2 Engine General

Created by Rafik Chabou ENGINE CF6-80E1 General Familiarization

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22 -- EE nn gg ii nn ee GG ee nn ee rr aa ll Engine Specifications

ObjectivesGiven an objective exercise, you will be able to:

Identify the location of the identification data plate Identify the identification data plate and engine specifications Identify the purpose of the identification data plate and engine

specifications

Overview The engine specifications for the CF6-80E1 engine consist ofthe following information:

Application Ratings Dimensions Engine safety hazards Ground transportation requirements

Each engine has an engine identification data plate that indicates the ratings

and other information for that engine. In this lesson, you will learn about the

identification and purpose of different engine specifications. You will also

learn about the identification, location, and purpose of the engine

identification data plate.

Purpose The engine specifications show the dimensions of the engine. The

applications identify the aircraft that are powered by the CF6-80E1 engine.

The ratings indicate the thrust developed by the engine. The engine safety

hazards show the areas that should be avoided when working close to an

operating engine. Information about the ground transportation requirements

helps to avoid damage to the engine and injury to the personnel during

transportation.


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ApplicationThe CF6-80E1 engine is available in the following variants:

CF6-80E1A1 CF6-80E1A2 CF6-80E1A3 CF6-80E1A4

These variants are installed on the following types of aircraft:

CF6-80E1A1 - Airbus A330-300 CF6-80E1A2 - Airbus A330-300 CF6-80E1A3 - Airbus A330-200 CF6-80E1A4 - Airbus A330-200

Ratings

Identification Data PlateLocation: The identification data plate is on the lower left-hand side of theaft fan case at the 8:30 position.

Identification: The identification data plate is a metal plate with a red-colored background and with text boxes for recording engine-relatedinformation.

Purpose: The identification data plate serves as a single source of importantengine information. This engine information includes the following data:


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Type certificate no. Production certificate number Model number Serial number Configuration type Take-off thrust rating Maximum continuous thrust

rating Service bulletin numbers Date of manufacturing Status of EPA compliance

Specifications

Engine Safety HazardsLocation: The engine safety hazards are areas that are specified on theinlet and exhaust sides of aninstalled engine.Identification: These hazard areasare designated as follows:

Inlet suction danger area Exhaust wake danger area

However, personnel can approach

an operating engine at minimum

ground idle thrust using a specified


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area called the Entry Corridor Safety zone. For more information on these

areas and the precautions that need to be taken when working close to a

running engine, refer to the Aircraft Maintenance Manual.

Purpose: The engine safety hazard areas help to prevent injury to personneland damage to the engine and the aircraft.

Ground TransportationRequirementsIdentification: The CF6-80E1 engine can be transported as a complete

engine assembly or as separate subassemblies or as individual modules by

ground, air, or sea transportation.

Note: GE Aircraft Engines does

not recommend shipment of the

engine by rail.

When transporting the engine,great care must be taken aboutthe following:

The shipping stand mustmeet GEAE specificationM50TF1338.

Proper tie-down techniques must be used. Minimum clearances between the engine, stand and the trailer bed

must be maintained. When transporting by ground, vehicles with shock and vibration

absorbing systems should be used.

Purpose: The ground transportation requirements help to prevent damage tothe engine and injury to personnel during transportation.


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Engine ModulesObjectivesGiven an objective exercise, you will be able to:

Identify the location of the enginemodules

Identify the engine modules Identify the purpose of the enginemodules

OverviewThe CF6-80E1 engine is divided into thefollowing modules: Fan module Core module High pressure turbine (HPT) module Low pressure turbine (LPT) module Accessory drive module

In this lesson, you will learn about the location,identification, and purpose of these modules.

Fan ModuleLocation Left Side ViewThe fan module is installed at the front of the engine,adjacent to the core module.

IdentificationThe fan module consists of the following components:

Fan blades assembly Low pressure compressor rotor Low pressure compressor stator Fan frame

PurposeSupplies approximately 80 % of the engine thrust due to the acceleration of

the fan bypass airflow Boosts the primary airflow before it enters the high

pressure compressor, Houses the A-sump containing nos. 1, 2, and 3 bearings

Core ModuleLocation Left Side ViewThe core module is installed aft of the fan module, adjacent to the high


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pressure turbine (HPT) module.

