RD-170
Sign in to saveThe 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.
Key facts
- Rocket engine.name
- RD-170
- Rocket engine.image
- RD-170.jpg
- Rocket engine.caption
- Model of an RD-170 rocket engine, shown upside down
- Rocket engine.country_of_origin
- Soviet Union
- Rocket engine.designer
- NPO Energomash
- Rocket engine.manufacturer
- NPO Energomash
- Rocket engine.purpose
- Main engine
- Rocket engine.associated
- Energia
- Rocket engine.successor
- RD-180RD-191
- Rocket engine.status
- Retired
- Rocket engine.type
- liquid
- Rocket engine.oxidiser
- LOX
- Rocket engine.fuel
- RP-1
- Rocket engine.mixture_ratio
- 2.63
- Rocket engine.cycle
- Oxidizer-rich staged combustion
- Rocket engine.combustion_chamber
- 4
- Rocket engine.nozzle_ratio
- 36.87
- Rocket engine.throttle_range
- 40–100%
via Wikipedia infobox
Article
12 sectionsContents
- Shared turbopump
- Variants
- RD-170
- RD-171
- RD-171MV
- Dual-chamber derivative
- Single-chamber derivative
- Proposed variants
- Specifications
- See also
- References
- External links
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.
== Shared turbopump == 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.