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Aviation History
1965
1965 - 0050.PDF
34 AERO ENGINES FUCHT International. 7 January 1965 TABLE 3: TURBOPROPS Designation Manufacturer's AiRe»earchTPE33l Allison 5OI-DI3 General Electric Ivchenko AI-20 AI-J4 Kuznetsov NK-I2M Lycoming LTCIF-2 LTC4G-3 Rolls-Royce Dart 7 Dart 101 Dart 10 Dart 12 Tyne 512 Tyne 101 Tyne 20 Tyne 31 Rover TP/90 Turbomeca Turmo 3D Bastan 4 Astazou X UA Canada PT6A-6 Military T76-G-6 T56-A9 T78 T64-I0 T53-L-7 YT55-L-9 RDa.7 RDa.8 RDa.10 RDa.12 RTy.ll RTy.12 RTy.21.22 T74 Engine configuration 2c, 3t 14a. 4c 14a, 2ct, 2pt 10a. 3t 14a, 5t 5a + Ic, let, Ipt 7a + Ic, let, Ipt 2c, 3t 2c, 3t 2c, 3t 2c, 3t 6a, 9a, It, 3t 6a. 9a, It, 3t 6a, 9a, It, 3c 6a, 9a, It, 3t Ic, It la-t- lc,2ct,2pt la + Ic, 3t 2a + Ic, 3t 3a + Ic, let, Ipt Length (in) 46 145.2 113 236.2 58.4 62.2 98 97 98 99.5 108.7 108.7 108.7 35.44 75.6 61.05 75.27 62 Height (in) 24.5 42 46 38 38 38 38 44 44 44 27.6 30.53 Width (in) 16.5 30 45.3 23 24.25 38 38 38 38 43.2 43.2 43.2 20 37 26.97 19 Equip- ped weight (Ib) 255 1,756 1,167 5^070 555 795 1,227 1,237 1,377 1,378 2,275 2,219 2,218 190 694 465 281 270 TBO (hr) 2,200 500 250 4,800 3,600 3,600 Max Power s.h.p.;e.h.p.; r.p.m.; iXc; mass pres- flow; sure ratio 600; — ; — ; 0.614 3,460; 3.750 ; 13,820; 0.54 4,000; — ; — ; — 2,850; — ; 15.590; 0.49 — ; 4,000 ; — ; — — ; 2,500 ; — ; — — ; 14,795 ; — ; — 1,100; 1,150 ; 26,000; 0.641 2,445 ; 2,529 ; 18,750; 0.61 1,910; 2,100 ; 15,000; 0.656 2,470 ; 2,690 ; 15,000; 0.658 2,750; 3,025 ; 15,000; — 2,970 ; 3,245 ; 15,000; — 4,850; 5,325 ; 15,250; — 5,095; 5,505 ; I5,250;0.499 5,440 ; 5,855 ; 15,250; 0.439 7,870 ; 8,400 ; 15,250; — 118; 118 ; 47,000; 1.38 — ; 1,450 ; 33,500;0.657 1,000 ; 1,072 ; 33.500; 0.584; 640; 678 ; 43,000; 0.513; 550 ; 578 ; 37,500; 0.65 ; 5.6; 7.9 32.5; 9.25 137 ; 13 10.7 ; 6 23.5 : 5.6 23.5 ; 5.6 27 ; 6.35 27 ; 6.35 46.5 ; 13.5 46.5 ; 13.5 46.5 ; 13.5 1.88 ;2.8 13 ; 5.5 9.8 ; 5.5 — ; 7.5 5.3 ; 6.3 Remarks NA 300 COIN; Beech Super 18 eonv.; Turbo Commander; Stal- lion; Porter; Mitsubishi MU2 Electra; CV340/440 conv; CI30A T56-A-7. 8 (4,050 e.h.p.), CI30B E, Grumman E2A, C2A Development: regenerative engine Buffalo T64-I, XCI42A An-10, IL-18 An-24 Bear, Tu-114, 18ft 4in contra props OV-I Development Viscount 800; Herald, F-27 Argosy 220, Gulfstream W/rn boost, cooled blades; Argosy C.I NAMC YS-II; Convair 240/340, 440 Andover C.I ' Vanguard 952:Tyne 506 Vanguard 951, 953 Belfast, CL-44 RTy.2l Atlantic; RTy.22 