Ài-450m-e ( -e, Ì m1 2 eivchenko-progress.com/wp-content/uploads/pdf/ai450-v2opt.pdf · the parts...

Designed to powermulti-purpose helicoptersDesigned to powermulti-purpose helicopters

Turboshaft gas turbine engines

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Turboshaft gas turbine engines

ÀI-450M ( 1, Ì2)ÀI-450M ( 1, Ì2)MMÀI-450M-E ( -E, Ì - )AI-450-2ÀI-450M-E ( -E, Ì - )AI-450-2

M1 2 EM1 2 E Ukrainian Defence Industry

1907 - Creation of Motor Sich JSC 1945 - Creation of SE Ivchenko-Progress

Sphere of activityDevelopment, production and overhaul of gas-turbine engines for civil and military aviation, industrial gas-turbine drives and power-generating plants, consumer goods.

Structure14

structural

units

located

in

different parts

of

Ukraine

as

well

as

in

China, India, UAE, Algeria

one structural unit located in Zaporozhye

Number of employees over 21 000 3 100

CORPORATION ‘NPO ‘A.IVCHENKO’

YEAR OF CORPORATION ESTABLISHMENT - 2007

®

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Ukrainian Defence Industry

ÀI-450 ENGINE FAMILY

N = 465 hpshaft

N = 630...800 hpprop

ÀI-450Ì (Ì1 , M2) Turboshaft

ÀI-450 Turboshaft

AI-450BP, AI-450BP-2 Turbofan

R = 400...560 kgf

ÀI-450-2 Turboshaft

N = 630...800 hp shaft

N = 400...495 hpprop

Nshaft= 400...465 hp

ÀI-450Ì-E (Ì E, M2-E) Turboshaft1-

N hpshaft= 530...550

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AI-450Ñ-2 (ÑÐ-2)Turboprop

À I-450C Turboprop(CM, ÑD, ÑÐ)


POSSIBLE APPLICATION OF AI-450 ENGINE AND ITS MODIFIED VERSIONS

ÀI-450-2

Helicopters with takeoff weight of 3000...3300 kg

Perspective helicopters

Ìi-2Ì, MSB-2

ÀI-450M1, ?I-450M2, ?I-450? 1-Å, ?I-450? 2-Å

ÀI-450Ì, -Å?I-450?

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AI-450M

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AI-450Ì1

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AI-450M (Ì1, M2), AI-450M-P (? 1-P, M2-P) MAIN DATA

S/L static, ISA; uninstalled

- power, hp- specific fuel consumption, kg/h/hp


- width, mm- height, mm- length, mm- weight, dry, kg ( accord Ò 17106-79 )

Takeoff

cruise

Dimensions and weight

Max

in ance with GOS State Standart

4000.280

2850.320

534648

1115115

4650.270

3000.312

Engine models

ÀI-450Ì (Ì1, Ì2) ÀI-450Ì-P (Ì1-P, Ì2-P)

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PERFORMANCES/L static, ISA

Sp

ec

ific

fu

el

co

ns

um

pti

on

, k

g/h

/hp

Propeller shaft power , hp

0.25

0.30

0.35

0.40

0.45

150 200 250 300 350 400 450 500

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Takeoff

oEngine inlet air temperature, C

Sh

aft

po

wer,

hp

PERFORMANCE

250

300

350

400

450

500

-60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

S/L, ISA

H = 3000 m, ? = 70.1 kP?amb

? =0 ?I-450? (? 1-P, Ì2-P)

? =0 ?I-450? (? 1, Ì2)

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200

250

300

350

400

-60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

ContiniousPERFORMANCE

Sh

aft

po

wer,

hp


S/L, ISA

H = 3000 m, ? = 70.1 kP?amb

H = 3000 m, ? = 70.1 kP?amb

? =0 ?I-450? (? 1-P, Ì2-P)

? =0 ?I-450? (? 1, Ì2)

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70

80

90

100

110

120

130

-60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

Takeoff


PERFORMANCE

Fu

el

co

ns

um

pti

on

, k

g/h

S/L, ISA

H = 3000 m, ? = 70.1 kP?amb ? =0 ?I-450? (? 1-P, Ì2-P)

? =0 ?I-450? (? 1, Ì2)

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PERFORMANCE

60

70

80

90

100

110

-60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

Fu

el

co

ns

um

pti

on

, k

g/h

S/L, ISA

H = 3000 m, ? = 70.1 kP?amb

? =0 ?I-450? (? 1-P, Ì2-P)

