ENGINES OF THE THIRD MILLENNIUM - mfa.gov.ua · 2020. 11. 3. · Ukrainian Defence Industry Foundation date: May 5, 1945 ZAPOROZHYE MACHINE-BUILDING DESIGN BUREAU PROGRESS STATE ENTERPRISE

Zaporozhye - 2020

ENGINESENGINESOF THE THIRD MILLENNIUMOF THE THIRD MILLENNIUM

ENGINESENGINESOF THE THIRD MILLENNIUMOF THE THIRD MILLENNIUM

ZAPOROZHYEZAPOROZHYE

MACHINE-BUILDING DESIGN BUREAU PROGRESS STATE ENTERPRISEMACHINE-BUILDING DESIGN BUREAU PROGRESS STATE ENTERPRISE

NAMED AFTER ACADEMICIAN A.G. IVCHENKONAMED AFTER ACADEMICIAN A.G. IVCHENKO

ZAPOROZHYE

MACHINE-BUILDING DESIGN BUREAU PROGRESS STATE ENTERPRISE

NAMED AFTER ACADEMICIAN A.G. IVCHENKO

Ukrainian Defence Industry

®

®


Foundation date: May 5, 1945

ZAPOROZHYE MACHINE-BUILDING DESIGN

BUREAU PROGRESS STATE ENTERPRISE

NAMED AFTER ACADEMICIAN A.G. IVCHENKO

(IVCHENKO-PROGRESS SE)

FORM OF PROPERTY: - IVCHENKO-PROGRESS SE integrated in the State Concern «UKROBORONPROM»

SPHERE OF ACTIVITIES: - design, manufacture, certification, putting into series production, overhaul, test of aircraft and industrial gas turbine engines

CO-OPERATION: - more than 230 associated enterprises and suppliers

QUANTITYPRODUCTION: - Motor Sich JSC, Zaporozhye, Ukraine - Povazske Strojarne JSC, Povazska Bystrica, Slovak Republic

OPERATION: - 64 types of aircraft powered by engines and APUs of IVCHENKO-PROGRESS SE design are operated in more than 100 countries. - More than 80 thousand piston and gas turbine engines have been manufactured by series production plants. - Total operating time of the gas turbine engines in service is over 300 million hours.

HISTORY

c IVCHENKO-PROGRESS SE, 2020c

2

THE BASIC SPHERES OF ACTIVITIES

DESIGN MANUFACTURE

TEST, DEVELOPMENT AND CERTIFICATIONPUTTING IN SERIES PRODUCTION AND IMPROVEMENT

OF CONSUMER'S CHARACTERISTICS

OVERHAUL

®

3

IVCHENKO-PROGRESS SE, 2020


RECOGNITION

OF CERTIFICATION AUTHORITIES

®

State aviation administrationof Ukraine

Certificates No. UA.21J.0004, No. UA.145.0073,No. and others

UKRAINE

Interstate Aviation CommitteeAviation Register (ARMAK)

Certificates No. СПР-15, No. R-69and others

Bureau Veritas (France)

Certificates DSTY ISO 9001:2015, ISO 9001:2015 No. UА228430,BS EN 9001:2015, EN 9100:2016 No. UK 562016-01

European Aviation Safety Agency (Germany)

Certificate No. 216/2008,No. 1702/2003 Part 21A.23(b)2

4


1 8 2 8

BUREAU VERITASCertification

UA

ER

UB

V ERI T

AS

АРСД ТУ ВС ЕНОГ НЫЖЕ Й

М

ИОЦ ННА ЫИВ Й

А

ИТМ ЕО ТК

IN ET EE TIRS MT MA OTE C A NV IOIAT

MORE THAN 60 CERTIFICATES OF VARIOUS TYPES


®

TECHNICAL PRIORITIES

АI-20АI-25

D-36The 1- st in the USSR bypass engine

for regional aircraft, m›1The 1- st in the USSR three-shaft turbofan engine

with high bypass ratio for short-haul aircraft

The 1- st in the USSR turboprop engine with longservice life achived (over 20 000 hours)

D-18ТD-136

D-27Тhe most powerful in the world turboshaft engine

for heavy-lift helicoptersThe world first series-producen propfan

engine for medium tactical transport aircraft

The 1- st in the USSR turbofan with a thrustexceeding 20 tons for long-haul heavy transports

5



®


PISTON AND TURBOSHAFT ENGINES FOR LIGHTHELICOPTERS AND ULTRAHEAVY MILITARY

TRANSPORT HELICOPTERS

* - year of project launch- series production- manufacture, testing, final development, certification- design

Мi-1

Ка-15

Ка-18

Ка-26

G-4

B-5

B-10,-11

Мi-26Т

Мi-26

D-136 1971*

Yak-100

Ка-226

AI-450 1994*

АI-26/GR/GRF 1945*

АI-14V 1951*

AI-450M/M1 2006*

Мi-26/26Т

AI-136T2010*

Helicoptersof take off weight

up to 15 t.

