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1. O AIRBUS SA Fam‖ y to A319′A320′A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′A320′A321
TECHNICAL TRAINING MANυ AL
TP REV 6
ENGINE SYSTEM D/0
ENGINE CHARACTERISTICS
Thc Airbus A319,A320 and A321 aircrarts arc powcrcd by two
PヽVl100G― JM turbofan cngincs
This cnginc can producc a thnlst f10m 22000 1bs(10000 kg)t033000
lbs(14900 kg)dcpcnding On thc aircraft version sct by thc Data Storage
Unit(DSU)whiCh iS cOnncctcd to the ElcctrOnic Enginc Control(EEC)
Thc PW l100G― Jヽ4 is a● vin spo01 Ultra high bypass turbofan cngine
wih the Fan DHve Gear Systcm(FDGS)whiCh Cnablcs thc fan and thc
system provides engine control, engine monitoring and help for
maintenance and trouble shooting.
Page 68
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systcm consisting Ofthc EEC、vith●vo indcpcndcnt channcls
cfliciency.

2. SA Familyto A319′ A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
AiRBuS
A319′ A320′ A321
UNIT(DSu}
Copyright€d by United Technologies Corporation - Pran & Whitlney Oivision. All REhls Reserved
ENGINE CHARACTERISTICS― ENGINE CONTROL
UM72DlPWl100005̲003‑Engine System D′ 0(3) Page 69
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PWl127GJM 26 8 Kibs

3. A:RBUS SA Fam‖ y to A319′A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′A320′ A321
TECHNICAL TRAINING MANUAL
TP REV 6
ENGINE SYSTEM DiO
ENGINE MODULES
The engine rotor comprises ofa single stage fan rotor, J stage Lp
Compressor,8 stage HP Compressor,2 stage HP turbine and j stage Lp
turbine. The engine is built on a modular concept.
The different modules are:
- Fan rotor,
- Fan case.
- FDGS.
- Fan Intermediate Case (FlC),
- Low Pressure Compressor (LPC),
- Compressor Intermediate Case (CIC),
- High Pressure Compressor (HPC),
- Dimrser and combustor,
- High Pressure Turbine (HPT),
- Turbins Intennediatc Case (TIC),
- Low Pressure Turbine (LPT),
- Turbine Exhaust Case (TEC),
- Angle and Mdn Gear boxes.
Page 70
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OAiRBUS SA Fam‖ y to A3197A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
COMPRESSOR
lNTERMEDlATE
CASE(CIC)
LOW PRESSuRE
COMPRESSOR
(LPC)
TURBINE EXHAuST
CASE{TEC)
cOpylghted by United TechnoloOies Corporaion Pr3● &vVhiltney Dlvision Al R19hts Reserved
ENGINE MODULES
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Page 71
ANOLE CEARBOX{ACB)
AND MAIN GEARBOX(MCB)
HlGH PRESSuRE

5. O AIRBUS SA Fam‖ y tO A319′A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATiCES― ENGINES
A319′ A320′A321
TECHNICAL TRAINING MANUAL
TP REV 6
ENGINE SYSTEM D/O
ENGINf, MODULES (continued)
FAN ROTOR AND FAN CASE
The Fan rotor contributes to approximately 90% ofthe thrust.
The fan rotor comprises ofthe fan drive shaft, inlet cone and 20 wide
chord fan blades. The fan blades are made of aluminium alloy
honeycomb structure and reinforced by Titanium leading edges.
The fan rotational speeds being lower helps in reducing rotational
loads and bird strike fan damage.
The fan rotates in a clockwise direction as viewed from the aft looking
forward.
The inlet cone is made ofcomposite material and is anti-iced with a
continuous airflow from ofthe 2.5 compressor stage.
The fan case provides an annular path for the bypass air flow.
The case is made ofsingle piece composite material (Kevlar). lt holds
the outer edge of the Fan Exit Guide Vanes (FECV).
The inner walls behind the fan blade area are provided with acoustic
liners for noise reduction.
A rubberized strip along the fan blade area helps in minimizing the
gap and prevents contact between the blades and the case.
―
Page 72
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O AIRBU5 SA FamHyto A319′ A320′ A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
ACCOuSTIc TREATMENT
FAN CASE ASSEMBLY
cOpynghted by united Technolo9ies COrpOratlon Pratl&ヽ ■
hltney Oivision A‖ R10hts Reserved
ENGINE MODULES‐ DヽN ROTOR AND FAN CASE
UM72DlPVVl100005̲003‐ Eng ne System D′ 0(3) Page 73
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7. OAIRBuS
A319′ A320′ A321
TECHNICAL TRAININC MANUAL
SA Familyto A319′ A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
ENGINE SYSTEM D/O
ENGINE MODULES (continued)
FAN DRIVE GEAR SYSTEM (FDGS) AND FAN
INTERMEDIATE CASE
The FDGS allows the fan ro be driven by the LP shaft at a lower speed.
