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  2. Staged combustion cycle - Wikipedia

    en.wikipedia.org/wiki/Staged_combustion_cycle

    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 ...

  3. Rocketdyne F-1 - Wikipedia

    en.wikipedia.org/wiki/Rocketdyne_F-1

    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.

  4. RD-253 - Wikipedia

    en.wikipedia.org/wiki/RD-253

    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 ...

  5. RD-180 - Wikipedia

    en.wikipedia.org/wiki/RD-180

    '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.

  6. Chemical Automatics Design Bureau - Wikipedia

    en.wikipedia.org/wiki/Chemical_Automatics_Design...

    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.

  7. RD-191 - Wikipedia

    en.wikipedia.org/wiki/RD-191

    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.

  8. RD-0124 - Wikipedia

    en.wikipedia.org/wiki/RD-0124

    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.

  9. Expander cycle - Wikipedia

    en.wikipedia.org/wiki/Expander_cycle

    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.