Search results
Results From The WOW.Com Content Network
Schematic diagram illustrating a 2-spool, high-bypass turbofan engine with an unmixed exhaust. The low-pressure spool is coloured green and the high-pressure one purple. Again, the fan (and booster stages) are driven by the low-pressure turbine, but more stages are required. A mixed exhaust is often employed.
English: Schematic diagram illustrating the operation of a 2-spool, high-bypass turbofan engine, with LP spool in green and HP spool in purple. Polski: Schematyczny diagram pracy uogólnionego silnika turbowentylatorowego wysokoprzepływowego.
An animation of a turbofan engine. This is a 2-spool, high-bypass turbofan typical of those found on modern passenger aeroplanes. Turbofan engines provide good thrust at speeds at up to approximately Mach 1.6, at higher speeds turbojet engines are more effective whilst turboprop engines are more effective at low speeds. 1. Nacelle 2. Fan 3.
In a geared turbofan, a planetary reduction gearbox between the fan and the LP shaft allows the latter to run at a higher rotational speed thus enabling fewer stages to be used in both the LP turbine and the LP compressor, increasing efficiency and reducing weight. However, some energy will be lost as heat in the gear mechanism and weight saved ...
The Pratt & Whitney PW4000 is a family of dual-spool, axial-flow, high-bypass turbofan aircraft engines produced by Pratt & Whitney as the successor to the JT9D.It was first run in April 1984, was FAA certified in July 1986, and was introduced in June 1987.
The PW2000 is a dual-spool, axial air flow, annular combustion, high bypass turbofan with a dual-channel full authority digital engine control system. It was certified in 1984 as the first civilian FADEC-controlled aviation engine. [3]
Schematic diagram illustrating the operation of a low-bypass turbofan engine. Turbofans differ from turbojets in that they have an additional fan at the front of the engine, which accelerates air in a duct bypassing the core gas turbine engine. Turbofans are the dominant engine type for medium and long-range airliners.
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 ...