POWER PLANT IAE V2500 PRESENTATION

INTRODUCTION

The IAE V2500-A5 engine is a two spool, axial flow,

high bypass ratio turbo fan power engine. The
V2500-A5 powers the complete single aisle family of
aircraft except the A318. V2500-A5 engines are
available in several thrust ratings.
All the engines are basically the same. A
programming plug on the Electronic Engine Control
(EEC) changes the available thrust.

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INTRODUCTION
Two spool, axial flow, high bypass ratio turbo fan power engine

Japanese Aero Engine

Corporation: Fan & LPC
Rolls Royce: HPC & Ext Gearbox
Pratt & Whitney: Comb Chamb &
HPT
MTU Germany: LPT
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POWER PLANT IAE V2500 PRESENTATION

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POWER PLANT IAE V2500 PRESENTATION

INSTALLATION

The power plant installation includes the engine, the

engine inlet, the exhaust, the fan cowls and the
reverser assemblies. The pylon connects the engine
to the wing structure. The engine is attached to the
pylon by FWD and AFT mounts.

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INSTALLATION

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GENERAL
ENGINE CHARACTERISTICS
The IAE V2500-A5 engine is a two spool, axial flow, high The pylons supply an interface between the engine and
bypass ratio turbo fan power engine. The V2500-A5 the aircraft for electrics and fluids.
powers the complete single aisle family of aircraft A320 .
V2500-A5 engines are available in several thrust ratings. NACELLE
All the engines are basically the same. A programming The engine is enclosed in the nacelle, which supplies
plug on the Electronic Engine Control (EEC) changes the aerodynamic airflow around the engine and ensures
available thrust. protection for the accessories.
The power plant installation includes the engine, the
engine inlet, the exhaust, the fan cowls and the reverser ENGINE CONTROL
assemblies. The pylon connects the engine to the wing The engine includes a Full Authority Digital Engine
structure. The engine is attached to the pylon by FWD Control (FADEC), which supplies engine control, engine
and AFT mounts. monitoring and help for maintenance and trouble
The Airbus A319/A320 are powered by two IAE V2500- shooting.
A5 turbofan engines.
These engines can produce a thrust ranging from 22,000
lbs (9,980 kg) to 33,000 lbs (14,970 kg) depending on
the aircraft version set by the engine data-programming
plug.

PYLON
The engines are attached to the lower surface of the
wings by pylons. 8
ENGINE CHARACTERISTICS

E: Enhanced, hot & high

Nacelle, supplies aerodynamic
M: Corporate A319 climb airflow around the engine and
ensures protection for the
accessories.

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ENGINE GENERAL PARAMETERS

Flat rating: by Engine data programming plug

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POWER PLANT INSTALLATION D/O

MODULAR CONCEPT

The V2500-A5 is designed using a modular concept.

For easy maintenance and quicker return-to-service,
the engine is made of 5 primary modules:
fan,
intermediate case,
High Pressure (HP) system,
Low Pressure (LP) turbine,
accessory drives.

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MODULAR CONCEPT

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POWER PLANT INSTALLATION D/O

LP ROTOR the booster compressor and the fan.

The LP rotor has the forward fan, the booster Exhaust gas from the LP turbine goes through a nozzle
compressor and the LP shaft, all driven by the LP to supply propulsive thrust.
turbine. The speed of the LP rotor is indicated on ECAM
as N1. The LP rotor is supported by roller and ball bearings,
which are lubricated and cooled.
The fan assembly has 22 wide-chord blades and
supplies most of the engine thrust. The air produced by The turbine exhaust case is the main structural support
the fan is known as secondary airflow or bypass airflow. for the rear of the engine. It is also the location of the
The intermediate case is the main structural support for rear engine mount.
the front of the engine. To protect the fuselage in case of
a fan failure, it is designed to contain any broken blades.
The 4-stage booster compressor is located in the
intermediate case. The booster supplies air to the engine
core. This is primary airflow. The LP rotor (N1) is made of
the fan and the booster compressor
driven by the LP turbine.
The intermediate case is also the location for the forward
engine mount.

