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Aviation History
1965
1965 - 0049.PDF
FLIGHT International, 7 January 1965 AERO ENGINES 1965... Data for Representative Engines UNLESS otherwise stated, performance is based upon standard-day conditions, and the maximum power is the sea-level static figure. Airflow and pressure-ratio figures are for this condition. It is clearly impossible to adopt a common standard of quoting performance, but most major manufacturers give guaranteed-minimum figures, and these have been used wherever available. It is no easier to tar every engine with the same brush even in such superficially simple matters as giving a figure for its length or weight; but the values quoted are those provided by the manufacturers, and careful inspection shows that some firms are more honest than others in allowing tor the external dressing which a bare engine has to wear before it can be put into an airframe. The column headed TBO gives the maximum time between overhauls authorized for the engine; many operators may not yet have attained this life with the same powerplant. The column "Engine configuration" describes the basic geometrical layout: the numbers indicate how many stages there are of fan blading f, axial compression a, centrifugal compression e, turbine stages t, compressor-turbine stages ct, and power-turbine stages pt, and a plus-sign means that the portions so linked rotate together; the piston-engine configurations are simpler, 04, inj signifying four opposed direct-injection cylinders, R9,g,s meaning a nine-cylinder radial, geared and supercharged, turb being short for a turbosupercharger, I4L being an inverted four-in-line and 2 sir, two stroke. Designation Manufacturer's BMW 8026 BS Olympus 301 Olympus 320Olympus 593 B Orpheus 803 Viper 200 Viper 521 GE — CJ6I0 IHI JRIOO Mikulin AM-3M/RD-3MOKL TO-I Omnipol M70I Pratt & Whitney JT3C-*JT3C-26 JT4A-11 JT4A-29 JT8B-3 JTII JTI2A-6 JTI2A-2I Rolls-Royce Avon 200 Avon 301 RBI46R Avon 520 Avon 530 RBI 45 RBI62 SNECMA Mars Turbomeca Marbore 6 Military — B.OI.2I B.OI.22R— BS.Or.3 BS.V.II — J79-5B J79-IIA J79-I5 J85-5 — J3-7 — M209 — _ J57-20, 20A J75-P-I9W J52-8 J58 J60-3A R.A.24R 60 Series R.A.29/1.3 R.A.29/6 Atar 9C Atar 9K M-45B — Engine confi figuration Ic, It 6a, 7a, It, It — — 7a, It 7a, It 8a, It 17a, 3t 17a, 3t 17a, 3t 8a, 2t, ab 8a, 2t 8a, It 6a, It 8a, 2t Ic, ItIc, It 9a, 7a, It, 2c 9a, 7a, It, 2t, ab 8a, 7a, It, 2t 8a, 7a, It, 2t, ab 9a. 2t 9a, 2t, ab 15a, 2t, ab 16a, 2t, ab 16a, 3t 17a, 3t 9a, 2t, ab 6a, It 9a, 2c, ab 9a, 2t, ab Ic, It Length (in) 23.6 128 138.22 75.5 63.9 66.6 202.17 207.96 207.96 108.8 40.5 72.85 — 200 —81.38 136.77 220144.1 259.3 74.2 126 134.6 138 126 134 50 37 234 239.36 55.74 TABLE Height (in) — 44.5 50 38 27 28 — — — 36.53 — — — — 42 2426 — 24.84 Width (in) 14.95 44.5 _ 47.85 32.4 24.5 24.5 38 38.31 38.31 20 17.7 28.35 — 54 35.28 38.88 38.8843 43 30.15 21.9 21.9 41 44 39 39 15.526 40.2 40.1621.7 23.35 1: TURBOJETS Equipped weight (Ib) 84 _ 5,000? 850 580 628 3,635 3,530 3,685 559 381 915 — 5,500 728 4,234 4,7505,100 5,960 2,118 448 651 _ — 3,343 3,491 457275 3,025 3,153 — 370 (hr) — _ — — — — 4,000 —5,600 _ — — — 4,100 2.200 — — — — Max. s.l. static ratine Ib thr.; r.p.m.; s.f.c 101; 45.000; 1.05 20,000; —; — 33,000*; —; —32,500*; —; — 5,000; 10,000; 1.08 2,500; 13,800; 1.07 3,120; 13,800; 0.98 15,600; 7,460; — 15.800; 7,460; — 17,000; 7,685; — 3,850*; 16,500; — 2,850; 16,500; 0.99 3,085; 12,700; 1.055 3,153; —; 1.15 19,180; —; — 822; 22,000; 1.21,962; 15.400; — 13,500; 8,200; — 18,000*; 8,000: —17,500; 8,000; — 26,500*; —; — 9,300; —; — 30,000+*; —; —3,000; —; — 