Transall, licence-built Under development: Short SC51 31 Belfast Development Breguet 941 Nord 262, Guarani Turbo Skyvan, Potez 842: wil give 715 e.h.p. PT6A-8 (680 e.h.p.) under development. King Air, Charger, Potez 841, DHC types Designation Manufacturer's A!ResearchTSE33l Allison BMW 60I2A 6022 Boeing 550-1-22C BS Gnome HI200 Nimbus 7S0 Continental Model 217-2A Model TS-325-1 DB.720/PTL6 GE.CT58-II0 KHD T I6B Lycoming LTCIK-S LTC4B-8 PAW JFTDI2A.3 R-R Napier Gazelle 162 Turbomeca Artoust 3B Turmo 3C Agusta TM25I UA of Canada PT6B-9 Military T63-A-5 Mk 101 Mk 100 — T65-T-I T58-8 T64-6 T53-L-11 T55-L-7 N.Ga 13 Engine Configuration 2c, 3t 6a + Ic, 2ct, 2pt Ic, It la + Ic, let, Ipt 10a, 2ct, 2pt 2a + Ic,2ct, Ipt 2 x 2a + 1 c, 2ct, la + Ic,2ct, Ipt 4a + Ic,2ct, Ipt 10a, 2ct, Ipt 14a, 2ct, 2pt Ic, It 5a + Ic, let, Ipt 7a + 1 c, 1 ct, 2pt 9a, 2ct, 2pt lla, 2ct, Ipt Ic, 2t la + Ic, 2ct, 2pt lc,2t 3a + Ic. let, Ipt (in) 35 40.81 27.5 37.5 54.8 61.6 52.0 34.2 64.6 59 83 32.5 47.6 44.04 74.5 71.46 77.8 46.85 59 TABLE Height (in) 19.5 2X5 22.5 27.2 21 — 19.06 30 32.1 33.5 24.68 28.2 24.8 Width (in) 18.5 19 14.95 22.5 17 20.1 37.96 18.25 20.3 16 24 24.2 23.0 24.25 21.9 33.5 19.96 27.3 14.57 19 4! T ped weight (Ib) 200 136 100 211 350 390 519 136 485 304 724 154 496 580 870 875 287 485 280 245 URBOSHAFTS Max Power ch.p.; r.p.m.; out- s.f.c; mass pres- put flow; sure r.p.m.; ratio 500; 39,000; 6,000; 0.619; 4.4; 6.5 250; 35,000; — ; 0.71 ; 3 ; 6.2 100; 45,000; 3-8,000; I25lb/hr; —; 3 250; — ; — ; — ;—; — 425; — ; 6,000; 0.75 ; 4.46; 5.92 1,250; 26,750; 19,500; 0.65 ; 12.3; 8.1 1.050:35.300; 2,150; 0.68 ; 11.0; 6.5 1,400; 32,400; 6,600; 0.57 ; 6.45; 7.0 310; — ; 6,017; 0.66 ; 3.3; 6.0 I,250;2I,200; 6,100:0.604; — ; 5.5 1,250; 26,300; 6,000; 0.64 ; 12.4; 8.3 2,850; 13.600; 13,600; 0.495; 24.5; 12.6 100; 50,000; — ; 0.41 ; — ; 2.8 1,100; 26,000; — ; 0.652; 10.7; 6 2,500; 14,550; — ; 0.59 ; —; — 4,050; — ; —; — ;—: 6.5 1,575; 19,900; 2,500; — ; 16.2; 5.9 550; 33,500; 6,000; 0.716; 9.5; 5.2 l,5O0;33,700; 5,700; 0.595; 13 ; 5.5 310:43,000; — ; — ;—; — 550; 6,230: — ; 0.665; 5.3; 6.3 Rated on alt (ft); — ; 10,000 5,000 — 0 15,000 0 3,280 0 •pee (let) too 0 — 0 100 0 0 0 Ihr power d s.h.p.; s.f.c. ; 400;0.65l ; 159; 0.82 • 950; 0.602 770; 0.705 — ; — 800; 0.70 1.750; 0.485 1,330:0.695 405; 0.81 485; 0.69 Remarks Development LOH 60I2L, Do32E BSI05;Do32Z T50-BO-IO, 330 s.h.p.; QH-50D AB.204B, 205, etc Scout; Wasp Coupled T72 S6I; S62; Vertol 107 Model 2 