Rocket engines using kerosene propellant

rocket engine by Rocketdyne

thumb|A model of the RD-180

family of rocket engines developed by SpaceX for use on its launch vehicles

The RD-170 () is the world's most powerful and heaviest liquid-fuel rocket engine. It was designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns kerosene fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at in a staged combustion cycle.

The NK-33 (GRAU index: 14D15) and its vacuum-optimized variant, the NK-43, were rocket engines developed in the late 1960s and early 1970s by the Kuznetsov Design Bureau for the Soviet space program's ill-fated N1 Moon rocket. The NK-33 is among the most powerful LOX/RP-1 powered rocket engines ever built, noted for its high specific impulse and low structural mass.

The RD-191 () is a high-performance single-combustion chamber rocket engine, developed in Russia and sold by Roscosmos. It is derived from the RD-180 dual-combustion chamber engine, which itself was derived in turn from the four-chamber RD-170 originally used in the Energia launcher.

The RD-107 () and its sibling, the RD-108, are a type of rocket engine used on the R-7 rocket family. RD-107 engines are used in each booster and the RD-108 is used in the central core. The engines have four main combustion chambers (each with a nozzle) and either two (RD-107) or four (RD-108) vernier chambers.

rocket engine used on the Saturn I and IB

upper stage used on Soviet and later Russian expendable launch systems

family of rocket engines developed by SpaceX for use on its Falcon 1 launch vehicles

The RD-0110 (, and its derivatives, the RO-8, RD-0108, RD-461) is a rocket engine burning liquid oxygen and kerosene in a gas generator combustion cycle. It has four fixed nozzles and the output of the gas generator is directed to four secondary vernier nozzles to provide attitude control for the stage. It has an extensive flight history with its initial versions having flown more than .

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liquid-propellant rocket engine

The RD-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. RD-0124 engines are used on the Block I stage used on Soyuz-2.1b and Soyuz-2.1v. A variant of the engine, the RD-0124A, is used on the Angara rocket family's URM-2 upper stage.

The RD-0109 is a rocket engine burning liquid oxygen and kerosene in a gas generator combustion cycle. It has single nozzle and is an evolution of the RD-0105. It was the engine used on the Vostok Block-E that launched Yuri Gagarin to orbit.

The RD-8 (Russian: and GRAU Index: 11D513) is a Soviet / Ukrainian liquid propellant rocket engine burning LOX and RG-1 (a rocket grade kerosene) in an oxidizer rich staged combustion cycle. It has four combustion chambers that provide thrust vector control by gimbaling each of the nozzles in a single axis ±33°. It was designed in Dnipropetrovsk by the Yuzhnoye Design Bureau as the vernier thruster of the Zenit (GRAU: 11K77) second stage. As such, it has always been paired with the RD-120 engine for main propulsion.

The YF-100 is a Chinese liquid rocket engine burning LOX and kerosene in an oxidizer-rich staged combustion cycle. The engine is designed for use on the first stage of the Chinese government's new generation of launch vehicles, the Long March 5, the Long March 6 and the Long March 7. The engine's maiden flight, on the Long March 6, took place on September 20, 2015.

The RS-27 (Rocket System-27) was a liquid-propellant rocket engine developed in 1974 by Rocketdyne to replace the aging MB-3 in the Delta. Incorporating components of the venerable MB-3 and the H-1 designs, the RS-27 was a modernized version of the basic design used for two decades. It was used to power the first stage of the Delta 2000, 3000, 5000, and the first model of the Delta II, the Delta 6000.

The RD-58 (, GRAU index: 11D58) is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 engine, which was the first staged combustion engine in the world. The engine was initially created to power the Blok D stage of the Soviet Union's abortive N1 rocket. Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets. An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N1's roll-control engine.

rocket engine used on the first stages of Titan rockets

thumb|Rocketdyne LR89 at the Evergreen Aviation & Space Museum The Rocketdyne LR89 was a liquid-fueled rocket engine developed in the 1950s by Rocketdyne, a division of North American Aviation. It was designed to serve as a booster engine the Atlas rocket family. The LR89 was a liquid oxygen (LOX) and RP-1 (kerosene) engine.

