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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 ...
Modular construction allows sub-assemblies or modules to be changed without the need for full power testing of the engine after replacement. Modules are changed “on condition” [ 6 ] by monitoring deteriorating trends in performance and mechanical measurements, such as exhaust gas temperature and oil samples, and by visually assessing blade ...
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.
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.
Studied with General Electric Aviation to possibly replace the jointly produced CFM56 engine, the M123 added a seventh high pressure compressor (HPC) stage to the M88's six-stage HPC unit. [10] Later known as the CFM88, the engine was a proposed powerplant for the Regioliner, the DASA / Aerospatiale / Alenia successor to the MPC 75 .
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 stability problems.
In full afterburner it produces a thrust of more than 30,000 pounds-force ... Specific fuel consumption: 0.562 lb/lbf/h (57.3 kg/kN/h) (dry thrust),
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.