TV3-117VMA-SBM1Vseries 5 (AI-130)

АI-450-2 2016*

Helicoptersof take offweight up

to 4 t.

Heavy-lifthelicopters

6


2013*

AI-136T-22013*

MSB-2 «Nadiya»

Mi-2М

Mi MSB-2

®

Аn-12

Аn-10

IL-18

IL-20, IL-22

IL-38

Аn-24

Аn-26

Аn-30

АI-20АSeries 1, 2, 3, 4,AI-20M Series 6

1955*

AI-24 Series 2, AI-24T, AI-24VT

1957*

Аn-70

Аn-140

D-27

1985*

TV3-117VMA-SBM1,TV3-117VMA-SBM1I

1996*

АI-450С-2

2010*

TURBOPROP ENGINES FOR REGIONALAND MILITARY TRANSPORT AIRCRAFT,SPECIAL PURPOSE AIRCRAFT AND GA


7



UAV «AKINCI»

AI-450С

2011*

DA50-JP7

For GAaircraft type

DART-450

AI-450СP

2014*

UTL-450

AI-450CP-2

2016*

TA-20

®

Yak-40

М-15

АI-25series 2, 2M

1962*

D-18Tseries 1, 3

1972* D-36 series 1, 1А, 2А, 3А, 4А

1967*

D-18T series 3M

2012*

Аn-124,Аn-124-100М-150

Аn-225

Аn-72

Yak-42

Аn-74

Аn-74ТК-300

Аn-124-100

Тu-334

Bе-200ChS

D-436Т1, D-436ТР

1991*

TURBOFAN ENGINES FOR REGIONAL,MILITARY TRANSPORT ANDMULTIPURPOSE AIRCRAFT

D-436-148FM2013*

An-148, -158

Аn-178

Аn-148, -158, -178

AI-282015*

D-436-1482002*


8



®

L-39

Yak-130

АI-25ТL,АI-25ТLK,АI-25ТLSh 1980*

1998*DV-2

AI-222-25,АI-322

1948*1970*

2005*

АI-322F

АI-14

Yak-18

Yak-12

PISTON, TURBOFAN ENGINES, INCLUDINGENGINES WITH AFTERBURNER, FORTRAINERS AND COMBAT TRAINERS

L-15A


L-59(39MS)

Yak-130D

L-15B

L-39М1

9



2014*

АI-322-30

2016*

АI-322-30F

For light combat aircraft

For light trainingaircraft and lightcombat aircraft

JL-8 (K-8W)

®

АI-8

Аn-8

Аn-10

Bе-12

Мi-6

АI-9

Mi-14

Mi-24

Yak-40

М-15

АI-9V,AI-9V series 1,

AI-9V-1

Мi-171

Мi-28

Мi-24 (Мi-35)

Мi-8МТV

Аn-140

АI9-3B

Аn-148

АI-450МS*

AUXILIARY POWER UNIT (APU)

1957*1964*

1971*

1994*

2002*


10



®

11



OUR ENGINES ARE OPERATEDIN MORE THAN 100 COUNTRIES OF THE WORLD

®АI-20А series 1, 2, 3, 4, AI-20К series 5, AI-20М series 6

IL-18

АI-20А, AI-20К series 5,AI-20М series 6

Аn-10

АI-20А, AI-20К series 5

IL-22

АI-20М series 6

IL-38

АI-20А, АI-20К series 5, АI-20М series 6I

Output shaft power, ehp ........ 4,000 ............ 4,250Equivalent specific fuel

, kg/h/ehp .......... 0.270 ............ 0.239consumption

АI-20K АI-20М

Takeoff, (S/L static; ISA)

Аn-12

АI-20К series 5, AI-20М series 6

IL-20

АI-20К series 5

13



®

Аn-32

Bе-12

АI-20D series 4, 5, 5Е

АI-20D series 4

АI-20D series 5, 5Е

Output shaft power, ehp ................................... 5,180 ..................... 5,180Equivalent specific fuel

, kg/h/ehp ..................................... 0.227 ..................... 0.227consumption

