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The General Electric CJ610 is a non-afterburning turbojet engine derived from the military J85, and is used on a number of civilian business jets.The model has logged over 16.5 million hours of operation.
The higher-thrust variants, GE90-110B1 and -115B, have a different architecture from that of the earlier GE90 versions. General Electric incorporated an advanced larger diameter fan made from composite materials which enhanced thrust at low flight speeds. However, GE also needed to increase core power to improve net thrust at high flight speeds.
The BR710 comprises a 48 in (120 cm) diameter single-stage fan, driven by a two-stage LP turbine, and a ten-stage HP compressor (scaled from the V2500 unit) driven by a two-stage, air-cooled, HP turbine. This engine has a thrust-specific fuel consumption (TSFC) of 0.39 lb/(lbf⋅h) (11 g/(kN⋅s)) at static sea level takeoff and 0.64 lb/(lbf⋅ ...
Cutaway showing the configuration : 1 fan, 2A+1C HP compressor, 1 HP and 2 LP turbine Type Turbofan: National origin: Canada: Manufacturer Pratt & Whitney Canada: First run November 1993 [1] Major applications: Cessna Citation II Bravo Cessna Citation V Encore Cessna 560XL Embraer Phenom 300 MQ-20 Avenger: Number built: 4,600 (May 2023) [2]
The J47 design used experience from the TG-180/J35 engine which was described by Flight magazine in 1948 [4] as the most widely used American-conceived turbojet.. The turbojet featured a revolutionary anti-icing system where hollow frame struts allowed heated airflow to pass through from the compressor, allowing fighter jets equipped with the engine to function at high altitudes, and in cold ...
In case of a rocket or a jet aircraft, the force is exactly the thrust (T) produced by the engine. If the rocket or aircraft is moving at about a constant speed, then distance divided by time is just speed, so power is thrust times speed: [ 9 ]
Two booster stages were added to the LP (low pressure) compressor and the last two stages of the HP compressor were removed [6] which increased the overall pressure ratio to 29.3. Although the 86.4 in (2.19 m) diameter fan was retained, the airflow was raised to 1,450 lb/s (660 kg/s), yielding a static thrust of 51,000 lb f (227 kN). The ...
The Grumman F-14 Tomcat with the TF30-P-414A was underpowered, because it was the Navy's intent to procure a jet fighter with a thrust-to-weight ratio (in clean configuration) of 1 or better (the US Air Force had the same goals for the F-15 Eagle and F-16 Fighting Falcon).