? =0 ?I-450? (? 1, Ì2)

Continious

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AI-450M-E (Ì1-E, M2-E) MAIN DATA

S/L static, ISA; uninstalled



- width, mm- height, mm- length, mm- weight, dry, kg ( accord

Takeoff

cruise

Dimensions and weight

Max

in ance with Ò 17106-79 ) GOS State Standart

5500.273

4000.310

534648

1115115

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AI-450M (M-P, M-E) LONGITUDINAL SECTION VIEW

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AI-450M1(M1-P, M1-E) LONGITUDINAL SECTION VIEW

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DESIGN FEATURESThe ÀI-450Ì urboshaft engines

The engine consists of three modules:

w

w

w

r

Compressor

Combustion chamber

Compressor turbine

Free turbine

The engine control system

( t

Reduction gea

Ì1, Ì2, M1-E, M2-E) has a two-rotor design consisting of a gas generator rotor and free turbine rotor.

The free turbine transmits power to the reduction gear, arranged in front of the engine, through the shaft passing inside the gas generator rotor shaft.

Each rotor is mounted on two bearing supports built in the engine stator. To obtain the required engine vibration characteristics the gas generator rotor front bearing support and free turbine rear rotor bearing support are carried on elastic-oil dampers.

Reduction gear with accessory gearbox built in the same casing;

Gas generator containing inlet section, compressor, combustion chamber and compressor turbine;

Free turbine with its shaft.

is of two-stage design non-axial configuration with a gear ratio of 6.5:1. Axial force arising in the running block helical gear is transmitted to the torquemeter pistons. The driven and non-driven accessories are mounted on the reduction gear and accessory gearbox casing.

is of annular type, return-flow design with a low NOx emission level. To reduce the engine length the î

combustion chamber flow section is turned by 180 .

The engine-to-helicopter attachment is of two-planar type: in front plane by two horizontal trunnions mounted on the reduction gear casing, and in rear plane by two eye-lugs in joint between the combustion chamber casing and jet nozzle.

The materials of parts and special coatings enable the engine to be operated under all climatic conditions.

, which provides two variants of adjustment by power under the basic engine performance ratings, is electronic, double-channel with the added hydromechanical redundant channel. The engine operation monitoring and diagnostics are carried out by means of airborne and ground monitoring equipment in accordance with parameters transferred by engine sensors and indicators.

with

The parts of the AI-450M (M-E) and AI-450M1 (M1-E) reduction gears are completely unified, and on AI-450Ì2 (M2-E) engine the reduction gearbox is unified with the baseline AI-450 engine .

is of single-stage design containing a high-pressure centrifugal wheel, radial vaned diffuser and axial stator blades. The compressor front casing is the engine basic load-carrying structure where the gas generator rotor front bearing support is arranged.

is of a supersonic single-stage design with cooled nozzle vanes and rotor blades made of heat-resistant alloy.

is of axial, single-stage design, uncooled.

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AI-450-2 ENGINE

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AI-450-2 MAIN DATA

Length, mm ………………………………….......................................…........1149Width, mm ………………………………….......................................…..........520Height mm ………………………………….......................................….........567Weight, dry according to ...125

Dimensions and weight.

.., ( , kg, not more GOS State StandartÒ 17106-79 )

2.5 min OEI rate

min OEI rate

, S/L static; ISÀ

30 S/L static; ISÀ

Takeoff, S/L static; ISÀ

Ìax cruise, S/L static; ISÀ

- output shaft power, hp, not less ……………………………….....................750+30 Ñ)

,- output shaft power, hp, not less ……………………………….....................660

+30 Ñ)



- specific fuel consumption, kg/h/kgf…………………………...………...........0.294

(flat rated up to t =amb




o

o

o

o

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CHARACTERISTICSS

pecif

ic f

uel co

nsu

mp

tio

n, kg

/h/h

p

S/L static, ISA according to GOSÒ 4401-81 State Standart

Output shaft power, hp

CN

0,20

0,25

0,30

0,35

0,40

0,45

0,50

0,55

0,60

0,65

0,70

0,75

0,80

50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

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500

550

600

650

700

750

-50 -40 -30 -20 -10 0 10 20 30 40 50

îAmbient air temperature, Ñ

Takeoff

30-minute emergency

Ou

tpu

t sh

aft

po

wer,

hpCHARACTERISTICS

2.5-minute emergencyNshaft

S/L static, ISA

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500

550

600

650

700

750

0 500 1000 1500 2000 2500 3000 3500 4000

Altitude, m

2.5-minute emergency

Takeoff

30-minute emergency

Ou

tpu

t sh

aft

po

wer,

hp

CHARACTERISTICS

Nshaft

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Static, ISA according to GOSÒ 4401-81 State Standart

