B1 B2 C D E 8C(+reheat) F G 9B 9C 9K 9K50

(1968)-steel turbine housing-new turbine with air cooled blades-new exit vanes-weight savings

produced: 1020

ATAR 101 9K 9K50

year 1961 1968

thrust (lbf) 10900 11060(reheat) (15100) (15870)

rpm 8400 8400

TET (C°) 920 935(F°) 1690 1715

pressure ratio: 6.15 6.15

compressor stages: 9 9max. diameter (mm/in):1020 / 40.2

101 9K50

Dassault Mirage F.1

Mirage 50

ATAR 9K50

B1 B2 C D E 8C 8K50(+reheat) F G 9B 9C 9K 9K50

-9K50 without afterburner (1973)

produced: 111

ATAR 101 9K50 8K50

year 1968 1973

thrust (lbf) 11060 10800(reheat) (15870)

rpm 8400 8400

TET (C°) 935 926(F°) 1715 1700

pressure ratio: 6.15 6.12

compressor stages: 9 9max. diameter (mm/in):1020 / 40.2 1022

Dassault Super Etendard

Type built main application

A0-B2 50 OuraganC 140 Mystere IICD 370 Mystere IICF 32E 598 Etendard, VautourG 462 Super Mystere B2, Mirage III8C 176 Etendard IVM9B 419 Mirage IIIC9C 1671 Mirage IIIE, Mirage 59D 129K 248 Mirage IV9K50 1020 Mirage F.1, Mirage 508K50 111 Super Etendard

total 5309

1957: Now what?

Cooperation P&W

2-spool turbofan engines

TF-104 1964 Mirage IIIT testbedTF-106 1965 Mirage IIIT testbedTF-306 12,700 / 1966 Mirage F2

20,500 lbs 1967 Mirage G8

M53-P2

single spool turbofan 14,500 / 21,400 lbsmodular construction (12 modules)

M53 1970M53-P2 1981 1985 Mirage 2000

Dassault Mirage 2000

with Turbomeca:Larzac 04twin-spool turbofan 2960 lbs

1978 Alphajet

M88twin spool turbofan 11,250 / 16,900 lbs21 modules

1990 Dassault ACX / Rafale A

Dassault Rafale

with Rolls-Royce:Olympus 593twin spool turbojet 32,000 / 38,000 lbs

1976 Concorde

1968: project M56

goal: high performance engines >20,000 lbsfor mid range (pr 20)for long haul (pr 30)

1971: CFM formed (equal parts with GE)

GE: HP components, motor managementSNECMA: LP components, installation

CFM56-2 CFM56-3 CFM56-5A

24,000 lbs 23,500 lbs 25,000 lbs

197419771979 B707

DC8 Super 70 B373 A320DC9 etc. A321KC-135 A340E-3 etc.E-6 AEW

over 22,000 built (mid 2011)

CFM56-2

CFM56-5A

1948 1949 1950 1950 1951 1952 1953 1954 1955 1956 1957 1958 1961 1968 1973

Thrust

15,900 lb

4,850

10,800

SFC

0.95

1.35 lb/(lbf*hr)

Mass Air Flow101 lb/sec

160

2.5

4.2

Thrust/weight ratio

109-003

Atar V1

Atar 8CAtar E

M88-2

Dry thrust vs. mass air flow

Avon RA-29

J-52J-79-119

Atar 9K50

Spey Mk201

F100-P100M53-P2

R-11 F-300

J-57M-88-2

8000

9000

10000

11000

12000

13000

14000

15000

16000

50 60 70 80 90 100 110Mass air flow (kg/sec)

Specific thrust (thrust/airflow

0

10

20

30

40

50

60

70

80

90

100

M88-2 J-52 M53-P2 Atar9K50

J-79-119

F-100-P-100

AvonRA-29

J-57 R-11F300

SpeyMk201

Summary ATAR adventure

Compare B2 (1953)9K50/8K50 (1974)

dry thrust +93%mass air flow +46%compression ratio +40%max. diameter +15%weight +28%TET +11%

specific fuel consumpton -16%specific mass -32%specific mass 9C / B2 -35%

Summary ATAR adventure

•Long development•Small steps•Low risk•Long life?•Low specific fuel consumption

•Lower power than contemporaries•Late

Provided opportunity to start makingcommercial turbofans

Thank you