4,025*; —; — 14,370*; —; — 16,000*: —: — 10,250; 8,050; 0.786 12.725: 8,150; 0.802 3,650*; —; —4,409; —; — 14,110*; —; — 15,435*; —; —7,700*; —; 1.95 1,058; 21,500; 1.09 mass low (Ib sec); — — 84 44 52.8 167.9 167.9 167.9 44 44 — 278 —.37.25 180 180300 300 — —— — ; 173 185 —— — 159— 21.6 press- ratio — — 4.4 4.1 5.09 13 13 13 7 7 — 6.8 4.3 12.5 12.512 12 13 6.5 — — 9.1 10.3 —— — —16 3.84 Remarks Sailplanes. Augmenter increases, thrust to 1211b Vulcan B2 TSR2 SNECMA reheat. Concorde BACH. 126. G9I. Orpheus 805. Fuji TIA.70I, Gnat FI.703R, HF24Jet Provost; BACI45; Jindivik 3: MB326; Sokol GalebHSI25. Viper 525, PD808 BS8A F.I04G F4C T38. J85-I3. F5A/B Aero 1121. Lear Jet, HFB32Q, YAT 37n i*~TI \AT f\ I -jt U t VM 1 I 1 ^ FujiT-IBV/STOL TUI04A& B TS-llL-29 707-120, DC-8-10, JT3C-7, 720 F8U-2N707-320, DC-8-30 FI05 — YFI2-A, SR7IJetStar, T39, T-2B — Lightning F.I, T4. Without ab Scimitar, Sea Vixen, Variants inValiant Kl, Canberra PR9 and late HuntersLightning F3 and 5, Draken Avon 524. S25, 350, Comet 4, 4B 4C. 522, 526, Caravelle 1, IA. 527 (II,4001b), Caravelle 3 Caravelle 6 VJI0IC-X2Mirage Ill-V. G222, VAKI9IB, Do3t Mirage III Mirage III, IVDevelopment Super Magister, Paris II, III, CM 191 TABLE Hi TU RBOFANS Designation Manufacturer's Military Engine configuration .ength (in) Height Width (in) (in) Equip- ped weight (lbs) TBO (hr) Max s.l. static rating Ib total pres- by thrust; r.p.m.; s.f.c.; mass lure pass flow ratio;ratio (Ib/see); Remarks BS.S3 Pegasus BS.I00 DB 730/ZTL 6 GE CJ 805-23B CF 700 I.H.I. J3-F Kuznetsov NK8 Lycoming PLFIB-2 P & W JT3D-3 JT3D-5A JT8D-I JTFIOA-20 Rolls-Royce Conway 200 Conway 508, 509Conway 540 Conway 550 Medway RB.I4I Spey 505 Spey 506 Spey 511 Spey Junior RB.I72 RB.I78 SNECMA TFI06 Mars M45-AF Turbomeca Aubisquc Tourmalet BS.Pg.5 TF 37 TF33-5.9 TF33-7 TF30 R.Co 17 R.Co 12 R.Co 42 R.Co43D R.Sp.25 2f. 7a, 11, 2t, 4n 4a + Ic, 2ct, Ipt, If 17a, 3t, If 8a, 2t, If 8a, It, If If + 7a, Ic, It, It 2f + 6a, 7a, It, 3t 2f + 7a, 7a, It, 3t 2f + 4a, 7a, It, 3t 3f 7f, 9a, It, 2t 4f + 3a, 9a, 11, 2t 4f + 3a, 9a, It, 2t 4f, 12a, 2t, 2t 4f, 12a, 2t, 2t 5f, 12a, 2t, 2t 4f, 12a, 2t, 2t 3f + 3a, 6a, It, 2t 3f + 6a, 7a, 11, 3t, ab If, la + Ic, 2t 98.8 130.9 74 93.7 66.28 136.5 138 122.5 136136 154154 110 110 114.6 110 82 198 80.63 54 48 48 53 53 40 40 40 29.53 48 20.353.3 32.233.46 40.68 53 5344.5 4242 5050 37 37 37 37 31.8 KM 25.59 3,800 670 880 4,170 4,605 3,041 3,550 4,5425,001 5,101 2,200 2,288 2,312 2,023 1,331 3,357 640 1,600 3,200 6,700 1,200 600 15,500; —30,000*; — 1,345; —16,100; 7.310; 4,200; 3,748; 20,940; 5,220; 18,000; 0.56— ; 0.69 — ; 0.75 — ; 0.364 8,000; — 10,410:0.7359,966; 0.656 10,712; - 21,000; — ; —14,000; 11,000; — (9,500*; — ; — 20,600; 18,000; 20,370; 21,825; 17,300; 9,850; 10,410; 11,400; 8,740; 6,000; 25,000; 19,840*;6,600- 7,700;1,543; 32,500:0.60 5.500- — ; — 6,600; 12,490;12,530, 12,390; 0.560; 0.612 9,260; 14,500; ; 0.53 426 128 183.4 480 316 285 367 375 20T 208 206 230 49 12.5 16 14 14.8 15.8 16.8 16.9 19.1 16 6.9 1.54 1.9 6 1.42 I.I 0.3 0.6 0.6 1.03 1.08 1.0 1.5 P.I 127, Do31 With PCB front nozzles Development CV990 Mystere 20 Development IL-62 WFG 614 707-I20B, 720B, DC8-50, DC8-F. TF33-3 (JT3D-2), B52H, CI35B. JT3D-3B, 707- 320B, C CI4IA, Starlifter 727, 727C. Caravelle IOBIR, Sup Caravelle. Saab 37. JT8D-5 (12,0001b) DC-9 Fill A. B Victor B2 707-420, DC8-40 VCI0 Super VCI0 HS 681 Trident IC One-Eleven 200 One-Eleven 300, 400, Trident IE F-28 Mystere 30! Conway successor Mirage Ill-V. Developed from P& WJTFIO Development Saab 105 Development W/th reheat
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