IdentificationThe core module consists of the following components:

Compressor rotor Compressor stator Compressor rear frame (CRF) Combustor Stage 1 HPT nozzle

PurposeThe core module supplies approximately 20 % of the engine thrust throughthe combustion and subsequent acceleration of the core airflow. The coremodule also provides drive to the accessory gearbox (AGB).

HPT ModuleLocation Left Side ViewThe HPT module is installed aft of the core module, adjacentto the low pressure turbine (LPT) module.

IdentificationThe HPT module consists of the following components:

HPT rotor HPT stator

PurposeThe HPT module extracts energy from the hot combustion gases leaving thecombustor. This energy is used by the HPT module to drive the HPC.

LPT ModuleLocation Left Side ViewThe LPT module is installed immediately aft of the HPT module.

IdentificationThe LPT module consists of the following components:

LPT rotor LPT stator

PurposeExtracts energy from the exhaust gases leaving the HPT module.This energy is used by the LPT module to drive the fan assembly.Houses the D-sump and contains the No. 6 bearing.


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Accessory Drive ModuleLocation Left Side ViewThe accessory drive module consists of components that areinstalled below the core module and inside the fan module.

IdentificationThe accessory drive module consists of the followingcomponents:

Inlet gearbox Transfer gearbox Accessory gearbox

PurposeThe accessory drive module receives the driving torque from thecompressor and drives the various accessories that are mounted on itsforward and rear sides.

Fan ModuleObjectivesGiven an objective exercise, you will be able to:

Identify the location of the components of the fan module Identify the components of the fan module Identify the purpose of the components of the fan module Identify the purpose of the fan module

OverviewThe fan module is divided into the followingcomponents:

Fan blades assembly Low pressure compressor rotor Low pressure compressor stator Fan frame

In this lesson, you will learn about the location,

identification, and purpose of the components

of the fan module


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Location Left Side ViewThe fan module is at the front of the engine. The fan module consists of a

number of components that are listed below. The fan blades assembly is

installed at the front of the fan module. The LPC rotor is installed aft of

the fan blades assembly inside the forward and aft fan cases. The LPC

stator is inside the forward and aft fan cases and surrounds the LPC rotor.

The fan frame is installed between the LPC and the HPC assemblies.

Purpose

Supplies approximately 80 % of the engine thrust by accelerating thefan bypass airflow

Boosts the primary airflow before it enters the high pressurecompressor

Houses the A-sump containing nos. 1, 2, and 3 bearings

Fan Blades AssemblyLocation: The fan blades assembly is

installed at the front of the fan module.

Identification: The fan blades assembly

consists of the following components:

Stage 1 fan disk 34 fan blades

The fan blades are installed on the stage 1fan disk.

Purpose: The fan blades assembly brings in air and accelerates it through

the fan duct to produce approximately 80 % of the rated thrust.


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Low Pressure Compressor RotorLocation: The LPC rotor is installed aft of the fan blades assembly insidethe forward and aft fan cases.

Identification: The LPC rotor consists of thefollowing components:

Stages 2 to 5 booster spools Stages 2 to 5 blades

Both the spools and the blades are made oftitanium.

Purpose: The primary function of the LPC rotoris to boost the flow of the fan inlet air into theHPC.

Low Pressure Compressor StatorLocation: The LPC stator is located insidethe forward and aft fan cases andsurrounds the LPC.

Identification: The LPC stator consists ofthe stages 2 to 5 stator vanes.

Purpose: The different stages of the LPCstator make sure that air is sent to thevarious stages of the LPC rotor at thecorrect angle.

Fan FrameLocation: The fan frame is installedbetween the LPC and the HPC assemblies.

Identification: The fan frame is a cast titanium unit with a central hub and12 radial struts.


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Purpose: The fan frame provides the main structural support for the

subassemblies of the fan module, core module,

accessory drive module, and the forward engine

thrust mount. The fan frame also contains air

extraction ports and passages for sump

pressurization, core compartment cooling, and

active clearance control. A variable bleed valve

(VBV) is installed in the fan frame to control the

airflow from the LPC rotor to the HPC rotor.