AI-450-2 DESIGN FEATURESThe AI-450-2 is a turboshaft engine with a free single-stage turbine

the samea single single

driving the output shaft via the reduction gear combined in with the accessory gearbox casing. Driving of auxiliary accessories is carried out from the gas generator rotor. The enginegas-generator consists of -stage centrifugal compressor, reverse-flow annular combustion chamber, -stage compressor turbine.

The gas generator rotor is mounted on two bearing supports: front ball bearing support and rear roller bearing support. For decreasing the total level of vibrations and stresses a damper with elastic ring is introduced in the front bearing support. The free-turbine rotor is mounted on two supports: front support with combination of roller bearing and ball bearing for taking axial loads, and rear support with roller bearing. An elastic oil damper is used in the free turbine rotor rear bearing support.

The engine consists of three modules:

r

Compressor

Combustion chamber

Compressor turbine

Free turbine

The engine control system

w Reduction gear with accessory gearbox built in the same casing;

w Gas generator containing inlet section, compressor, combustion chamber and compressor turbine;

w Free turbine with its shaft.

is of two-stage design non-axial configuration with a gear ratio of 5 8:1. The driven and undriven accessories (starter-generator, fuel-metering unit, oil pump block and centrifugal breather) are fitted to the reduction gearbox casing .

is of annular type, return-flow design with a low NOx emission level. To reduce the engine length the îcombustion chamber flow section is turned by 180 .

The engine-to-helicopter attachment is of two-planar type: in front plane by two horizontal trunnions mounted on the reduction gear casing, and in rear plane by two eye-lugs in joint between the combustion chamber casing and jet nozzle.

The materials of parts and special coatings enable the engine to be operated under all climatic conditions.

is electronic, two-channel with the additional redundant hydro-mechanical channel. The engine operation monitoring and diagnostics are carried out by means of airborne and ground monitoring equipment in accordance with parameters transferred by engine sensors and indicators.

Reduction gea with .

is of single-stage design containing a high-pressure centrifugal wheel, radial vaned diffuser and axial stator blades. The compressor front casing is the engine basic load-carrying structure where the gas generator rotor front bearing support is arranged.

is of a supersonic single-stage design with cooled nozzle vanes and rotor blades made of heat-resistant alloy.

is of axial, single-stage design, uncooled.

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01 - Gas generator02 - Free turbine rotor03 - Outlet diffuser04 - Reduction gear

04 01 02 03

AI-450M MODULES

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AI-450M (M-P, M-E) DIMENSIONS

Engine attachment front plane ( AP)

Engine attachment rear plane (RAP)

F

450.2 -3.5

À

RAP

FAP

1115

255174.1

534

80

19 from FAP

+1.5

À230.5

± 0

.3

397

648

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AI-450Ì1 (M1-P, M1-E) DIMENSIONS



F

1115

450.2 174.1 80+1.5- 3.5

534

255

397

648

À

À

À - À

23

0.5

± 0

.3

243 from FAP

FAP

RAP

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front rigging bracket

left-side view of engine

FAP

RAP

rear mounting brackets

rear rigging points

AI-450M (M-E) AI-450M1 (M1-E)/ MOUNTING AND RIGGING DIAGRAM



F

450.2

80

200

î40

38

6

À

À

B - B

À - ÀB

B

î40

200

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AI-450Ì2 (M E) DIMENSIONS2-



F

1103

FAP RAP

541.5310

584

554

260

6

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Ñ

B

RAP

?I-450Ì2 MOUNTING AND RIGGING DIAGRAM

mounting

Starboard engine mounting diagram Port engine mounting diagram

mounting

mountingmounting

mounting

Engine left-side view

À

À B

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558FAP


AI-450-2 DIMENSIONS

Engine attachment plane ( AP)

Engine rear attachment plane (RAP)

front F

F P A R PA

Shaft axle is a spring

125

1149

202618.25

307

R260

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AI-450-2 MOUNTING AND RIGGING DIAGRAM

