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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