The FDGS is a reduction gear mechanism which comprises ofa central
sun gear and five planetary gears arranged like a star
It helps in reducing the fan rotating speed and permits the LPC to
rotate at a higher speed. This helps in improving engine performance
and efficiency.
The ratio ofthe LPC speed: fan speed is approximately 3: l.
The LPC rotates in the opposite direction ofthe fan rotor
The FIC supports the FDCS and the bearings No. I, 1.5 and 2.
It also supports the inner edge ofthe Fan Exit Guide Vanes (FEGVs)
and the support fairings.
It houses a single stage Variable Inlet Guide Vanes (VIGVs) which
direct the air to the LP Compressor at the correct angle.
The VIGV's are controlled by the EEC.
UM72DlPW,100G05̲003‑Eng ne System D′ 0(3) Page 74
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C AIRBuS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
STAR CEARS ROTATE A30UT THEIR AXES
RINC CEAR ROTATES
(OUTPUT TO THE FAN)
︲
Ｎ
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SUN GEAR ROTATES
oNPUT FROM LPT) FAN EXIT FAIRINC
(SPLITTER)
FAN DRIVE GEAR SYSTEM FAN INTERMED:ATE CASE
COpy子 9hled by united Technolo9ies Coゃ oral on‐ Pratl&VVhiltneソ Div s on Al Rights Reserved
ENGINE MODULES‐ FAN DRIVE GEAR SYSTEM(FDGS)AND FAN INTERMEDIArE CASE
UM72DlPVVl100005̲003‑Englne System D′ 0(3) Page 75
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9. r(t AiTRBUS SA Fami:y to A319′ A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES‐ ENGINES
A319′A320′ A321 TP REV 6
TECHNICAL TRAINING MANUAL
ENGINE SYSTEM D/O
ENGINE MODULES (continued)
LOW PRESSURE COMPRESSOR AND COMPRESSOR
INTERMEDIATE CASE
Thc LPC comprises of3 stages ofaxial flow compressor with
integrally bladed rotot stators and the case.
It is connected to the FDGS to the tionr and the Lp rurbine shaft
splines at the rear.
It rotates counter clockwise viewed fiom the rear.
It acts as a super charger to pressurize the air before it enters into the
HPC,
It houses the 2.5 stage bleed valve at thc rear which releases the air
during engine operation to prevent surge and stall conditions.
The fbrward engine mounts are mounted on the CIC.
The CIC tmnsmits the engine core airflow from the LpC to lhe HpC.
It supports the bearing No.3 and also provides the ports fbr the 2.5
stage bleed air flow to join the fan air flow.
Page 76
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C AlttBUS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAININC MANUAL
lST STACE STATOR LPC 2 5 BLEED VALNIE
LPC CASE
FIRE CONTAlNMENT RINC
THRuST LINK
MouNT
HPC INLET
CASE AND
VANE ASSEMBLY
lST STACE
(1日 R)
LOW PRESSURE COMPRESSOR
ENGINE MODULES‐ LOヽV PRESSU
COMPRESSOR:NTERMED:ATE CASE
Copyr ghted by unled■echnologies COrporatiOn Prall&ヽ Vhliney Division AI R10his ReseⅣ ed
RE COMPRESSOR AND COMPRESSORINTERMEDIATE CASE
UM72Dl PVVl100G05̲003‑Eng ne System D′ 0(3) Page 77
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11. O AIRBuS SA Fam‖ yto A319′ A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
TP REV 6
ENGINE SYSTEM D/O
ENGINE MODULES (continued)
HIGH PRESSURE COMPRESSOR ROTOR
The HPC comprises ofeight stages axial flow compressor and the
shaft which are driven by the HP turbine.
A single stage ofvariable Inlet Guide Vane (VIGV) and the first three
stages ofVariable Stator Vanes (VSVs) ofthe HPC stators ensure a
smooth entry ofair to the HPC. Each stage ofthe variable stators is
connected by the unison rings.
The VIGVs and VSV stator vanes are operated by the primary and
secondary actuators controlled by the EEC.
The HP Compressor supplies air from Stage 3 and stage 8 to the
aircraft systems.
