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1 set of turbines and pumps; turbine produces approximately 257,000 hp (192 MW); equivalent to the power output of 3 nuclear-powered icebreakers; Ignition: pyrophoric start-up fuel capsule (triethylaluminium) [17] Vacuum thrust: 7,887 kN (1,773,000 lb f) Vacuum I sp: 338 s (3.31 km/s) Sea-level I sp: 309 s (3.03 km/s)
The fuel pump delivered 15,471 US gallons (58,560 litres) of RP-1 per minute while the oxidizer pump delivered 24,811 US gal (93,920 L) of liquid oxygen per minute. Environmentally, the turbopump was required to withstand temperatures ranging from input gas at 1,500 °F (820 °C) to liquid oxygen at −300 °F (−184 °C).
Merlin 1A produced 340 kilonewtons (76,000 lb f) of thrust and was used to power the first stage of the first two Falcon 1 flights in 2006 and 2007. Merlin 1B had a somewhat more powerful turbo-pump , and generated more thrust, but was never flown on a flight vehicle before SpaceX's move to the Merlin 1C.
These engines solved the reliability problems and provided nearly 30% more thrust, achieving a 1:1 dry thrust to weight ratio with a low fuel load. The subsequent F-14D, a combination of both remanufactured/upgraded F-14As and new manufacture F-14Ds, also used F110-GE-400 engines.
The thrust-to-weight ratio is usually calculated from initial gross weight at sea level on earth [6] and is sometimes called thrust-to-Earth-weight ratio. [7] The thrust-to-Earth-weight ratio of a rocket or rocket-propelled vehicle is an indicator of its acceleration expressed in multiples of earth's gravitational acceleration, g 0. [5]
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⋅ ...
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