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Burning all the oxygen delivered by the compressor stages would create temperatures (3,700 °F (2,040 °C)) high enough to significantly weaken the internal structure of the engine, but by mixing the combustion products with unburned air from the compressor at (600 °F (316 °C)) a substantial amount of oxygen (fuel/air ratio 0.014 compared to ...
The three-zone (reduced from four from the prototype) afterburner, or augmentor, contributes to the stealth of the aircraft by having fuel injectors integrated into thick curved vanes coated with ceramic radar-absorbent materials (RAM). These vanes replace the traditional fuel spray bars and flame holders and block line-of-sight of the turbines.
Specific fuel consumption: 0.562 lb/lbf/h (57.3 kg/kN/h) (dry thrust), 2.46 lb/lbf/h (251 kg/kN/h) (with afterburner) Thrust-to-weight ratio : 7.04:1 (afterburner)
The Pratt & Whitney F135 is an afterburning turbofan developed for the Lockheed Martin F-35 Lightning II, a single-engine strike fighter.It has two variants; a Conventional Take-Off and Landing variant used in the F-35A and F-35C, and a two-cycle Short Take-Off Vertical Landing variant used in the F-35B that includes a forward lift fan. [1]
The General Electric F110 is an afterburning turbofan jet engine produced by GE Aerospace (formerly GE Aviation). It was derived from the General Electric F101 as an alternative engine to the Pratt & Whitney F100 for powering tactical fighter aircraft, with the F-16C Fighting Falcon and F-14A+/B Tomcat being the initial platforms; the F110 would eventually power new F-15 Eagle variants as well.
For example, the General Electric F404-400 uses one igniter for the combustor and one for the afterburner; the ignition system for the A/B incorporates an ultraviolet flame sensor to de-activate the igniter after light-off on minimum fuel has been detected.
To keep the F414 in the same envelope, or space occupied in the airframe, as the F404, the afterburner section was shortened by 4 in (10 cm) and the combustor shortened by 1 in (2.5 cm). Also changed from the F404 is the construction of the first three stages of the high-pressure compressor which are blisks rather than separate discs and ...
For the F/A-18, GE based the F404 on the YJ101 engine they had developed for the Northrop YF-17, enlarging the bypass ratio from 0.20 to 0.34 to enable higher fuel efficiency. The engine consists of a three-staged fan, seven axial stage compressor arrangement, single stage low and high pressure turbines, an augmentor, and produces maximum ...