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OAiRBUS SA Fami!y to A319′ A320′ A321 PWl100G・ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′A321
TECHNICAL TRAINING MANUAL
STACE l
HPC FRONT HuB
STACE l,2,3
VARlABLE STATOR
HPC VAR:ABLE
INLET Cu:DE
VANE(VlGV)
CASE
H!GH PRESSURE COMPRESSOR
Copyr ghted by united TechnoloOies CorpOrat on ‐
Pratt 3 Whiltney Division AI Rilhis Reserved
ENGINE MODULES― HlGH PRESSURE COMPRESSOR ROTOR
UM72D,PVV4100G05̲003‑Eng ne System D′ 0(3)
O,4/RBUS S/S 20r4 All rights rcseNed. Confidential and prcpielary document
Page 79
STATOR VANE

13. OA:RBUS SA Fam‖ y to A319′A320′A321 PWl100G‐ Tl+T2
70‐ STANDARD PRATICES― ENGINES
A319′A320′ A321 TP REV 6
TECHNICAL TRAINING
ENGINE SYSTEM D/0
ENGINE MODULES(continued)
DIFFUSERAND COMBuST10N CHAMBERASSEⅣ IBLY
Thc unit hOuscs thc difFtlsct the annular combustion chambcr and thc
turbinc nOzzlc asscmbly lt also providcs thc brackcts for mounting
the Main Gear BOx(MGB)
Thc dittuscr converts thc kinctic cncrgy ofthe air cOming out ofthc
HPC into prcssurc cncrgy bcfOrc itゝ fed into thc colllbuS6on chambcr
Thc annular cOmbusion chamber houscs 18 fllei nozzlcs(6 Simplcx
and 12 Duplcx)and 2 ignitcr plugs and supports cfFcctivc combus● On
ofthc aiプ ftlcl mixturc
Thc ncw tcchnology high cmcicncy dcsign ofthe combustion chambcr
alsO hclps in rcducing C02 and NOx cmissiOns
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OAiRBUS SA Fam‖ y to A319′A320′ A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
TURB:NE NOZZLE ASSEMBLY
FuEL NOZZLE(13)
DIFFuSER OUTER CASE
coMBusT:oN CHAMBER
OυTER LlNER
coMBusT,oN CHAMBER
INNER LINER
DIFFuSER
coMBusT:oN CHAMBER
pyr ghted by untted TechnoloOies COrpOralon ̲Pra &VVhittney Division A,R10his Reserved
ENGINE MODULES― DIFFUSER AND COMBUST10N CHAMBER ASSEMBLY
BRAKETS
UM72DlPW,400G05̲003‑Eng ne System D′ 0(3)
@ AIRBUS SAS 2014 All rights reserued. Confidential and prcpietary document.
Page 81
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15. $atneus SA Fam‖ y to A319/A320′ A321 PWl100C‐ Tl+T2
70‐ STANDARD PRATICES― ENGINES
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
TP REV 6
ENGINE SYSTEM D/O
ENGINE MODULES (continued)
HIGH PRESSURE AND LOW PRESSURE TURBINES
The HP Turbine is made of two stage axial flow turbine, two stage
stator and turbine case.
The HP turbine unit has splines which attaches it to the HP Compressor
shaft.
HP Turbine d ves the HP Compressor
Integrated in the IIPT assembly is the TIC which directs the HP
Turbine airflow to align with the LP Turbine. lt suppofis the n"4
bearing.
The LP Turbine module comprises ofthree stage rotor assembly, LP
rotor shaft. statorc and the turbine case.
It drives the LP Compressor and the FDGS.
The HP and LP turbine cases have Active Case Cooling (ACC) cooling
manifolds around to control blade tip clearance.
UM72DT口″￢
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00G06003‑Englne System D′ 0(3) Page 82
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qrr rlltirU5 SA Fam‖ y to A319′A320′ A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′A321
TECHNICAL TRAINING MANUAL
HIGH PRESSuRE TURB!NE
LOW PRESSURE TURBINE
cOpyrighted by united Technologies Cofporalon ‐
Pratt&Whittney DivisiOn AI Righis ReseⅣ ed
ENGNE MODULES― HIGH PRESSURE AND LOヽV PRESSURE TURBINES
UM72DlPWl100005̲003‐ Engino System D′ 0(3) Page 83
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17. OAIRBUS
A3197A320′A321
SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
ENGINE SYSTEM D/0
ENGINE MODULES(continued)
TURBINE EXHAUST CASE
Thc TEC pcnllits an cxit path for thc gas■ ow coming out ofthc
turbincs
lt supports thc rcar roner bcahngs 5 and 6
Thc TEC provides thc attachment point for thc rcar enginc mount
it houses four Exhaust Gas Ttlrbinc(EGT)thermOcOuplcs
UM72D,PWl100G05̲003‑Eng ne System D′ 0(3) Page 84
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'Vl All(EUS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
70‐ STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
SECONDARY REAR ENG:NE
MOuNTATTACHMENT POINT
PRlMARY REAR ENCiNE
MOUNT Aπ ACHMENT POINT
EGT PROBE BOSS(4)
N05 BEARlNG
(AIRFOIL CONTROL)
TURB!NE EXHAuST CASE
Copy,9hted by united Technolo9ies CO子 pOralon ‐
Pratl&VVhitlney o,vision AI Rllhis Reserved
ENGINE MODULES‐ TURBINE EXHAUST CASE
UM72D4PWl100G05̲003‑Eng ne System D′ 0(3) Page 85
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19. AIRBuS
A319′ A3201A321
SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
70‐ STANDARD PRATICES― ENGINES
TP REV 6
TRAINING
ENGINE SYSTEM D/O
ENGINE GEAR BOX
The Engine Gear Box (EGB) comprises of two units: the MGB and the
Angle Gear Box (AGB).