Core ModuleObjectivesGiven an objective exercise, you will be able to:

Identify the location of the components of the core module Identify the components of the core module Identify the purpose of the components

of the core module Identify the purpose of the core module

OverviewThe core module is divided into the followingcomponents:

Compressor rotor Compressor stator Compressor rear frame (CRF) Combustor Stage 1 HPT Nozzle

In this lesson, you will learn about the location,identification, and purpose of the components of the core module.


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Location Left Side ViewThe core module is aft of the fan module. The core module consists of anumber of components that are listed below.

The compressor rotor is aft of the fan assembly and is surrounded bythe compressor stator. The front of the rotor is held in the aft end ofthe A-sump. In the rear, the rotor is held in the B and C sumps.

The compressor stator is aft of the fan module and surrounds thecompressor rotor.

The combustor is installed aft of the HPC. The compressor rear frame (CRF) is installed between the HPC and

the HPT. The stage 1 HPT nozzle is installed immediately aft of the combustor.

Purpose

Compresses the inlet air and allows combustion to take place, thusproviding the engine with approximately 20 % of the thrust

Provides driving torque to the AGB Provides structural support to several engine components

Compressor RotorLocation: The compressor rotor is aft of the

fan assembly and is surrounded by the

compressor stator. The front of the rotor is

held in the aft end of the A-sump. In the

rear, the compressor rotor is held in the B

and C sumps.

Identification: The compressor rotor

consists of 14 high-pressure compressor

stages. Each stage contains a set of blades.

The front of the rotor is supported by the

No. 3 roller bearing. The aft of the the rotor


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is supported by the No. 4 roller bearing and the No. 4 ball bearing.

Purpose: The compressor rotor compresses the air coming from the LPCbefore the air enters the combustor for combustion.

Compressor StatorLocation: The compressor stator is at the aft of the fan assembly andsurrounds the compressor rotor.

Identification: The compressor stator consists of

two casing halves. The two halves contain one stage

of inlet guide vanes (IGV), five stages of variable

stator vanes, and eight stages of fixed stator vanes.

Purpose: The compressor stator makes sure that air

compressed by each compressor rotor stage is

passed to the next compressor rotor stage at the

correct angle. The stator also provides the main

structural support to the central portion of the engine.

Compressor Rear Frame (CRF)Location: The compressor rear frame (CRF)is between the HPC and the HPT.

Identification: The CRF is a casting thatconsists of the following components:

Annular combustor Fuel nozzles Fuel manifold Igniter plugs 10 struts Stage 1 HPT nozzle


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Purpose:

Provides main structural support to the engine Provides space for the

B-C sump and the accompanying bearings

Provides a flowpath between the HPC and the HPT. Transmits axial and radial loads from the HPT rotor to the static

structure

CombustorLocation: The combustor is installed aft of the HPC.

Identification: The combustor consists of thefollowing components:

Inner and outer cowl assemblies Dome assembly Inner and outer liner assemblies

Purpose: The combustor provides space for proper

mixing and subsequent combustion of the mixture of

fuel and air.

Stage 1 HPT Nozzle

Location: The stage 1 HPT nozzle is installedimmediately aft of the combustor.

Identification: The stage 1 HPT nozzle consists of23, two-vane nozzle segments. The nozzle ismounted on the stationary seal support.

Purpose: The stage one HPT nozzle directs hot,

high-velocity, high-pressure gases onto the stage 1 HPT rotor blades, thus

causing them to rotate.


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HPT ModuleObjectivesGiven an objective exercise, you will be able to:

Identify the location of the components of the HPT module Identify the components of the HPT module Identify the purpose of the components of the HPT module Identify the purpose of the HPT module

OverviewThe high pressure turbine (HPT) module of the CF6-80E1 engine consists ofthe following components:

HPT rotor HPT stator

In this lesson, you will learn about

the location, identification, and

purpose of the components of the

HPT module.

