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Aviation History
1996
1996 - 2713.PDF
ENGINE DIRECTORY CRJ-X 70-seat regional jet. The CRJ-X is a stretched version of the CF34-powered Canadair Regional Jet. The engine will also be pitched at Aero International (Regional)'s AIR70 regional jet. GEsays the CF34-8C will be service-ready in February 1999. Japan Aero Engines, a group headed by Kawasaki Heavy Industries, and Ishikawajima-Harima Heavy Industries have already been signed-up to participate in the -8C programme. A growth version of GE's T700 turboshaft, which combines the core of the CT7-9 turbo prop with a new, increased-airflow compressor and full-authority digital engine-control, is now being developed for use on the NH Industries NH90 and Sikorsky S-92 twin-engined heli copters. In the military sector, GE has completed flight-test qualification of the F110-129ona US Air Force F-15. The engine is due to be manufactured in Japan within the next three years to power the Mitsubishi F-2 multi-role fighter. The F414, meanwhile, has accumulated more than 650h in the McDonnell Douglas F-18E/F test pro gramme. • M.iAiAhiWHiiUiirf.rama Model CF34-3A1 CF34-3B CF34-3B1 CF34-8C1 CF6-80A/A3 CF6-80C2 CF6-80E1 GE90-85B HiiiiMiraiii;, Model F110-100 Thrust kN lb 41 41 41 61.3 214 -222 233-273 293 -303 376 Max thrust dry kN lb 9,220 9,220 9,220 13,790 48,000-50,000 52,500-61,500 65,800-68,100 84,700 Length Rotor/fan m diameter (m 2.61 2.61 2.61 3.26 3.99 4.08 4.18 4.88 Max thrust (reheat) kN lb 78 17,530 124.6 28,000 1.24 1.24 1.24 1.32 2.19 2.38 2.44 3.35 Length m 4.62 SFC mg/Ns Ib/h/lb 10.11 .357 9.79 .346 9.79 .346 11.3 .399 9.76-9.99.344-0.352 8.8-9.65 .31-0.34 9.36-9.65.33-0.34 Rotor/Fan SFC diameter (m) mg/Ns Ib/h/lb 1.18 fan 1 1 1 1 1 1 1 1 fan 3 compressors LP HP 3 4 4 3 14 14 14 10 14 14 14 10 Compressors LP HP 9 turbines HP LP 2 2 2 2 2 2 2 2 4 4 4 4 4 5 5 6 Turbines LP HP 1 2 Application Canadair Challenger 601, Regional Jet Canadair Challenger 604 Canadair Regional Jet Selected for Bombardier CRJ-X Currently in development, FAA certification targeted for mid-1999 Airbus A310, Boeing 767 Airbus A30O600, A310, Boeing 747-300/ 400, 767, 767 AWACS, MDC MD-11 Airbus A330 A-market Boeing 777; -92B at 410kN under development for B-market 777 lApplicatiion Lockheed Martin F-16C/D F110-100B, which employs digital control/turbine upgrates is scheduled for production in 1997 F110-129 76.5 17,600 129.1 29,500 4.62 1.18 2 Lockheed Martin F-16C/D, Mitsubishi F-2, will be qualified on MDC F-15E in 1996 Increased-life version is in development, with qualification targeted for 1999 F118-101 F404-400 F404-402 F404-F1D2 F404/RM12 F414-400 75.6 0 53 47 54 62.27 17,000 0 11,900 10,500 12,140 14,000 74 16,600 79 17,700 80.5 18,100 97.86 22,000 2.55 4.03 