АI-20D

series 5, 5E

АI-20D

s eries 4 Takeoff, (S/L static; ISA)

Аn-8

АI-20D series 4

14



®

Аn-24

AI-24 series 2, AI-24T, AI-24VT

Аn-26

Аn-30

AI-24 series 2, AI-24T

AI-24VT

AI-24VT

Output shaft power, ehp ..................... 2,550 ................. 2,820 ............... 2,820Equivalent specific fuel

, kg/h/ehp ....................... 0.255 ................. 0.255 ............... 0.255consumption


15

АI-24TАI-24VTАI-24 series 2



®

АI-25 series 2, 2M

Thrust, kgf ............................................ 1,500, kg/h/kgf ........ 0.56Specific fuel consumption

АI-25


16

Yak-40М-15

АI-25 series 2М АI-25 series 2



®

L-39

JL-8 (K-8W)

АI-25ТL, АI-25ТLК, АI-25ТLSh

АI-25ТL

АI-25ТLК

АI-25ТLSh

L-39M1

Thrust, kgf ........................................... 1,720 ....................... 1,720 .............................. 1,850, kg/h/kgf ....... 0.58 ......................... 0.58 .................................. 0.6Specific fuel consumption

АI-25TL АI-25TLK АI-25TLSh


17



®

Аn-72

Yak-42D

D-36 series 1, 1А, 2А, 3А, 4А

D-36 series 1

D-36 series 1А

Аn-74

D-36 series 2А, 3АThrust, kgf .......................................... 6,500 ............... 6,500S , kg/h/kgf .... 0.365 ............... 0.358pecific fuel consumption

Takeoff, (S/L static; ISA), uninstalled

Аn-74ТК-300

D-36 series 4A

Thrust, kgf .......................................... 1,600 ............... 1,600 , kg/h/kgf ...... 0.65 ................. 0.63Specific fuel consumption

Max cruise, (H = 8 000 m, M = 0.75; ISA)

D-36

series 1, 1A, 2A, 3A

D-36

series 4A

18



®


Аn-225 «Mriya»

D-18Т series 1, 3, 3M

D-18Т series 1

D-18Т series 1, 3, 3M

D-18T series 1, 3, 3M


Аn-124, Аn-124-100

Thrust, kgf ..................................................................... 23 430,S , kg/h/kgf ..................... 0.345...0.362pecific fuel consumption

Thrust, kgf........................................................................ 4,860, kg/h/kgf ................................. 0.546Specific fuel consumption

19



®

D-136, D-136 series 1, AI-136T/T-2

Shaft power, hp .................................... 11,400 ........................ 12,200, kg/h/hp ........ 0.198 ................ 0.198/0.210Specific fuel consumption

D-136,

D-136 series 1

Max takeoff, (S/L static; ISA)

AI-136T/T-2

20



Мi-26/26T Heavy-lift helicopters

®

DV-2

L-59

21

Thrust, kgf ................................................... 2 200,, kg/h/kgf ............. 0.595Specific fuel consumption

DV-2




®

D-436Т1, D-436ТР, D-436-148

Тu-334-100

D-436Т1

Аn-148

D-436-148B

Bе-200ChS

D-436ТР

Аn-158

D-436-148 D-436-148D

22


D-436T1 D-436TP D-436-148B D-436-148D


Thrust, kgf ....................... 7,500 .............. 7,500 ..................... 6,570 ..................... 7 000,Specific fuel

, kg/h/kgf ....... 0.37 ................ 0.37 ..................... 0.351 ..................... 0.351consumption

Thrust, kgf ....................... 1,670 .............. 1,500 ..................... 1,560 ..................... 1,560Specific fuel

, kg/h/kgf ....... 0.61 ................ 0.61 ......................... 0.6 ......................... 0.6consumption



®TV3-117VМА-SBМ1

Аn-140

23

TV3-117VMA-SBM1


Max cruise, (H = 6 000 m, M = 0.5; ISA)Output shaft power, ehp .......................................................... 1,750E , kg/h/ehp ....................... 0.193quivalent specific fuel consumption

Output shaft power, ehp .......................................................... 2,500E , kg/h/ehp ....................... 0.206quivalent specific fuel consumption



®D-27

Аn-70

24

Output shaft power, ehp ............................................... 13,240E , kg/h/ehp .............. 0.180quivalent specific fuel consumption