MGB is attached to the core engine at 4:00 and 9:00.
It provides the drive to the hydraulic pump, Fuel Pump, Inregrared Drive
Generator (lDG), Permanent Magnet Alternator (PMA) and de-oiler
A cranl( pad to tum the HP rotor is located on the RH front side ofthe
MGB, undemeath the Engine Driven Pump (EDP).
The Air Staner is mounted on the right side aft ofthe MGB. Dudng
engine start the drive is transmitted rhrough the MGB andACB to d ve
the HP Compressor
The AGB is located forward ofthe MCB in the core engine area.
The MGB is connected ro rhe AGB through a lay shaft.
TheAGB is connected to the HP rotor by bevel gears and the tower shaft.
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Page 86
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OAiRBUS
A319′ A320′ A321
TECHNICAL TRA,NING MANUAL
SA Fam‖ y to A319′A320′A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
PERMANENT MACNET ALTERNATOR
01L CONTROL MODULE
(OCM)
MAIN GEARBOX(MCB)
HYDRAULIC ENG!NE
DRIVEN PUMP(EDP)
AIR TURBINE STARTER
(ATS)
FuEL MANIFOLD (IF,C)
MA:N GEARBOX VV:TH ACCESSOR:ES
cOpylghted by unled Technologies COrpOrat,on Pratt&ヽ Vhittney Division AI Rights Reserved
ENGINE GEAR 30X
UM7201PWl100G05̲003‐ Engine System D′ 0(3) Page 87
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lNTECRATED FUEL
PUMP AND CONTROL
GENERATOR
(IDG)

21. OA[RBUS SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′ A321
TECHNICAL TRAINING MANuAL
TP REV 6
ENGINE SYSTEM D/O
AERODYNAMIC STATIONS AND BOROSCOPIC PORTS
Several boroscopic ports are provided for preliminary inspection ofthe
gas path without engine disassembly.
Each stage ofthe rotor, both compressors and turbines have boroscopic
ports located at different positions on the engine case.
Igniter plugs ports are used to inspect the combustion chamber liners,
firel nozzles and first stagc nozzle guide vanes.
The main aerodynamic stations are identified in the gas path. Sorne
stations have pressure and./or temperature sensors for engine monitoring.
UM72DlPWllllllC05 003‐ Englne System D/0(3) 。
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Page 88
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AIRttUS
A319′ A320′ A321
TECHNiCAL TRAINING MANUAL
SA Family to A319′ A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
BOROSCOPE PORTS
HPC‐ 1
LPC‐2
LPC 3
HPC 3
:,PCI
HPC‐ 3
11,C‐ 6
HPC‐ 7
HPC‐ 8
ALRODYNAMl(]S IlへT10NS AN D BOROSCOPIC PORTS
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Copyrghted by unted Technclo9tes COrpOra」 on ̲Patt&7Vh tiney Division AI R10い ls Reserved
HP,2 1cN TERS
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UM72D4PW4100005̲003‑Eng ne System D′ 0(3)
OA/RAUS SAS 2074 A rights reseN6d. Confidential and proprietary document-
Page 89

23. O AIRBuS SA Fam‖ y to A319′A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′ A321
TECHNICAL TRAININC MANUAL
TP REV 6
ENGINE SYSTEM D/O
ENCINE BEARINGS
The engine bearings provide reduce rolling friction and supports the rotor
axially and radially within the structure.
It bears the different loads ofthe rotating shaft.
There are five bearing companments containing a total ofseven bearing.
No. I and L5 are tapered roller bearing and are used to supporl the fan
rotor and FDGS.
No. 2 and 3 are ball bearings and suppon rhe front part ofLP and HP
rotor respectively.
No.4 is roller bearing and suppon the rear ofN2.
No.5 and 6 are roller bearing and support the rear ofNl rotor.
The bearing compartment are lubricated, cooled and cleaned by engine
oil.
Bearing compartments are sealed using carbon seals to prevent oil leakage.
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