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astronautix.com RD-170

RD-170
RD-170 -

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Manufacturer Name: RD-170. Government Designation: 11D520. Designer: Glushko. Developed in: 1981-93. Application: Energia strap-on. Used on stages: Energia Strapon, Vulkan 0. Used on launch vehicles: Energia, Energia M, Vulkan. Propellants: Lox/Kerosene Thrust(vac): 806,000 kgf. Thrust(vac): 7,903.00 kN. Isp: 337 sec. Isp (sea level): 309 sec. Burn time: 150 sec. Mass Engine: 9,750 kg. Diameter: 4.0 m. Length: 3.8 m. Chambers: 4. Chamber Pressure: 245.00 bar. Area Ratio: 36.87. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Out of Production. First Flight: 1987. Last Flight: 1988. Flown: 8. References: 225 , 287 , 317 , 342 , 347 .

The RD-170 and RD-171 engines consisted of 4 chambers, 1 turbo-pump and 2 gas generators were developed simultaneously, the difference being one-plane gimballing in the RD-170 used in the Energia launch vehicle strap-ons versus two-plane gimablling in the RD-171 used on the first stage of the Zenit launch vehicle. The RD-171 can be gimballed using bellows to 6 degrees normally but it has reached 8-10 degrees in tests. The chamber conditions are 300 atmosphere pressure and at a 400 degrees C oxygen-rich gas mixture - very dangerous conditions. The RD-170 was very hard to prove and many designers thought it couldn’t be done. The first stage strap-ons were recovered under parachutes and returned to Baikonur for study. The engine was designed for 10 reuses but tests showed they could stand up to 20 burns.

The 170 MW turbo-pump is equivalent to three nuclear ice breakers. Developed 1973-1985. Figures are per chamber. Engine Cycle: staged combustion. Oxidizer: LOX at 432 kg/s. Fuel: Kerosene at 166.2 kg/s. The engine can be throttled back to 56% of full thrust. Chamber Mass: 480 kg. Burn Time: 140-150 sec. Diameter is per chamber.


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Last update 12 March 2001.
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