F P ARAP

618.25A

A

B

B

6

30

14

Â

M6-6e

45°

190

ØÌ8 ÞÒ

C-C

C

C

B-B? 52

Â

45°

250

À-À

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Îæèäàåìûå ïîêàçàòåëè áåçîòêàçíîñòè íà ýòàïå ìàññîâîé ýêñïëóàòàöèè:- íàðàáîòêà íà âûêëþ÷åíèå äâèãàòåëÿ â ïîëåòå- íàðàáîòêà íà äîñðî÷íûé ñúåì äâèãàòåëÿ

Ðåñóðñû:- ýêñïëóàòàöèîííûé - íàçíà÷åííûé

AI-450M, AI-450M-E, AI-450-2 RELIABILITY

Design of trouble-free operation in service:

·

·

indices

mean time between engine shutdown

un d

T >50000 h

T >10000 h

in flight fl shtd

unschmean time between schedule engine removal

Service life:

·

·

stto 1 overhaul and T.B.O.

assigned

3000 h12000 h

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SAFE OPERATION SUPPORT

The AI-450-2 safe operation is ensured by:

1.

2.

3.

AI-450M-E (? 1-E, M2-E),

Certification of compliance with AP-33 (FAR-33) Aviation Rules for power jets.

Airworthiness support within overall engine life cycle.

Aftersales support including:

- maintenance within guaranteed period;

- post-

- logistical support;

- flight and technical personnel training;

- development of operation and technical documents and their application;

- engineering support;

- informational support;

- organizational activities.

guaranteed maintenance;

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The control of all engine performance ratings under all conditions in operation is supported by a double-channel electronic digital control as combined with the engine sensors and actuators, and also by helicopter airborne systems. The functions of the automatic control system (ACS) are performed in the amount the same for both variants of power adjustment under the basic performance ratings of the engine.

1. Engine digital control (ÐÄÖ-450Ì) with included self-contained functional modules: - free turbine automatic protection (ÀÇÑÒ); - vibration monitoring (ÌÊÂ); - parameter monitoring (ÌÊÏ); 2. Fuel-metering pump (ÍÄ-450Ì) 3. rotational speed governor (ÐÎ450Ì) 4. Sensors and indicators.

- control of the engine accessories for conducting the engine start, cold cranking and false start (preservation

and depreservation);- automatic support of a free turbine rotational speed (with the basic and redundant hydromechanical ACMS); - control of fuel consumption under stable and variable performance ratings of the engine; - limitation and protection of engine against exceeding of accepted parameters; - protection against overspeeding by using an independent automatic protection system; - synchronization of the engine power in a twin-engined powerplant under stable performance ratings; - engine shutdown; - information interaction with the engine systems and helicopter airborne systems; - monitoring of the ACMS integral parts and interacting items with differentiation of malfunctions detected; - automatic reconfiguration of the ACMS according to the results of malfunctions detected (including a transfer

to a redundant hydromechanical ACMS); - record of information in the ÐÄÖ-450Ì nonvolatile internal recorder about malfunctions detected; - introduction and storage of operational adjustments and individual features of the engine.

The engine automatic control and monitoring system (ACMS).

ACMS composition:

The ACMS main functions:

AUTOMATIC CONTROL SYSTEM

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Control channel 1

Rotational speed governorÐÎ450Ì

Sensors

Airborne equipment

Parameter monitoring

(ÌÊÏ)

Cockpit instrument

panel

ACMS STRUCTURAL DIAGRAM

Fuel-meteringpump

(ÍÄ-450M)

Free turbine automatic

protection (ÀÇÑÒ)

Vibrationmonitoring

module (ÌÊÂ)

Digital engine control (ÐÄÖ-450M)

Control channel 2

Indicators

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Our engines are operated more than 100 countries of the world in

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2, Ukraine

Ivanova Str., 69068, Zaporozhye, Tel.: (+38 0612) 65-03-27; Fax (+38 0612) 12-89-22, [email protected]

13.06.2018 Dyachuk

Zaporozhye Machine-Building Design BureauProgress State Enterprise named after Àcademician A.G. Ivchenko

MOTOR SICH JSC

15, Motorobudivelnykiv av.,Zaporozhye, 69068,UkraineTel:Fax:

+38 (061) 720-44-09+38 (061) 720-50-00

E-mail: [email protected] www.motorsich.com

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Ài-450m-e ( -e, Ì m1 2 eivchenko-progress.com/wp-content/uploads/pdf/ai450-v2opt.pdf · the parts...

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