D-27

oTakeoff, (S/L; t = t + 15 C, P = 730 mm Hg)amb ISA amb



®

AI-322

АI-322


Thrust, kgf ........................................................ 2,500S , kg/h/kgf .................... 0.64pecific fuel consumption

L-15A

25



®

26



Мi-2М

MSB-2 «Nadiya»

AI-450M (M1, M-P, M1-P)

АI-450М (M1, М-P, М1-P)

Takeoff, (S/L static; ISA)Power, hp ............................................. 400 .................. 465S , kg/h/hp .... 0.280 ............... 0.270pecific fuel consumption

AI-450M(M1, M2)

AI-450M-P(M1-P, M2-P)

Mi-2MSB

®

27



UAV «AKINCI»

АI-450С (CM, СD, СР)

АI-450C

(CM, СD, СР)

DA50-JP7

DART-450 UTL-450

Propeller shaft power, hp .......................... 400...495S , kg/h/hp ................. 0.277pecific fuel consumption


®

Helicopters with takeoff

weight of 3,000...3,300 kg

Power, hp ................................................ 630...800S , kg/h/hp ....... 0.270...260pecific fuel consumption

29



АI-450-2, AI-450С-2 (СР-2)

AI-450-2

АI-450-2 АI-450С-2 (CP-2)

AI-450C-2 (CP-2)

Propeller shaft power, hp ........................... 630...800S , kg/h/hp ......... 0.270...260pecific fuel consumption


For UAVs typeFor GA aircraft type

TA-20


®TV3-117VМА-SBМ1V series 5, TV3-117VМА-SBМ2, АI-130

ТV3-117VМА-SBМ1V series 5 Мi-8MSB

ТV3-117VМА-SBМ2

Аn-140Т

ТV3-117VМА-SBМ2

ТV3-117VМА-SBМ1V series 5, АI-130

Medium transporthelicopter

Max emergency,(H = 6 000 m, M = 0.5; ISA)Free turbine shaft power, hp .............................. 2,000S , kg/h/hp .................... 0.193pecific fuel consumption

Max emergency, (S/L static; ISA)Power, hp .......................................................... 3,200

Takeoff, (S/L static; ISA)Propeller shaft power, hp .................................... 2,800S , kg/h/hp ..................... 0.210pecific fuel consumption

Max emergency,(H = 6 000 m, M = 0.5; ISA)Propeller shaft power, hp .................................... 2,000S , kg/h/hp ..................... 0.193pecific fuel consumption

Max emergency, (S/L static; ISA)Propeller shaft power, hp ................................... 3,200

30

Takeoff, (S/L static; ISA)Power, hp .......................................................... 2,800S , kg/h/hp .................... 0.212pecific fuel consumption



Мi-17

АI-130

AI-322-40

AI-322-40AI-322-30

AI-322-30

®

AI-322-30, AI-322-40

Light trainers and combat aircraftRegional passenger,

business aircraft

Takeoff, (S/L static; ISA)Thrust, kgf ................... 3,000 ............ 3,755Specific fuel

, kg/h/kgf ..... 0.7 ............ 0.381consumption

31



®AI-322F, AI-322-30F

АI-322F

АI-322F

Light combat aircraft

Takeoff,(S/L static; ISA)

Takeoff,(S/L static; ISA)

Fullaugmented

power

Fullaugmented

power

AI-322-30F

Thrust, kgf ................... 2,920 ............... 4,900Specific fuel

, kg/h/kgf ... 0.71 ................. 1.92consumption

Thrust, kgf ................... 2,500 ............... 4,200Specific fuel

, kg/h/kgf ... 0.64 ................... 1.9consumption

AI-322-30F

L-15B

32



D-436-148FM

Takeoff / Emergency, (S/L static; ISA)

An-178

D-436-148FM

Max cruise,(H = 11 000 m, M = 0.75; ISA)

Thrust, kgf ......................................... 7,880 / 8,800S , kg/h/kgf ............... 0.371pecific fuel consumption

Trhust, kgf...................................................... 1,700S , kg/h/kgf ............... 0.605pecific fuel consumption

33



Аn-148, Аn-158 modifications

The engine is designed forinstallation on regional passenger

and medium transport aircraft

®

®

34



SHORT-LIFE TURBOJET ENGINE AI-350

Maximum power rating, (S/L static; ISA; s =1.0)in

Thrust, daN ............................................................................. 350

Specific fuel consumption, kg/(daN·h) .........................................1.16

(Н = 5 000 m; М = 0.8; ISА; s = 1.0)F F in

Thrust, daN ............................................................................. 385