a.p.u. UH-IB, D, E CH-47B S64 Wessex 31 Alouette 3 Super Frelon A. 105 Hiller Ten 99: TL5 Designation Continental A6S-8F C90-I2F O-200-A O-100-A IO-346-A IO-360-A GIO-470-A GTSIO-520-A Franklin 2A-I20 4A-235 6AGS-335 Lycoming O-215-CIB IO-320-BIA IO-360-AIATVCM3S-BIA GO-480-BIA6 IO-S40-BIA5 IGSO-540-BIA VO-540-C2AIO-720-AIA McCullochPlWMIIVvll Model 43I8A, O-I00-I Meteor Alfa 2OKL NP-I WN-4ROmnipol MII0-H Potez-Avco 4E-30 Rollason-Ardem 4CO2 Mk 5 Engine configuration O4 O4 O4 O6 O4, inj O6, inj O6, g, inj O6, g, turb, inj O2 O4 O6, g, turb, inj O4 O4, inj O4, injO6, vert, turb O6, g O6, inj O6, inj, g, s O6, vert O8, inj O4, 2 str R4, s O4 O6, SO4, inj O4, inj O4 Length (in) 27.5 23.34 30.53 38.38 30 34.6 45.22 60.15 23.7 30.5 41.0 29.81 33.59 29.8134.73 39.84 38.62 48.5 34.73 46.08 34.5 34.2528.23 48.81 31.5 27.5 TABLE S: PISTON Height (in) 27 29.3 23.18 27.41 22.48 24.33 25.77 24.42 22.7 25.1 21.25 22.4 17.22 21.6135.65 28.02 19.6 20.29 25.57 22.53 12.3 i. 23.42 16.5332.28 23.3 Width (in) 31.5 31.5 31.56 31.5 33.38 31.4 33.56 33.56 30.7 31.5 31.6 32.0 32.24 34.2533.58 33.12 34.25 34.25 34.70 34.25 22.0 23.4631.57 32.6730.48 30.3 Equipped weight (Ib) 169 190 190 268 296.5 327 447 508 130 228 410 240 287 323478 432 437 532 442 400 114 220 295 238 ENOINI Bore (in) 3.875 4.0625 4.0625 4.0625 5.25 4.4375 5 5.25 4.625 4.625 4.5 4.375 5.125 5,1254.875 5.125 5.125 5.125 5.125 5.125 3.1875 4.1333.86 4.92 4.33 4.33 3.27 ES Stroke (in) 3.625 3.875 3.875 3.875 4 3.875 4 4 3.5 3.5 3.5 3.875 3.875 4.375 3.875 3.875 4.375 4.375 4.375 4.375 3.125 3.071 3.54 3.7 3.43 3.54 2.72 Capacity (cu in) 171 201 201 301 346 360 471 520 118 235 335 233 319.8 361434 480 541.5541.5 541.5 722 100 164.76 165.7 421 201 209 91.2 Com- pression ratio 6.3 7.0 7.0 7.0 8.5 8.5 8.6 7.5 9.5 7.0 7.0 6.75 8.5 8.77.3 7.3 8.7 7.3 8.7 8.7 7.8 6.5 6.5 6.5 7 8 7.8 Fuel grade (Oct) 73 80/87 80/87 80/87 91/96 100/130 100/130 100/130 100/130 80/87 100/130 80 91/96 100/130100/130 80/87 100/130 100/130 100/130 100/130 100/130 72 72 100/130 80 Maximum power s.h.p.; r.p.m.; s.f.c. 65; 2,300; — 95; 2,475; — 100; 2,750; — 145; 2,700; — - 165; 2,700; — 210; 2,800; — 310; 3,200; — 390; 3.400; — 60; 3,000; 0.49 125; 2,800; 0.49 260; 3,200; 0.50 108; 2,600; — 160; 2,700; — 200; 2,700; —270; 3,200; — 270; 3,400; — 290; 2,575; — 380; 3,400; — 305; 3,200; — 400; 2,650; — 110; 4,100; — 120; 2,900; — 68; 2,600; — 220; 3,000; — 120; 3,100; — 117; 2,850; 0.51 55; —; —
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