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Thrust reversal, also called reverse thrust, is the temporary diversion of an aircraft engine's thrust for it to act against the forward travel of the aircraft, providing deceleration. Thrust reverser systems are featured on many jet aircraft to help slow down just after touch-down, reducing wear on the brakes and enabling shorter landing ...
The Contrafan was designed to power the four-engine Boeing 747 at a cruise speed of Mach 0.9. Like the General Electric Unducted Fan (UDF), the RB529 would have direct-drive contra-rotating fans in pusher configuration, and it would have variable pitch fan blades that were capable of reverse thrust.
The reverse-thrust ratio (ratio of backward engine thrust to forward reverse thrust) can be as high as 84%. [6] However, this result is obtained with a cowl to attach air flow in a 7° angle and a large enough "target" (deflector door) installed. A reverse-thrust ratio of 55% can be reached on a simple target without the cowl. [7]
These either consist of cups that swing across the end of the exhaust nozzle and deflect the jet thrust forwards (as in the DC-9), or they are two panels behind the cowling that slide backward and reverse only the fan thrust (the fan produces the majority of the thrust). Fan air redirection is performed by devices called "blocker doors" and ...
The pitch of the fan can be reversed through Feather as with the Turbomeca Astafan. [2] or through Fine Pitch as employed in the Rolls-Royce/SNECMA M45SD-02. [3] [4] With reverse thrust engaged, the air for the fan typically enters the engine through an auxiliary intake formed by a longitudinal gap which is exposed near the cold nozzle exit plane.
The monobloc nozzle assembly is installed behind two Olympus 593s. The nozzles are shown in different operating positions to illustrate take-off (right) and landing reverse thrust (left). They are partially closed for take-off to reduce sideline noise. [25] They are fully closed to deflect the exhaust partially forward to produce reverse thrust.
The front and back fans are both variable-pitch propellers; by 1993, the coaxial fans could combine to produce 85% of the desired 4,000 kgf (8,800 lbf; 39 kN) maximum reverse thrust, [27] and by 1995, the reverse thrust capability was 3,800 kgf (8,300 lbf; 37 kN).
The engine's name is a combination of the Roman numeral V, symbolizing the five original members of the International Aero Engines consortium, formed in 1983 to produce the engine, and 2500, which represents the 25,000-pound-force (110 kN) thrust produced by the original engine model, the V2500-A1.
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