Specific fuel consumption, kg/(daN·h) .........................................1.50

Parameters are presented at the maximum electric power takeoff from the built-in alternator - 5 kVA

The engine is designedfor application within UAV

®

35



AI-28

Advancedgeared fan engines

Specific fuel consumption by 15...20% lower thanthat of current engines in this thrust class

Regional passenger

and medium transport aircraft

Max takeoff, (S/L static; ISA)Thrust, kgf ...................................................................................... 10,300Ambient air temperature to which this thrust is

оmaintained invariable, С ................................................................... +30

Takeoff , (S/L static; ISA)Thrust, kgf ................................................................................... 9,400Ambient air temperature to which this thrust is


Max cruise, (H =11 000 m, М = 0.8, ISA)Thrust, kgf ........................................................................................ 1,860Specific fuel consumption, kg/h/kgf ................................................. 0.545Ambient air temperature to which this thrust is


An-178 modification

®AI-9500F

36



Tactical fighter

Takeoff

(S/L static; ISA; )s = 1,0in

Full augmented power

(S/L static; ISA; )s = 1,0in

Thrust, kgf ............................................................ 9,500 ...................................... 6,400S , kg/h/kgf ........................ 1.74 ........................................ 0.84pecific fuel consumption

®

Аn-8

Ве-12

Мі-6

Мі-6ААn-10

Мі-10

AI-8

AI-8

Generator terminals power, kW ........ 60

Fuel consumption, kg/h ................... 120

S/L static; ISA

38



®

Ка-52

Bleed airflow, kg/s ............... 0.38

Bleed air pressure, total, MPa, min ..................... 0.24

oBleed air temperature, С ..... 130

АІ-9

Yak-40

Ка-29

Ка-27

Ка-32

Ка-50

Ка-60

Мі-14

Мі-24

М-15

S/L static; ISA

AI-9

39



®

АІ-9V, AI-9V series 1,

AI-9V-1

Мі-8МТ (Мі-8АМТ)

Мі-172

Мі-8МТV

Мi-24 (Мi-35)

Мi-171

Мi-28

AI-9V, AI-9V series 1, AI-9V-1

S/L static; ISA

Aircraft electric system DC power, kW ........ 3

Bleed airflow, kg/s .................................... 0.4

Bleed air pressure, total, MPa, min ........ 0.29

Bleed air temperature, К .......................... 433

Мі-8 (Мі-17)

40



®

S/L static; ISA

Generator terminals power, kW ....................................... 40

Bleed airflow, kg/s, not less .......................................... 0.72

Bleed airflow pressure, absolute, МPa, not less ......... 0.368oBleed airflow temperature, С, not more ........................ 215

Fuel consumption, kg/h, not more .................................. 115

AI-450МS*

* Design is jointly developed by Motor Sich JSCand IVCHENKO-PROGRESS SE

APUs

Аn-140

AI9-3B

Аn-148

S/L static; ISA

Aircraft electric system AC power, kVA ........... 16

Bleed airflow, kg/s .......................................... 0.4

Bleed air pressure, total, MPa, not less ....... 0.32oBleed air temperature, С .............................. 260

АІ9-3B АI-450МS*

41



®

GAS-PUMPING UNIT (GPU)

АІ-336-2-8

Gas-pumping unit (GPU)

АI-336-1/2-10

АI-312

Rated power, kW ............... 4,200 .................. 6,300 ................... 6,300 ................ 8,000 .............. 10,000 ............. 10,000 .............. 12,000оflat rated up to t , C .......... + 35 .................... + 15 ..................... + 25 .................. + 15 .................. + 15 ................. + 15 .................. + 15amb

Free turbine rpm ................ 8,200 .................. 8,200 ................... 8,200 ................ 8,200 ................ 4,800 ............... 6,500 ................ 6,500Efficiency ............................. 26.5 ....................... 31 ........................ 31 .................. 31.8 ..................... 34 ..................... 34 .................... 37

D-336-1/2 АI-336-2-8 АI-336-1-10 АI-336-2-10

Developed on the basis of basic GTD variants with parameters, equipment, systems for power, gas and other industrial applications required for a Customer.

