RD-170

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"RD-175" redirects here. For the Minolta RD-175, see Minolta RD-175.
RD-170
RD-170 rocket engine.jpg
RD-170 rocket engine model on exhibition in Saint Petersburg's Museum of Space and Missile Technology.
Country of origin Soviet Union/Russian Federation
Manufacturer NPO Energomash
Application Main engine
Liquid-fuel engine
Propellant LOX / RP-1 (Soviet/Russian equivalent)
Cycle Staged combustion
Configuration
Nozzle ratio 36.87[1]
Performance
Thrust (vac.) 7.887 MN (1,773,000 lbf)
Thrust (SL) 7.550 MN (1,697,300 lbf) [1]
Thrust-to-weight ratio 82
Chamber pressure 245 bar[1]
Isp (vac.) 338 s (3.31 km/s)
Isp (SL) 309 s (3.03 km/s)
Burn time 150 s[1]


The RD-170 (РД-170, Ракетный Двигатель-170, Rocket Engine-170) is the world's most powerful liquid-fuel rocket engine, designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns the Russian equivalent of RP-1 fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbo pump rated at 170 MW,[2] in a staged combustion cycle.[2]

Shared turbopump[edit]

Several Soviet and Russian rocket engines use the approach of clustering small combustion chambers around a single turbine and pump. During the early 1950s, many Soviet engine designers, including Valentin P. Glushko, faced problems of combustion instability, while designing bigger thrust chambers. At that time they solved the problem by using a cluster of smaller thrust chambers.

Variants[edit]

RD-170[edit]

The RD-170 engine was developed for use the on the Energia launch vehicle, both of which were in production only for a short time.

RD-171[edit]

RD-171 model

Building on the technology from the Energia launch vehicle the Zenit rocket was developed, which uses a RD-170 variant, the RD-171. While the RD-170 had nozzles which swiveled on only one axis, the RD-171 swivels on two axes. Models called the RD-172 and RD-173 were proposed upgrades providing additional thrust, but they were never built.

RD-180[edit]

Main article: RD-180

This variant uses only 2 combustion chambers instead of the 4 of the RD-170. The RD-180 used on the Atlas V, replaced the three engines used on early Atlas rockets with a single engine and achieved significant payload and performance gains. This engine had also been chosen to be the main propulsion system for the first stage of the now cancelled Russian Rus-M rocket.[3]

RD-191[edit]

Main article: RD-191

Yet another variant, the single-chambered RD-191, is used in the Russian Angara rocket.[4]

RD-151[edit]

The RD-151 is the RD-191 with thrust reduced from 196 to 170 tonnes. This engine was test-fired on July 30, 2009. The first flight test of this engine was conducted on August 25, 2009 as part of the first launch of South Korean Naro-1 rocket. The first stage of the Naro-1 rocket is made of the Universal Rocket Module (URM) from the Angara rocket.[5][6]

RD-193[edit]

RD-193 was proposed as a replacement for the NK-33, which is being used in the Soyuz-2-1v vehicle. On October 19, 2012, NPO Energomash announced that three days earlier, an experimental RD-193 engine completed its fifth live firing without leaving test bench No. 2 at the company's NIK-751 test facility. During five tests, the engine burned for a total of 678 seconds. Following the tests, the engine was to be disassembled and checked for any defects to clear it for further tests, NPO Energomash said. In 2013, NPO Energomash announced that tests of RD-193 engine had been completed.

RD-180M,V and RD-175[edit]

On 28 July 2011 NPO Energomash summarised the results of the work on Rus-M rocket engine and considered the possibility of construction several new variants of RD-170 family engines.[7] According to the information, new and proposed variants will be marked as:

  • RD-180M for manned Atlas V rocket.
  • RD-180V for Rus-M rocket.
  • RD-175 with 9800 kN thrust for proposed Energia-K rocket.[8]

Specifications[edit]

  • 4 combustion chambers, 4 nozzles
  • 1 set of turbines and pumps - Turbine produces approximately 257,000 hp (192 MW); equivalent to the power output of 3 nuclear-powered icebreakers
  • Ignition: Hypergolic
  • Vacuum thrust of 1,773,000 lbf (7,887 kN)
  • Vacuum Isp of 338 s (3.31 km/s)
  • Sea Level Isp of 309 s (3.03 km/s)
  • Weight: 9,750 kg (21,500 lb)
  • Thrust to weight ratio: 82

See also[edit]

References[edit]

External links[edit]