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RD-107
Glushko LOx/Kerosene rocket engine family used on R-7 and subsequent booster stages (including Molniya, Soyuz in 21st Century). First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's.

Glushko decided that an ICBM using German ideas was impossible. He had developed the RD-110 with a cylindrical burner but it suffered combustion instabilities, the engine equivalent of flutter when breaking the sound barrier. Glushko returned to his experiments from the 30's with cylindrical burners - combining his ideas with German ones. He used slots for cooling the nozzle for example. The RD-106 was the result and it made the R-7 possible. The R-7 rocket had an RD-107 on the first stage strap-ons and an RD-108 on the second stage core. After 120 seconds the strap-on rockets fell off into the desert and 2.5 minutes later the second stage separated. The RD-108 had one turbo-pump but 4 combustion chambers. It made it possible to quickly prove the design of a single engine and then move to four. A single gas generator used the decomposition of H2O2. The hot gas spun up the turbine and was vented. The turbines turned the kerosene and oxygen turbo-pumps. Kerosene was used to cool the engine nozzles and then passed to the mixing head. Igniters were used because the propellants weren't hypergolic. Vernier rockets were used for flight control. It took one week and 300 people to prepare a Soyuz rocket for launch. A unique feature you wouldn't find today was a rotating handle on the engine where a soldier and a supervisor would prevent the pump seals freezing during the start of fuelling. It was automatically closed later. There were 9 modifications to the rocket for Progress, Soyuz, etc. The R-7 became the mass production record holder with more than 1,700 flights of its family. This means 1,700 x 5 engines x 4 chambers per engine, plus ground test models. Developed in 1954-1955.



Subtopics

RD-211 Glushko Nitric acid/Kerosene rocket engine. long-distance missile. Developed 1952-55. Original four-chamber engine design planned for use on the R-12 IRBM. Abandoned due to limited thrust and the RD-214 was developed in its place.

RD-212 Glushko Nitric acid/Kerosene rocket engine. Developed 1952-56. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead.

RD-214 Glushko Nitric acid/Kerosene rocket engine. R-12, Kosmos 11K63 stage 1. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957.

RD-213 Glushko Nitric acid/Kerosene rocket engine. Winged rocket M-40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level.

RD-111 Glushko LOx/Kerosene rocket engine. R-9 stage 1. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing LOx loading in 20 minutes. First flight 1961.

RD-112 Glushko LOx/UDMH rocket engine. ICBM stage 1 (stage 2 was RD-113). Developed 1960.

RD-113 Glushko LOx/UDMH rocket engine. ICBM stage 2 (stage 1 was RD-112). Developed 1960. Upper stage version of RD-112 with larger nozzle.

RD-114 Glushko LOx/UDMH rocket engine. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65.

RD-115 Glushko LOx/UDMH rocket engine. ICBM stage 2 (stage 1 was RD-114). Developed 1961-65. Upper stage version of RD-114 with larger nozzle.

RD-108-8D727K Glushko LOx/Kerosene rocket engine. Molniya 8K78-3. Out of Production.

RD-107-11D511 Glushko LOx/Kerosene rocket engine. Soyuz 11A511-0, Soyuz 11A511U-0. Design 2000. Diameter is per chamber. First flight 1965.

RD-108-11D512 Glushko LOx/Kerosene rocket engine. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. First flight 1965.

RD-107-8D74 Glushko LOx/Kerosene rocket engine. R-7 8K71, Vostok 8K72, Vostok 8K72K strap-ons. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's.

RD-108-8D75 Glushko LOx/Kerosene rocket engine. R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / LOx. Diameter is per chamber. First flight 1957.

RD-107-8D76 Glushko LOx/Kerosene rocket engine. Sputnik 8A91-0. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / LOx. Diameter is per chamber. First flight 1958.

RD-108-8D727 Glushko LOx/Kerosene rocket engine. Molniya 1, Molniya 8K78M-1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / LOx. Diameter is per chamber. First flight 1964.

RD-108-8D77 Glushko LOx/Kerosene rocket engine. Sputnik 8A91-1. Out of Production. Diameter is per chamber. First flight 1958.

RD-117 Glushko LOx/Kerosene rocket engine. Soyuz ST stage 1. In production. Update of RD-107. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. First flown 2001.

RD-107-8D728 Glushko LOx/Kerosene rocket engine. Molniya 0, Molniya 8K78M-0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / LOx. Diameter is per chamber. First flight 1964.

RD-107-8D74-1958 Glushko LOx/Kerosene rocket engine. Luna 8K72-0. Out of production. Diameter is per chamber. First flight 1958.

RD-108-8D75-1958 Glushko LOx/Kerosene rocket engine. Luna 8K72-1. Out of production. Diameter is per chamber. First flight 1958.

RD-118 Glushko LOx/Kerosene rocket engine. In production. Update of RD-107, used in Soyuz ST launcher. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. First flight 2001.

RD-107-8D74-1959 Glushko LOx/Kerosene rocket engine. Out of production. Diameter is per chamber. Used on Vostok 8K72K launch vehicle. First flight 1960.

RD-108-8D75-1959 Glushko LOx/Kerosene rocket engine. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Used on Vostok 8K72K launch vehicle. First flight 1960.

RD-117PF Glushko LOx/Kerosene rocket engine. manned Soyuz-launcher stage 1. Design concept. Update of RD-107. Probably version using Sintin instead of kerosene.

RD-107-8D74K Glushko LOx/Kerosene rocket engine. Developed in 1957-1960. Used in strap-ons for Molniya 8K78, R-7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Fuel T-1 or RG-1 kerosene. First flight 1959.

RD-108-8D75K Glushko LOx/Kerosene rocket engine. Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1. Diameter is per chamber. First flight 1959.

RD-107-11D511P Glushko LOx/Kerosene rocket engine. Soyuz 11A511U2-0. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG-1) / LOx. Diameter is per chamber. First flight 1982.

RD-108-11D512P Glushko LOx/Kerosene rocket engine. Soyuz 11A511U2-1. Out of production. A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982.

RD-107-8D74PS Glushko LOx/Kerosene rocket engine. Sputnik 8K71PS-0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 1956-1957. Flown 1957-1958. Propellants kerosene (RG-1) / LOx. Diameter is per chamber.

RD-108-8D75PS Glushko LOx/Kerosene rocket engine. Sputnik 8K71PS-1. Out of Production. Diameter is per chamber. First flight 1957.



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