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The Prometheus rocket engine is an ongoing European Space Agency (ESA) development effort begun in 2017 to create a reusable methane-fueled rocket engine for use on the Themis reusable rocket demonstrator and Ariane Next, the successor to Ariane 6, and possibly a version of Ariane 6 itself.
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 first ship of the class, Etna, measures 146.6 metres (481 ft 0 in) long overall with a beam of 21 m (68 ft 11 in) and a draught of 7.25 m (23 ft 9 in). The ship has a standard displacement of 5,980 tonnes (5,890 long tons) and a full load displacement of 13,400 t (13,200 long tons).
Starting fluid is not recommended for regular use with some two-stroke engines because it does not possess lubricating qualities by itself. Lubrication for two-stroke engines is achieved using oil that is either mixed into the fuel by the user or injected automatically into the fuel supply; engines requiring premixed fuel that are run solely on starting fluid do not receive an adequate supply ...
The effects may include: corrosion, abrasive wear, clogged cylinder valves, fuel equipment damage, fuel pump failure, premature ignition, ignition failure, explosion, or engine failure. [1] Several indices are used to characterise fuels. [2] For spark-ignition engines the fuel has an octane rating.
Most designs of liquid rocket engines are throttleable for variable thrust operation. Some allow control of the propellant mixture ratio (ratio at which oxidizer and fuel are mixed). Some can be shut down and, with a suitable ignition system or self-igniting propellant, restarted. Hybrid rockets apply a liquid or gaseous oxidizer to a solid fuel.
For diesel engines it depends on the type of fuel, for distillate fuels the cetane numbers are used. Cetane numbers are tested using a special test engine and the existing engine was not made for residual fuels. For residual fuel oil two other empirical indexes are used: CCAI and Calculated Ignition Index (CII).
The LR87 was an American liquid-propellant rocket engine used on the first stages of Titan intercontinental ballistic missiles and launch vehicles. [1] Composed of twin motors with separate combustion chambers and turbopump machinery, [2] it is considered a single unit and was never flown as a single combustion chamber engine or designed for ...
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