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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]
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.
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 ...
In a free turbine the turbine driving the compressor rotates independently of that which powers the propeller or helicopter rotor. Cooling air, bled from the compressor, may be used to cool the turbine blades, vanes and discs to allow higher turbine entry gas temperatures for the same turbine material temperatures.**
A ducted fan may be powered by any kind of motor capable of turning the fan. Examples include piston, rotary (Wankel), and turboshaft combustion engines, as well as electric motors. The fan may be mounted directly on the powerplant output shaft, or driven remotely via an extended drive shaft and gearing.
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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. [13] A bypass ratio of 6, for example, means that 6 times more air passes through the bypass duct than the amount that passes through the combustion chamber.