D-336-1/2-4 D-336-1T/2Т AI-312

D-336-1/2

D-336-1/2-4

D-336-1Т/2Т

43



®

GTD АІ-2500,

GTD АІ-3000

Rated power, kVA ................................... 4,000 ....................... 6,000Voltage, V .................................... 6,300/10,500 ........... 6,300/10,500Current frequency, Hz .............................. 50/60 ...................... 50/60Current ...................................................................... AC three-phase

POWER STATIONS

Modular

gas turbine

power station

Gas turbine power station

GTD АI-336E-1-4,

GTD АІ-336Е-1-6

GTPS АІ-2500, GTPS АІ-3000

MGTPS АI-4000,

MGTPS АI-6000

Rated power, kVA ..................................... 2,500 ........................ 3,000Voltage, V ..................................... 6,300/10,500 ............ 6,300/10,500Current frequency, Hz .............................. 50/60 ........................ 50/60Current ........................................................................ AC three-phase

AI-2500 AI-3000oup to t +15 Camb

AI-4000 AI-6000oup to t +15 Camb

oup to t +35 Camb

oup to t +15 Camb

44



®LOW-EMISSION COMBUSTIONCHAMBERS

D-336, АI-336 GAS TURBINE DRIVES

OF ALL MODIFIED VERSION S WITH LOW-EMISSION

COMBUSTION CHAMBERS

LOW-EMISSION COMBUSTION CHAMBERS

FOR INDUSTRIAL GAS TURBINE UNITS

OF VARIOUS POWER LEVELS BOTH NEW

AND TO BE UPDATED

Nitrogen oxide concentration

3NOx Ј 50 mg/Nm

Carbon monoxide concentration

3CO Ј 100 mg/Nm

under all power ratings without water supply

45



®

3 GPU capacity, thousand,Nm /24h ........ 420...2603Volumetric fuel gas flow rate, m /s .................. 0.2

Inlet pressure range, MPa (abs) ........... 0.4 ... 2.1Outlet pressure range, MPa (abs) ........ 3.1 ... 4.5

oInlet gas temperature, С ...................... -20 ...+40oOutlet gas temperature, C, not more .............. 80

3Volumetric gas-and-steam mixture flow rate, m /h ......... 15,000Gas-and-steam mixture oxygen content, % ......................... Ј 2

oGas-and-steam mixture temperature, С ............................. 100Fuel (kerosene) consumption, kg/h ..................................... 320

oWater flow rate at mixture cooling to 100 C, kg/h ............ 6,500

AI-45

Unit type Automotive unit with extensible arm-like pipeline and turntableTurntable rotation speed, rpm ............... Ј 1.5Arm-pipeline lifting (lowering)speed, m/sec ......................................... Ј 0.5Maximum arm-pipeline length, m .............. 16

AI-19GIG-А

SPECIAL EQUIPMENT

АІ-9VP

GAS-PUMPING UNIT

GPU-C-0,7/45-5 АI-45

АI-19GIG

INERT GAS GENERATOR

GAS TURBINE DRIVE (GTD)

АИ-25В-0,8, SUPERCHARGER

GPU-С-0,7/45-5 АI-45

Supercharger

46



AI-19GIG

AI-19GIG-А

MOBILE UNIT

2 Gas operating pressure, kg/cm ............ up to 30 ..... up to 12

FGPU gas pressure drop 2ratio, kg/cm less than 0.5 ..... less than 0.5 .............................

Purification grade:

- from solid particles larger than 40 µ ........... full ..... full

- from liquid fractions .................................... full ..... full

Gas flow rate, kg/h up to 2,500 ..... up to 1,200 ..........................

®

SPECIAL EQUIPMENT

FILTER SEDIMENT

TRAP

FREE TURBINE

MODULE

МSТ-198

CONTAINERIZED VARIANTCONTAINERIZED VARIANT

FILTER SEDIMENTTRAP

Free turbine power, MW ....................................... 20.0

Free turbine rotational speed, rpm ..................... 3,000

Turbine inlet gas temperature, K ........................... 9082Turbine inlet gas pressure, kg/cm 2.83.......................

Turbine inlet air flow, kg/s ..................................... 96.4

Turbine expansion ratio ........................................ 2.63

Efficiency .............................................................. 0.91

МSТ-198

Pressure ratio, max ................................................... 63Compressor power, m /h .................................. 50,000

Pressure ratio, not less .................................................... 103Steam flow rate, m /h (kg/s) .......................... 210,000 (0.16)

ТМ50

ТМ210

COMPRESSORS

OF ТМ50, ТМ210

UNITS

47



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ENGINES OF THE THIRD MILLENNIUM - mfa.gov.ua · 2020. 11. 3. · Ukrainian Defence Industry Foundation date: May 5, 1945 ZAPOROZHYE MACHINE-BUILDING DESIGN BUREAU PROGRESS STATE ENTERPRISE