Location Left Side ViewThe HPT module is installed aft of the core module. The components of the

module are listed below.

The HPT rotor is installed aft of the stage 1 HPT nozzle. The HPT stator surrounds the HPT rotor and is installed aft of the

stage 1 HPT nozzle.

Purpose

The HPT module extracts energy from the hot combustion gases

leaving the combustor. This energy is used by the HPT module to drive

the HPC rotor.


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HPT RotorLocation: The HPT rotor is installed aft of the stage 1 HPT nozzle.

Identification: The HPT rotor is a two-stageturbine that is splined to the HPC rotor inthe core module.

Purpose: The purpose of the HPT rotor is to

extract energy from the hot, high-pressure

combustion gases leaving the combustor. This

energy is used by the HPT rotor to drive the HPC rotor in the core module.

HPT StatorLocation: The HPT stator surrounds the HPT rotor and is installed aft ofthe stage 1 HPT nozzle.

Identification: The HPT stator consistsof the following components:

Stage 2 HPT nozzle assembly Stages 1 and 2 shrouds Stator case Active clearance control manifold

Purpose:

Provides a sealed flowpath for gases flowing out from the HPT rotor Forms part of the active and passive clearance control system that is

used to maintain close clearances between the shrouds and the HPTrotor blades

LPT ModuleObjectivesGiven an objective exercise, you will be able to:

Identify the location of the components of the LPT module Identify the components of the LPT module


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Identify the purpose of the components of the LPT module Identify the purpose of the LPT module

OverviewThe low pressure turbine (LPT) module of the CF6-80E1 engine consists ofthe following components:

LPT rotor LPT stator Turbine rear frame (TRF)

In this lesson, you will learn about the

location, identification, and purpose of

the components of the LPT module.

Location Left Side ViewThe LPT module is aft of the HPTmodule. The components of themodule are listed below.

The LPT rotor is installed aft of the HPT module and is enclosedwithin the LPT stator.

The LPT stator is aft of the HPT module and encloses the LPTrotor.

The turbine rear frame (TRF) is installed between the LPTstator and the exhaust nozzle.

PurposeThe LPT module drives the fan blades assembly and the LPC rotor in the

fan module. The LPT module also provides support and space for

components at the rear of the engine.

LPT RotorLocation: The LPT rotor is installed aft of the HPT module and is enclosed

within the LPT stator.


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Identification: The LPT rotor is a five-stage

turbine that is driven by the combustion gases

leaving the HPT. The LPT rotor is supported by the

No. 6 roller bearing housed in the D-sump.

Purpose: The LPT rotor drives the fan bladesassembly and the LPC rotor in the fan module.

LPT StatorLocation: The LPT stator is aft of the HPT module and encloses the LPTrotor.

Identification: The LPT stator consists of a

one-piece, tapered casing. The inside of the

casing contains five stages of stator vanes.

Purpose: Each stage of the LPT stator

makes sure that the exhaust gases exiting

from the previous LPT rotor stage are

directed to the next stage at the correct

angle. The LPT stator provides support to the rear of the engine. The outer

portion of the LPT stator casing provides space for different pipes and

manifolds.

Turbine Rear Frame (TRF)Location: The turbine rear frame (TRF) is installed between the LPT stator

and the exhaust nozzle.


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Identification: The TRF consists of an inner and an

outer flange that are held together by 12 radial

struts. The outer flange contains two bolt circles,

rear engine mounts, and radial ports. The inner

flange houses the D-sump.

Purpose:

Supports the rear of the engine and the LPTrotor and stator assemblies

Houses the D-sump Straightens the airflow into the exhaust nozzle for improved engine

performance Provides space for rear engine mounts Provides ports for insertion of the T5 sensor and for borescope

inspection

Accessory Drive ModuleObjectivesGiven an objective exercise, you will be able to:

Identify the location of the components of the accessory drive module Identify the components of the accessory drive module Identify the purpose of the components of the accessory drive module Identify the purpose of the accessory drive module

OverviewThe accessory drive module of

the CF6-80E1 engine consists of

the following components:

Inlet gearbox (IGB) Transfer gearbox (TGB) Accessory gearbox (AGB)


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In this lesson, you will learn about the location, identification, and purposeof the components of the accessory drive module.