The five-stage LP Turbine extracts energy from the gas

stream delivered from the HP Turbine in order to drive 13
MODULAR CONCEPT - LP ROTOR

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POWER PLANT INSTALLATION D/O

HP ROTOR AND COMBUSTION CHAMBER

The HP rotor is made of a 10-stage HP compressor driven

by a 2-stage HP turbine. The speed of the HP rotor is
indicated on the ECAM as N2.

The HP compressor is also the source of customer bleed

air.
The HP rotor is supported by roller and ball bearings,
which are lubricated and cooled.

The annular combustion chamber is located between the

HP compressor and HP turbine. It is equipped with ports
for 20 fuel nozzles and 2 igniter plugs.

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MODULAR CONCEPT - HP ROTOR AND COMBUSTION CHAMBER

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POWER PLANT INSTALLATION D/O

ACCESSORY GEARBOX

The accessory gearbox is located at the bottom of

the fan case and is driven by the HP rotor through
the Angle gearbox. The fuel pumps, oil pumps,
hydraulic pump, Integrated Drive Generator (IDG)
and dedicated alternator are all driven by the
gearbox.
During engine starting, the starter rotates the HP
compressor through the gearboxes.

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MODULAR CONCEPT - ACCESSORY GEARBOX

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POWER PLANT INSTALLATION D/O

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ENGINE BEARINGS

ENGINE BEARINGS NO.4 AND NO.5 BEARINGS

The No.1, 2 and 3 (front) bearing compartment is built The No.4 bearing is a roller bearing, which is secured
into the case module and contains the support bearings onto the bearing support assembly. Rotor support is
for the low spool and high spool stubshafts. transmitted through the bearing and bearing support to
The No.4 bearing compartment is part of the the diffuser case inner wall.
diffuser/combustor module and the No 5 is located on the The Low Pressure Turbine (LPT) shaft is supported at
exhaust case. the rear end by the No.5 roller bearing, which is located
on the exhaust case. The No.5 bearing inner race is
NO.1 AND NO.2 BEARINGS secured on the shaft by an interference fit and is secured
The No.1 ball bearing carries the axial loads generated against the seal assembly by a coupling nut. The outer
by the LP rotor system. This bearing is a split inner race race is loosely fitted in the bore of the bearing support.
ball bearing. The No.1 bearing support provides
structural support for the No.1 bearing, oil supply tube
and No.1 bearing seal support. The No.2 bearing is a
cylindrical roller bearing with a shouldered outer race.

NO.3 BEARING
The No.3 ball bearing, internal gearbox and support
assembly are located in the internal gearbox and drive
section of the Low Pressure Compressor (LPC)
intermediate case module.

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ENGINE BEARINGS

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COMPRESSOR - LPC FAN MODULE ASSEMBLY
At the fan exit the air stream divides into two flows:
·the core engine flow
·the by-pass flow
The core engine “hot” exhaust and the “cool” bypass flow are “mixed”
in the C.N.A. before passing through the single propelling nozzle to
the atmosphere

By-pass
Flow

Core
Flow

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COMBUSTION SECTION

COMBUSTION SECTION

The diameter of the diffuser section is larger at the rear

than at the front.

This diametral difference decreases the speed of the air

and changes the energy of the speed into pressure.

The combustion section includes primarily the diffuser

case, combustor, fuel injector and igniters. The high
compressor exit guide vanes, the turbine nozzle assembly
and the No.4 bearing compartment are also part of the
module.

The diffuser case has twenty mounting pads, where the

fuel injectors are installed and two mounting pads where
the igniter plugs are installed and six Borescope bosses
located around the case.

The combustor is an annular type combustor, which

includes an outer liner assembly and an inner liner
assembly.
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COMBUSTION SECTION OPERATION

Primary functions:
- straighten the flow of air from the HPC,
- change the flow of air characteristics to get the
best speed and pressure for combustion,
- mix fuel with the air and supply ignition to make the
fuel burn,
- hold the No.4 bearing in position
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ANGLE AND MAIN GEARBOX

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