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The CFE CFE738 is a small turbofan engine aimed at the business/commuter jet market manufactured by the CFE Company, and is used on the Dassault Falcon 2000. Design and development [ edit ]
The GE Passport is a high bypass ratio turbofan. The engine is a twin-spool, axial-flow turbofan with a high bypass ratio of 5.6:1 and an overall pressure ratio of 45:1. The front fan is attached to the three-stage low-pressure compressor; the 23:1 pressure ratio 10-stage high-pressure compressor includes five blisk stages for weight reduction.
Data from FAA General characteristics Type: Twin spool Turbofan Length: 105.8 in (269 cm) (flange to flange) / 130.44 in (331.3 cm) (fan spinner face to aft tail cone) Diameter: 50 in (130 cm) fan case Dry weight: 3,135.7 pounds (1,422.3 kg) (dry) Components Compressor: 24-blade, single-piece Single-stage fan, 2-stage LP and 8-stage HP compressor Turbine: 2 stage HP and 5 stage LP turbine LP ...
The engine's name is a combination of the Roman numeral V, symbolizing the five original members of the International Aero Engines consortium, formed in 1983 to produce the engine, and 2500, which represents the 25,000-pound-force (110 kN) thrust produced by the original engine model, the V2500-A1.
The basic CF6-50 engine was also offered with a 10% thrust derate for the 747SR, a short-range high-cycle version used by All Nippon Airways for domestic Japanese operations. This engine is termed the CF6-45. The engine is designated the General Electric F103 in United States Air Force service on KC-10 Extenders and Boeing E-4s.
The engine final assembly line is located at MTU Aero Engines at their location in Hanover, Germany. LAN Airlines confirmed an order for 15 Airbus A318 aircraft, for a total of 34 engines (30 installed and 4 spares) powered by PW-6000 engines on 15 August 2005.
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The JT8D is an axial-flow front turbofan engine incorporating a two-spool design. There are two coaxially-mounted independent rotating assemblies: one rotating assembly for the low pressure compressor (LPC) which consists of the first six stages (i.e. six pairs of rotating and stator blades, including the first two stages which are for the bypass turbofan), driven by the second (downstream ...