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Since the afterburning exit temperature is effectively fixed, [why?] the temperature rise across the unit increases, raising the afterburner fuel flow. The total fuel flow tends to increase faster than the net thrust, resulting in a higher specific fuel consumption (SFC). However, the corresponding dry power SFC improves (i.e. lower specific ...
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 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.
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 Pratt & Whitney J58 (company designation JT11D-20) is an American jet engine that powered the Lockheed A-12, and subsequently the YF-12 and the SR-71 aircraft. It was an afterburning turbojet engine with a unique compressor bleed to the afterburner that gave increased thrust at high speeds.
It was later adapted with an afterburner for supersonic designs, and in this form it was the world's first production afterburning turbofan, going on to power the F-111 and the F-14A Tomcat, as well as being used in early versions of the A-7 Corsair II without an afterburner. First flight of the TF30 was in 1964 and production continued until 1986.
It features an eight-stage axial-flow compressor powered by two turbine stages, and is capable of generating up to 2,100 lb f (9.3 kN) of dry thrust, or more with an afterburner. At full throttle at sea level, this engine, without afterburner, consumes approximately 400 US gallons (1,500 L) of fuel per hour.
Pratt & Whitney designed the J57 to have a relatively high overall pressure ratio to help improve both thrust-specific fuel consumption and specific thrust, but it was known that throttling a single high-pressure-ratio compressor would cause
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