The YF-115 is a Chinese liquid rocket engine burning LOX and kerosene in an oxidizer-rich staged combustion cycle. A high efficiency/high thrust environmental-friendly rocket engine was always an objective within Programme 863. Development began in the 2000s, along with its sibling, the bigger YF-100, which would power the LM-5, LM-6 and LM-7 boosters and first stages. Testing was directed by the China National Space Administration (CNSA) commencing in 2005. Development works are mainly carried out by the Xi'an Aerospace Propulsion Institute. It is used as the upper stage engine for China's ne

1950s British aircraft rocket engine

The S1.5400 (GRAU Index 11D33) was a Soviet single-nozzle liquid-propellant rocket engine burning liquid oxygen and kerosene in an oxidizer-rich staged combustion cycle, the first rocket engine to use this cycle in the world. It was designed by V. M. Melnikov, an alumnus of Isaev, within Korolev's Bureau, for the Molniya fourth stage, the Block-L. It was the first Soviet engine designed for start and restart in vacuum, and had the highest Isp at the time of its deployment.

thumb|An LR105 Atlas sustainer engine on display at the Air Zoo. The LR105 is a liquid-fuel rocket engine that served as the sustainer engine for the Atlas rocket family. Developed by Rocketdyne in 1957 as the S-4, it is called a sustainer engine because it continues firing after the LR89 booster engines have been jettisoned, providing thrust during the ascent phase.

The LR91 was an American liquid-propellant rocket engine, which was used on the second stages of Titan intercontinental ballistic missiles and launch vehicles. While the original version - the LR91-3 - ran on RP-1/LOX (as did the companion LR87-3) on the Titan I, the models that propelled the Titan II and later were switched to Aerozine 50/N2O4.

The SE-2000 (formerly known as SCE-200, also referred as Semi-Cryogenic Engine-2000) is a 2 MN thrust class liquid rocket engine, being developed to power ISRO's existing LVM3 and upcoming heavy and super heavy-lift launch vehicles. It is being developed by the Liquid Propulsion Systems Centre (LPSC) of ISRO, and is expected to have first flight in 2020s.

The RD-810 (РД-810) is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene (RG-1) in a staged combustion cycle. It has a single combustion chamber that provides thrust vector control by gimbaling of the nozzle in two axis by +/- 8°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family.

Rocket design meant for use on the Titan I missile

Re-usable rocket booster proposed for Angara carrier rocket

The RD-193 () is a high performance single-combustion chamber rocket engine, developed in Russia from 2011 to 2013. It is derived from the RD-170 originally used in the Energia launcher.

rocket aircraft engine

The XLR50 was a pump-fed liquid-propellant rocket engine burning RP-1 and LOX in a gas generator cycle developed by General Electric. It was used to power the first stage of the Vanguard rockets on the Vanguard project. As was common to engines based on the V-2 experience, the turbine was driven by steam generated by catalytic decomposition of H2O2 and the combustion chamber was regeneratively cooled. The engine was gimbaled to supply thrust vectoring. Also, the exhaust gases of the turbine were ducted to dual auxiliary nozzles that acted as verniers to enable roll control of the rocket.

The RD-0110R (, GRAU index: 14D24) was a rocket engine burning kerosene in liquid oxygen in a gas generator combustion cycle. It had four nozzles that can gimbal up to 45 degrees in a single axis and was used as the vernier thruster on the Soyuz-2.1v first stage. It also had heat exchangers that heat oxygen and helium to pressurize the LOX and RG-1 tanks of the Soyuz-2.1v first stage, respectively. The oxygen was supplied from the same LOX tank in liquid form, while the helium was supplied from separate high pressure bottles (known as the T tank).

The RD801 (Ukrainian: ) is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene (RG-1) in a staged combustion cycle. It has a single combustion chamber that provides thrust vector control by gimbaling of the nozzle in two axis by +/- 6°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family.