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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).
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio
The pumps (one for the fuel and one for the oxidizer) in electric-pump feed engines are driven by an electric motor. [19] The Rutherford engine uses dual brushless DC electric motors and a lithium polymer battery. It is claimed that this improves efficiency from the 50% of a typical gas-generator cycle to 95%. [20]
RS-68 being tested at NASA's Stennis Space Center Viking 5C rocket engine used on Ariane 1 through Ariane 4. A rocket engine is a reaction engine, producing thrust in accordance with Newton's third law by ejecting reaction mass rearward, usually a high-speed jet of high-temperature gas produced by the combustion of rocket propellants stored inside the rocket.
It is manufactured by the Motor Sich factory in Zaporizhzhia, Ukraine. It was the first engine in the USSR that could deliver more than 20,000 kgf (~196 kN or ~44,000 lbf) of thrust. [ 3 ] The first start of a full-scale engine occurred on September 19, 1980, the An-124 maiden flight on December 24, 1982 and the engine passed official bench ...
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.
SpaceX’s Merlin 2 LOX/RP-1-fueled engine on a gas-generator cycle, capable of a projected 7,600 kN (1,700,000 lbf) of thrust at sea level and 8,500 kN (1,920,000 lbf) in a vacuum and would provide the power for conceptual super-heavy-lift launch vehicles from SpaceX, which Markusic dubbed Falcon X and Falcon XX.
Compressor: 3-stage axial and 1-stage centrifugal (each gas generator) Combustors: Reverse flow annular combustor; Turbine: 1-stage gas generator turbine + 1-stage free-power turbine (each gas generator) Fuel type: Aviation Kerosene, such as Jet A-1, JP-4 or JP-5; Oil system: Pressure spray at 80 psi (5.5 bar) with return
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