarbide
coating. They are also lubricated with solid
molybdenum-base lubricant at blade installation.

作者: 帅哥 时间: 2009-3-20 16:33:19

molybdenum
D.J.[məˈlibdinəm]
K.K.[məˈlɪbdənəm]
n.
钼

tungsten carbide
碳化钨,硬质合金

sub-contractor
分承包人;副承包商

hard coat
硬膜

作者: 帅哥 时间: 2009-3-20 16:33:34

fan blade root

作者: 帅哥 时间: 2009-3-20 16:36:19

mounting flange
安装用法兰

作者: intellectual 时间: 2009-11-18 21:39:52

谢谢了，怎么看不到链接

作者: luozhiyun 时间: 2009-12-17 00:16:43

果然是强悍如楼主....

作者: cren_06 时间: 2009-12-25 23:02:56

最近在学习发动机

作者: zczc59715046 时间: 2010-4-15 14:43:04

谢谢分享,谢谢分享谢谢分享

作者: hlj853 时间: 2010-5-4 01:18:45

打包下载多好呀

作者: zczc59715046 时间: 2010-5-8 15:18:16

11312312312313

作者: f214216709 时间: 2010-5-17 13:24:22

没有附件的吗？

作者: f214216709 时间: 2010-7-30 15:29:17

没有内容的吗

作者: 月夜青衫 时间: 2010-9-12 16:56:54 标题: 呵呵

谢谢老兄

作者: fengxinghuajing 时间: 2010-9-13 07:41:28 标题: 1

好好学习天天向上

作者: 快乐’傲翔 时间: 2010-10-30 15:26:00

能不能给我发一完整的文件呀？谢谢！（QQ1048178982）

作者: kinran 时间: 2010-12-29 14:10:05

谢谢谢~

作者: kinran 时间: 2011-1-3 11:09:14

麻烦楼主给我发份这个的邮件吧！拜谢！！！！！！！！！！！448797344@qq.cm

作者: 979199501 时间: 2011-4-9 20:01:12 标题: 回复 1# 帅哥的帖子

民航网确实很多好东西，基本上都是帅哥的，谢谢分享

作者: 979199501 时间: 2011-4-12 01:05:33 标题: 回复 1# 帅哥的帖子

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