Location Left Side ViewThe accessory drive module is installed below the core module. The module is

mounted on the lower surface of the compressor casing. The components of

the module are listed below.

The inlet gearbox (IGB) is attached to the forward side of thefan frame.

The transfer gear box (TGB) is installed aft of the fan frame atthe 6 o’clock position

The accessory gearbox (AGB) is mounted on the lower portion ofthe engine core at the 6 o'clock position.

PurposeThe accessory drive module transfers torque from the HPC rotor to the

AGB to drive the various engine and aircraft accessories.

Inlet Gearbox AssemblyLocation: The inlet gearbox (IGB) assembly is attached to the forward side

of the fan frame.

Identification: The IGB consists of a titanium housing containing an adapter,

bevel gears, bearings, and oil jets.

Purpose: The IGB transfers torque from

the HPC rotor to the transfer gearbox

(TGB) through the radial drive shaft.


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Transfer GearboxLocation: The transfer gearbox (TGB) is installed on the lower, rear side of

the fan module between the inlet gearbox (IGB) and the accessory gearbox

(AGB).

Identification: The TGB is made up of an

aluminum housing, adapters, bevel gears,

bearings, and oil jets.

Purpose: The TGB transfers the torque to

the AGB through the horizontal drive

shaft.

Accessory Gearbox

Location: The accessory gearbox (AGB) is mounted on the lower portion of

the engine core at the 6 o'clock position.

Identification: The AGB is made

up of a one-piece aluminum alloy

housing containing drive pad

adapters, spur gears, bearings, and

seals.

Purpose: The AGB provides torque

to a number of engine and aircraft

accessories such as the IDG, the

hydraulic pump, and the fuel pump.


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Airflow PathsObjectives

Given an objective exercise, you will be able to:

Identify the location of the components of the airflow paths Identify the components of the airflow paths Identify the purpose of the components of the airflow paths

OverviewThe airflow paths of the CF6-80E1 engine can be divided into the followingcomponents:

Fan bypass airflow Core/combustor airflow Parasitic airflow Sump pressurization

In this lesson, you will learn about the location, identification, and purposeof the components of the airflow paths.

LocationThe various airflow paths of the CF6-80E1 engine are listed below:

The fan bypass airflow or the secondary airflow is the fan air thatbypasses the engine core and exits through the fan nozzle.

The core/combustor airflow or the primary airflow consists of air thatflows through various sections of the engine core. This air then exitsinto the atmosphere through the engine exhaust nozzle.

Parasitic airflow is the air that is bled from the core/combustorairflow and the fan bypass airflow.

Sump pressurization consists of parasitic airflow that is used topressurize the engine sumps.

Fan Bypass AirflowLocation: The fan bypass airflow or the secondary airflow is the fan air that

bypasses the engine core and exits through the fan nozzle.


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Purpose: The fan bypass airflow provides

approximately 80 %of the thrust to the

engine. The fan bypass airflow also

provides a portion of the air for parasitic airflow.

Core/Combustor Airflow

Location: The core/combustor airflow or the primary airflow consists of air

that flows through various sections of the engine core. This air then exits

into the atmosphere through the engine exhaust nozzle.

Purpose: The core/combustor airflow provides

approximately 20 % of the thrust to the

engine. The core/combustor airflow also provides a majority of the air for

parasitic airflow.

Parasitic Airflow

Location: Parasitic airflow is the air that isbled from the core/combustor airflow and the fanbypass airflow.

Purpose: The parasitic airflow is used for various external and internalengine functions such as:

Sump pressurization, internal cooling, and thrust reverser operation. HPT and LPT active clearance control. Engine anti-icing, aircraft ventilation, and cabin air-conditioning.


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Sump Pressurization

Location: Sump pressurization consists of parasitic airflow that is used topressurize the engine sumps.

Purpose: Sump pressurization is used toprovide pressurized air to the areas aroundthe sumps. This minimizes leakage of oilacross the sump seals during engine operation,especially at high power settings.

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2 Engine General