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In the full-flow rocket engine, the preburner exhaust is fed into a turbine and then into the main combustion chamber. Several variants of the staged combustion cycle exist. Preburners that burn a small portion of oxidizer with a full flow of fuel are called fuel-rich , while preburners that burn a small portion of fuel with a full flow of ...
The design incorporates a greatly simplified combustion chamber, a reduced number of engine parts, and the removal of the F-1 exhaust recycling system, including the turbine exhaust mid-nozzle and the "curtain" cooling manifold, with the turbine exhaust having a separate outlet passage [17] beside the shortened main nozzle on the F-1B.
The RD-253 uses an oxidiser-rich staged combustion cycle. It was used for the first time in July 1965, when six engines powered the first stage of the Proton rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that time by achieving high levels of thrust, specific impulse and pressure in the combustion ...
'Rocket Engine-180') is a rocket engine that was designed and built in Russia. It features a dual combustion chamber, dual-nozzle design and is fueled by a RP-1/LOX mixture. The RD-180 is derived from the RD-170 line of rocket engines, which were used in the Soviet Energia launch vehicle.
The combustion chamber is an annular and three-zone design. In the first zone the hydrogen combustion takes place in subsonic airflow, in two others — in supersonic flow. The combustion chamber is completely designed and manufactured in KBKhA, and the new and advanced design and technological solutions have been realized.
Burn ignition is provided chemically, by feeding a starter fluid into the combustion chamber and gas generator, which is self-igniting on contact with liquid oxygen. The engine is capable of throttling down to 30% of nominal thrust; the design also allows for a short-duration enhanced thrust (up to 105% of nominal level) in emergency situations.
The RD-0124 (Russian: Ракетный Двигатель-0124, romanized: Raketnyy Dvigatel-0124, lit. 'Rocket Engine 0124', GRAU index: 14D23) is a rocket engine burning liquid oxygen and kerosene in an oxygen-rich staged combustion cycle, developed by the Chemical Automatics Design Bureau in Voronezh.
Expander rocket cycle. Expander rocket engine (closed cycle). Heat from the nozzle and combustion chamber powers the fuel and oxidizer pumps. The expander cycle is a power cycle of a bipropellant rocket engine. In this cycle, the fuel is used to cool the engine's combustion chamber, picking up heat and changing phase.