4.04 2.26 4.04 3.91 1.18 0.89 0.89 0.89 0.89 0.78 3 3 3 3 3 3 9 7 7 7 7 7 1 1 1 1 1 1 2 1 1 1 1 1 Lockheed U-25 length excludes exhaust nozzle McDonnell Douglas F-18C/D McDonnell Douglas F-18C/D Lockheed F-117A Saab JAS 39 Gripen under development for McDonnell Douglas F/A-18E/F •iwliwi Total Model CT7-5A2 CT7-7A CT7-9B CT7-9D Power kW shp 1,294 1,268 1,344 1,447 TURBOSHAFTS Model CT7-2A CT7-2D/-2D1 CT7-6/-6A CT7-6D CT7-6E CT7-8 T64419 T700401 T700-401C T700-700 T700-701 T700-701A T700-701C T700/T6A T700/T6E 1,735 1,700 1,878 1,940 Power kW shp 1,212 1,212 1,491 1,514 1,685 1,790 3,538 1,260 1,342 1,210 1,266 1,285 1,404 1,491 1,681 1,625 1,625 2,000 2,030 2,259 2,400 4,750 1,690 1,800 1,622 1,698 1,723 1,890 2,000 2,400 Length m 2.41 2.41 2.44 2.44 Length m 1.15 1.15 1.19 1.22 1.26 1.24 1.97 1.18 1.15 1.15 1.18 1.18 1.18 1.19 1.26 Rotor/Fan diameter (m) 0.74 0.74 0.74 0.74 Rotor/fan diameter (ml 0.64 0.64 0.64 0.67 0.64 0.64 0.5 0.64 0.64 0.64 0.64 0.64 0.64 0.64 0.64 ug/J 80.4 80.1 79.6 76.9 ug/J 80.1 80.1 77.2 76 74.2 76.7 80.1 78.4 77.7 78.6 78.4 78.6 78.1 76 74.7 SFC Ib/h/shp 0.476 0.474 0.471 0.455 5FC Ib/h/shp 0.474 0.474 0.457 0.45 0.439 0.454 0.474 0.464 0.46 0.465 0.464 0.465 0.462 0.45 0.442 compressor stage 5axl + lcfgl 5 axl + 1 cfgl 5 axl +1 cfgl 5 axl +1 cfgl Total compressor stage 5 axl +1 cfgl 5 axl +1 cfgl 5 axl +1 cfgl 5 axl +1 cfg! 5 axl +1 cfgl 5 axl +1 cfgl 14 axl 5 axl +1 cfgl 5 axl +1 cfgl 5 axl +1 cfgl 5 axl +1 cfgl 5 axl +1 cfgl 5 axl +1 cfgl 5 axl + 1 cfgl 5 axl +1 cfgl Turbines HP LP 2 2 2 2 2 2 2 2 Turbines HP LP 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 Application Saab 340A Spec weight (dry): 355.2kg (7831b) Airtech (CASA/IPTN) CN-235 Series 10 Spec weight (dry): 355.2kg (7831b) Saab 340B, selected forSukhoi &80 Spec weight (dry): 365.1kg (8051b) Let L-610G Spec weight (dry): 365.1kg (8051b) • Application Bell 214ST Spec weight (dry): 194.6kg (4291b) Sikorsky S-70, selected for Kamov Ka64 Spec weight (dry): 200.5-211.4kg) EH Industries EH101 (Civil) Spec weight (dry): 220kg Sikorsky S-92 Spec weight (dry): 228.6kg NH Industries NH 90 Sikorsky S-92 Sikorsky CH/MH-53-E in service scheduled for first qtr 1997, by retrofit Bell AH-1W, Kaman SH-2G, Sikorsky VH-60 Specweight (dry): 200kg (4411b) Sikorsky HH-60H, HH-60J, SH-60B, SH-60F Spec weight (dry): 207.7kg (4581b) Sikorsky UH-60A, EH-60A, MH-60G Spec weight (dry): 198.2kg (4371b) McDonnell Douglas AH-64A Spec weight (dry): 198.7kg (4381b) Sikorsky S-70A, S-70C Spec weight (dry): 198.7kg (4381b) McDonnell Douglas AFf€4, Sikorsky UH-60L, S-70 Spec weight (dry): 206.8kg (4561b) EH Industries EH101 (Military) spec weight (dry): 220kg (485kg) NH Industries NH 90 FLIGHT INTERNATIONAL 9 - 15 October 1996
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