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The 22-blade fan of an A320's V2500-A1 Rolls-Royce based the 10-stage HP compressor on an 8-stage run in the RB401 in the mid 1970's followed by a 9-stage run in the RJ.500 . The V.2500 would use 10 stages, with the first 4 with variable stators, giving a pressure ratio of 20:1. [ 4 ]
IAE's current purpose is the development, production and aftermarket services of the V2500 aero engine family, which powers the Airbus A320 family and McDonnell Douglas MD-90 aircraft. IAE also supplies the V2500-E5 to power the Embraer KC-390 military transport aircraft; this arrangement is the first military application of the engine. [18]
The fan diameter was expected to range from 108 to 118 in while having a bypass ratio of 18:1 to 20:1. Availability of the engine was estimated between 1992 and 1994. [1] In December 1986 the V2500 SuperFan was officially offered to Airbus as powerplant for the Airbus A340 being developed at that time. With that offer, more design details were ...
A propfan, also called an open rotor engine, open fan engine [1] [2] or unducted fan (as opposed to a ducted fan), is a type of aircraft engine related in concept to both the turboprop and turbofan, but distinct from both. The design is intended to offer the speed and performance of a turbofan, with the fuel economy of a turboprop.
Aircraft powered by a propfan or "unducted fan" engine. Pages in category "Propfan-powered aircraft" The following 10 pages are in this category, out of 10 total.
A propfan engine (also called "unducted fan", "open rotor", or "ultra-high bypass") is a jet engine that uses its gas generator to power an exposed fan, similar to turboprop engines. Like turboprop engines, propfans generate most of their thrust from the propeller and not the exhaust jet.
The Contrafan was designed to power the four-engine Boeing 747 at a cruise speed of Mach 0.9. Like the General Electric Unducted Fan (UDF), the RB529 would have direct-drive contra-rotating fans in pusher configuration, and it would have variable pitch fan blades that were capable of reverse thrust.
The bypass ratio (BPR) of a turbofan engine is the ratio between the mass flow rate of the bypass stream to the mass flow rate entering the core. [1] A 10:1 bypass ratio, for example, means that 10 kg of air passes through the bypass duct for every 1 kg of air passing through the core.