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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. [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.
The General Electric GE36 was an experimental aircraft engine, a hybrid between a turbofan and a turboprop, known as an unducted fan (UDF) or propfan.The GE36 was developed by General Electric Aircraft Engines, [3] with its CFM International equal partner Snecma taking a 35 percent share of development. [4]
Turbofan engines with a bypass ratio of at least 4. Pages in category "High-bypass turbofan engines" The following 49 pages are in this category, out of 49 total.
These sizes achieve the desired high bypass ratios of over 30, but they are approximately twice the diameter of turbofan engines of equivalent capability. [67] For this reason, airframers usually design the empennage with a T-tail configuration in order to avoid the turbulent propwash adversely influencing the elevators and causing vibration ...
These engines produce nearly 80% of their thrust by the ducted fan, which can be seen from the front of the engine. They come in two types, low-bypass turbofan and high bypass, the difference being the amount of air moved by the fan, called "bypass air". These engines offer the benefit of more thrust without extra fuel consumption.
More recent large high-bypass turbofans include the Pratt & Whitney PW4000, the three-shaft Rolls-Royce Trent, the General Electric GE90/GEnx and the GP7000, produced jointly by GE and P&W. The Pratt & Whitney JT9D engine was the first high bypass ratio jet engine to power a wide-body airliner. [46]
In 2010, Pratt & Whitney launched the development of an ultra high-bypass version, with a ratio significantly higher than the PW1100G's 12.2:1 for the A320neo, to improve fuel consumption by 20% compared to a CFM56-7 and reduced noise relative to the FAA's Stage 4 by 25 dB. In 2012, wind tunnel tests were completed on an earlier version of the ...
Normally a low specific thrust turbofan would have an ultra-high bypass ratio and be fitted with a reduction gearbox between the fan and the LP shaft to allow the IP compressor and LP turbine to operate at a much higher rotational speed than the fan to reduce the number of stages required in these multi-stage devices.