RD-270 (Russian: Раке́тный дви́гатель 270, Rocket Engine 270, 8D420) was a single-chamber liquid-bipropellant rocket engine designed by Energomash (USSR) in 1960–1970. It was to be used on the first stages of proposed heavy-lift UR-700 and UR-900 rocket families, as well as on the N1. It has the highest thrust among single-chamber engines of the USSR, 640 metric tons at the surface of Earth. The propellants used are unsymmetrical dimethylhydrazine (UDMH) and nitrogen tetroxide (N2O4). The chamber pressure was among the highest considered, being about 26 MPa. This was achieved by applying full-flow staged combustion cycle for all the incoming mass of fuel, which is turned into a gas and passes through multiple turbines before being burned in the combustion chamber. This allowed the engine to achieve a specific impulse of 301 s (2.95 km/s) at the Earth's surface.
The engine testing was underway when the decision was made to cancel the program. Development was stopped with all other work on corresponding rocket projects on 11 December 1970.
The development of RD-270 started on 26 June 1962. Preliminary investigations and development of the engine and its further production were performed under the guidance of Valentin Glushko and finished in 1967. It became the most powerful engine in the world to date that used high-boiling propellant. During 1967–1969, several test firings were performed with experimental engines that were adapted to work at sea level and had a short nozzle. In total, 27 test firings were performed with 22 engines, three engines were tested twice, and one of them was tested three times.[2] All works stopped later together with corresponding activities on the UR-700 project.
The RD 270 was also considered for the R-56 rocket (although never formally adopted) until work on the design stopped in June 1964.[2][3]
During development, Glushko studied the use of pentaborane "zip" propellants in a modified RD-270M engine. This would have created immense toxicity problems but increased the specific impulse of the engine by 42 seconds (0.41 km/s).[4]
Designedit
The engine throttle range was 95–105%, the thrust vector control range was ±12° (project R-56) and ±8° for UR-700 rocket family. The oxidizer-to-fuel ratio was 2.67 and can be changed by up to 7%.[1]
To achieve such a high specific impulse and pressure in combustion chamber as RD-270 has, two circuits of full-flow staged combustion cycle were applied. The pair of turbines with preburners turns the fuel into the gaseous form and circulates all of the fuel components. One of the turbines uses the fuel-rich gas to power a fuel pump, another one uses the oxidizer-rich gas to power the oxidizer pump. As a result, the main combustion chamber (MCC) burns only generator gas. The engine controller regulates the functions of the two independent fuel and oxidizer circuits.[1]
With the purpose to cool MCC it has layered wall structure with four internal belts of slots. Some parts of nozzles are covered by zirconium dioxide for thermal protection.[1]
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This article needs additional citations for verification Please help improve this article by adding citations to reliable sources Unsourced material may be challenged and removed Find sources RD 270 news newspapers books scholar JSTOR November 2018 Learn how and when to remove this message RD 270 Russian Rake tnyj dvi gatel 270 Rocket Engine 270 8D420 was a single chamber liquid bipropellant rocket engine designed by Energomash USSR in 1960 1970 It was to be used on the first stages of proposed heavy lift UR 700 and UR 900 rocket families as well as on the N1 It has the highest thrust among single chamber engines of the USSR 640 metric tons at the surface of Earth The propellants used are unsymmetrical dimethylhydrazine UDMH and nitrogen tetroxide N2O4 The chamber pressure was among the highest considered being about 26 MPa This was achieved by applying full flow staged combustion cycle for all the incoming mass of fuel which is turned into a gas and passes through multiple turbines before being burned in the combustion chamber This allowed the engine to achieve a specific impulse of 301 s 2 95 km s at the Earth s surface RD 270 RD 270 Country of originUSSR RussiaDate1969DesignerV Glushko USSR Ukrainian Soviet Socialist RepublicManufacturerEnergomashSuccessorRD 270MStatusRetiredLiquid fuel enginePropellantN2O4 UDMHCycleFull flow staged combustionPerformanceThrust vacuum6 710 MN 1 508 000 lbf 1 Thrust sea level6 270 MN 1 410 000 lbf 1 Thrust to weight ratio189 91Chamber pressure26 1 MPa 3 790 psi 1 Specific impulse vacuum322 s 3 16 km s Specific impulse sea level301 s 2 95 km s DimensionsLength194 in 4 900 mm Diameter132 in 3 400 mm Dry weight3 370 kg 7 430 lb 1 Used in1st stage of proposed UR 700 and UR 900 The engine testing was underway when the decision was made to cancel the program Development was stopped with all other work on corresponding rocket projects on 11 December 1970 Contents 1 History 2 Design 3 See also 4 References 5 External linksHistory editThe development of RD 270 started on 26 June 1962 Preliminary investigations and development of the engine and its further production were performed under the guidance of Valentin Glushko and finished in 1967 It became the most powerful engine in the world to date that used high boiling propellant During 1967 1969 several test firings were performed with experimental engines that were adapted to work at sea level and had a short nozzle In total 27 test firings were performed with 22 engines three engines were tested twice and one of them was tested three times 2 All works stopped later together with corresponding activities on the UR 700 project The RD 270 was also considered for the R 56 rocket although never formally adopted until work on the design stopped in June 1964 2 3 During development Glushko studied the use of pentaborane zip propellants in a modified RD 270M engine This would have created immense toxicity problems but increased the specific impulse of the engine by 42 seconds 0 41 km s 4 Design editThe engine throttle range was 95 105 the thrust vector control range was 12 project R 56 and 8 for UR 700 rocket family The oxidizer to fuel ratio was 2 67 and can be changed by up to 7 1 To achieve such a high specific impulse and pressure in combustion chamber as RD 270 has two circuits of full flow staged combustion cycle were applied The pair of turbines with preburners turns the fuel into the gaseous form and circulates all of the fuel components One of the turbines uses the fuel rich gas to power a fuel pump another one uses the oxidizer rich gas to power the oxidizer pump As a result the main combustion chamber MCC burns only generator gas The engine controller regulates the functions of the two independent fuel and oxidizer circuits 1 With the purpose to cool MCC it has layered wall structure with four internal belts of slots Some parts of nozzles are covered by zirconium dioxide for thermal protection 1 See also editRocket engine Staged combustion cycle RD 253 engine for Universal Rocket family RD 170 comparable Russian RP 1 LOX engine with four combustion chambers F 1 comparable RP 1 LOX engine Raptor comparable methane engine Proton rocket successor of one of universal rocket series N1 Carrier 1 alternative rocket for Soviet lunar projects References edit a b c d e f g RD 270 8D420 in Russian a b Harvey Brian 2007 Soviet and Russian Lunar Exploration Springer Praxis pp 61 62 ISBN 0387218963 Hendrickx Bart 2011 Heavy Launch Vehicles of the Yangel Design Bureau Part 2 PDF Journal of the British Interplanetary Society 64 2 24 Archived from the original PDF on 23 November 2015 Astronautix RD 270 Archived 2009 04 30 at the Wayback Machine External links editArticle title Retrieved from https en wikipedia org w index php title RD 270 amp oldid 1183319588, wikipedia, wiki, book, books, library,
