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Aviation History
1962
1962 - 1027.PDF
FLIGHT International, 28 June 1962 1025 AERO ENGINES 1962 . . . Data for Representative Engines UNLE88 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 cendition. It is clearly impossible to adopt a common standard of quoting performance, but most major manufacturers give guarantsed-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 for 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 stage* there are of fan blading f, axial compression a, centrifugal compression c, 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 turbosupereharger and I4L being an inverted four-in-line. TABLE 1: TURBOJETS Designation Manufacturer BMW 8026 BS Gyion Junior 2 Gyron Junior 10 Olympus 12 Olympus 7 Olympus 21 Orpheus 3 Orpheus 4 Viper 11 Viper 500 Continental 352-5A 354-7A CJ69-1400 Fiat 4004.000 GECJ610-1 CJ80S-3B \ippon-miJ3-3 P&WAJT3C-2 JT3C4 JT3C-7 JT3C-12 JT3C-26 JT4A-9 JT4A-11 JT4A-29 JT8A JT12A-6 JT12A-21 R.R.Aron24R Aron2»/l Avon 533R RB.108 RB.146R SNECMA Atar09B3 Atar09K Turb. Marbore 2 Marbore 6 Military — Mk 101 — Mkl04 Mk201 Mk301 Mk803 MklOl Mk22 "~~ J69-25 J69-29 — — — — J79-5B J79-11A J79-15 J85-5 J85-7 J93-5 — J57-43W — — — J57-20 — — J75-19W J52-6 J60 — Mk210 Mk350 — — Avon 301 — — — Engine configuration lc, It 8a, 2t 8a,2t,ab 7a, 8a, It, It 5a, 7a, It, It 6a.7a.lt.lt 7a, It 7a, It 7a, It 8a, It lc.lt la + lc. It la + lc, It lc.lt 8a, 2t 17a, 3t 17a, 3t 17a, 3t 17a, 3t 8a, 2t, ab 8a, 21 — 8a, It 9a, 7a, It, 2t 9a, 7a, It, 2t 9a, 7a, It, 2t 9a. 7a, It, 2t 9a, 7a, It, 2t, ab 8a, 7a, It, 2t 8a, 7a, It, 2t 8a, 7a, It, 2t, ab 9a, 2t 9a,2t,ab 15a, 21, ab 16a, 3t 17a, 3t 8a, 2t 16a,2t,ab 9a,2t, ab 9a, 2t, ab 2c, It 2c, It Length (in) 23.6 121 191 132 126.5 131 75.5 77.5 63.9 66.6 50 46.25 44.8 36.2 40 109.56 202.17 20756 20736 108.8 39.3 — 72.85 167.33 138.64 136.77 138 220 144.1 144.1 259.3 74.2 126 126 126 134 46.5 145 247.04 233.96 37.2 37.2 Diam. (in) 14.96 32.3 32.3 40 41.75 44.5 32.4 32.4 24.5 24.5 24.9 22.36 22.3 22.44 17.7 31.6 38 38.31 38.31 20.2 17.5 — 28.35 38.88 38.88 38.88 38.88 38.88 43 43 43 21.9 21.9 41.5 39 39 20.8 41.5 40.16 40.16 14.4 14.4 Weight 84 2,100 3,100 3,815 4,000 — 850 900 580 628 364 335 370 209 355 2,815 3,635 3,485 3,630 555 327.5 .— 926 3,840 4,234 3,495 3,550 4,750 5,050 5,100 5,960 436 651 — 3,343 3,491 269 — 2,939 3,153 356 363 Air flow Ob/sec) — — — — — 84 82 44 52.8 19.8 28.3 — 10.4 44 167.9 167.9 167.9 167.9 42.5 42.5 300+ .— 180 180 180 180 180 300 300 300 — — — 173 185 38.8 — 149.9 — 17.7 21.7 Press ratio 6 7 10.9 10.8 — 4.4 — — 5.09 — — 5.1 4 7 13 13 13 13 7 6.5 8 — 12.5 12.S 12.5 12.5 12.5 12 12 12 6.5 6.5 — 9.08 10.3 5.25 — 5.5 — 3.85 3.84 Max. power lb thrust; r.p.m. 101 ;45,000 7,100; 14,000*; 13,500; 17,000; 20,000; 5,000; 10,000 4,230; 2,500; 3,000; 1,025:21,730 1,700; 22,000 1,400; 21,000 595; 25,000 2,850; 16,500 11.650;7,460 15,600; 7,460 15,800; 7,460 17,000; 7,685 3,850*; 16,500 2,450; 30,000*; 2,645; 13,750; 8,000 13,500; 8.000 12,000; 8,000 13,000; 8,000 18,000*; 8,000 16,800; 8,000 17,500; 8,000 26,500*; 8,500; 3,000; 4,025*; 14,430*; 10,250; 8,050 12,600; 8,150 2,200; 17,500 16,600*; 13,230*; 8,400 15,435t; 880; 22,600 1,060; 21,500 Typical cruise power Feet; knots; thrust; s.f.c; r.p.m. _ 20,000; 500; 1,190; 1.25; 36,000; 420; 875; 1.14 45,000; 600; 205; 1.24; 20,000 45,000; 600; 330; 1.315; 20.130 25,000; 400; 403; 1.128; 19,800 — 25,000; 525; 4,300; 0.97; 7,460 — — — 35,000; 585; 1,180; 1.54; 16,500 35,000; 585; 580; 1.17; 14,850 65,000; 1,800 — — 20.000; 565; 4,850; 0.963 30,000; 565; 4,100; 0.91 — — — — — — — 35,000; 1,180; 3,650; — 35,000; 475; 2,420; 0.908 25,000; 425; 4,630; 0.932 — — —. 