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For aircraft, the quoted thrust-to-weight ratio is often the maximum static thrust at sea level divided by the maximum takeoff weight. [2] Aircraft with thrust-to-weight ratio greater than 1:1 can pitch straight up and maintain airspeed until performance decreases at higher altitude. [3]
The engine has an overall pressure ratio of 35:1, which is extremely high for an engine with a centrifugal compressor. Other cycle parameters are a bypass ratio of 5.3 and airflow of 240 lb/s (108.9 kg/s). The take-off thrust is 5,600 lbf (24.9 kN), flat-rated to ISA +15°C (30°C, 86°F).
The ATF's increasing weight during development required more thrust to meet the performance requirements; as gross weight grew to 60,000 lb (27,200 kg), the required maximum thrust was increased by 20% to 35,000 lbf (156 kN) class. Pratt & Whitney's design changed to incorporate a 15% larger fan, increasing bypass ratio from 0.25 to 0.30.
The engine used a special high-temperature JP-6 fuel. The six YJ93 engines in the XB-70 Valkyrie were capable of producing a thrust to weight ratio of 5:1 allowing for a speed of 2,000 mph (3,200 km/h) (approximately Mach 3) at an altitude of 70,000 feet (21,000 m). [4]
Max takeoff weight: 42,300 lb (19,187 kg) Fuel capacity: 7,000 pounds (3,200 kg) internal [67] Powerplant: 1 × General Electric F110-GE-129 for Block 50 aircraft , 17,155 lbf (76.31 kN) thrust dry, 29,500 lbf (131 kN) with afterburner (1 × Pratt & Whitney F100-PW-229 for Block 52 aircraft, 17,800 lbf (79 kN) thrust dry and 29,160 lbf (129.7 ...
Fuel for the rocket would come from the aircraft fuel supply. ... and internal fuel [62] Max takeoff weight ... and 1/2 fuel [u] Thrust/weight: 0.78 (1.03 ...
When Airbus launched its A330 twin-jet in June 1987, its only engine options included the General Electric CF6-80C2 and the Pratt & Whitney PW4000. [4] Rolls-Royce was studying whether to launch a RB211-700, 65,000 lbf (290 kN) development of the RB211 for the A330, the long-range Boeing 767 and McDonnell Douglas MD-11, derived from the Boeing 747-400's -524D4D, with growth potential to 70,000 ...
The PW 300 series has been developed in partnership with MTU who are responsible for the low pressure turbine. The first variant, the PW305A, has the following configuration and was designed with a core flexible enough for engines with take-off thrusts from 20 kN to 31 kN (4,500 to 7,000 lb): a single-stage fan driven by a three-stage low pressure turbine, supercharging a four-stage axial ...