9,900: 290; 353; 1.365 9,900; 470; SSO; 1.41 TBO Main applications (hi) — 1,800 — — — 100 2,600 1,800 1,200 — 2,400 — — — — — — 3,200 1,200 — — — — Sailplanes Buccaneer S.l T.188 Vulcan B.l Vulcan B.2 Vulcan G.91 GnatT.l Jet Provost 4, JindivikJ3 D.H. 125.PD-808 T-37B Target drones Aero 1121, SAAC-23 Convair 880M B-58 F-104G F4H.F-110.A3J T-38 GAM-72 XB-70 Tl-B B-S2G 707-120, DC-8-10 707-120,720, DC-8-10 720 F8U-2N DC-8-20/30,707-320 DC-8-30,707-320 F-105 A2F.A4D-5 JetStar,T-39 — Lightning Comet4,4B,4C Caravelle SC.1, Balzac Lightning 3, Saab-35F Mirage me Mirage m, TV Magister, Paris 1 — Paris 2, 3, CM.191 * With reheat; t with reheat at Mach numbers above 1.0, TABLE 21 TURBOFANS Designation Manufacturer 33.53 Pegasus BS.75 GECF700-2B CJ805-23B P&WAJT3D-1 JT3D-2 JT3D-3 JT3D-8A JT3D-12A JT8D-1 JTF10A-6 JTF10A-20 R-R Conway 12 Conway 42 Conway 43 SpeyS05 SpeyS06 <-NECMA TF-106 Turb. Aubisaue Military BSPg.5 TF33-3 TF33-5 TF33 TF30 Engine configuration 2f.7a.lt.2t 3f, 10a,2t,2t 8a.2t.lf 17a, 3t, If 2f + 6a, 7a, It, 3t 2f+6a,7a,lt,3t 2f + 6a, 7a, It, 3t 2f + 7a,7a,lt,3t 3f + 6a, 7a, It, 3t 2f+4a,7a,lt,3t 2f+6a,7a,lt,4t 3f 7f.9a.lt.2t 4f+3a,9a,lt,2t 4f +3a,9a, lt,2t 4f, 12a.2t.2t 4f, 12a.2t.2t 3f+6a.7a,lt,3t,ab If, la + lc2t By pass ratio 1.75 IS 1.56 1.42 1.42 1.42 iTs 1.1 0.3 0.6 0.6 1.03 1.08 1.5 Length (in) 98.8 89 65 139 136.32 136.5 136.5 138 147 122.5 125.2 136 154 154 110 110 198 81.2 Diam. (in) 48 34.4 34 53 53 53 53 53 54 44.5 39.2 42~ 51 51 37 37 50.4 22.2 Weight 0» 1,610 640 3,730 4,090 3,900 4,170 4,490 2^94 2,390 3,550 4,542 5,001 5,101 2,200 2^57 3,357 Airflow (lb/sec) Total 196 130 4173 480 480 480 305 280 367 363 203 208 230 49 Hot 72 44 167.9 198 198 198 146 216 227 227 100 100 92 Press, ratio 13 7 13 12.5 12.5 12.5 15.5 14 14.8 15.8 16.8 16.9 16 6.9 Max. power lb thrust; r.p.m. 18,400; 7,550; 8,900 4,200; 16,500 16,100; 7,310 17,000; 8,000 17,000; 8,000 18,000; 8,000 21,000; 22,000; 14,000; 11,000 10,500; 19,500*; 17,500; 9,980 20,370; 9,966 21,825; 10,172 9,850; 12,490 10,410; 12,530 19,680*; 14,500 1,550; 32,500 Typical cruise power Feet; knots; thrust; s.f.c. 25,000; 460; 2,530; 0.783 25,000; 525; 5,100; 0.83 30,000; 525; 3,150; 0.8 35,000; 460; 3,230; 0.778 30,000; 525; 3,500; 0.785 35,000; 460; 3.580; 0.763 35,000; 460; 4,250; 0.746 25,000; 505; 3,500; 0.82 25,000:505: 0.805 36,000; 475; 4,625; 0.90 36,000; 475; 5,250; 0.84 36,000; 475; 5,345:0.819 25,000; 470; 3,730; 0.776 25,000; 470; 3,730; 0.78 TBO (hr) 1,200 1,400 1.000 2,500 = 1 Main applications Hawker P. 1127 CV-990 707-120B, 720B, DC-8-50 B-52H,C-135B 707-320B.DC-8F C141A 727 Douglas 2086 F-lllA 707-420, DC-8-40 VC10 Super VC10 Trident 1, One-Eleven Trident, One-Eleven Mirage UJV Saab-105 * The JTF10A-20 will have full reheat; the related TF-106 is to be rated at 11,2401b dry and 19,680lb with full reheat, with s.f.c. (dry) of 0.60 and l-p and h-p r.pjn. of9J70 and 14J00.
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