Rocketdyne LR101
Government Designation:
LR101-11. Designer: Rocketdyne. Propellants:
Lox/Kerosene Thrust(vac): 540 kgf. Thrust(vac): 5.30 kN. Isp: 246 sec. Isp (sea
level): 209 sec. Burn time: 283 sec. Mass Engine: 22 kg. Chambers: 1. Area
Ratio: 5.60. Combustion Chamber Materials: 347 CRES austenitic stainless steel.
Country: USA. Status: In Production. LR101-NA-11 at 21.8 kg mass,
4.63/5.30 kN sea level/vac thrust, 209/246 sec sea level/vac Isp, 1.8 mixture
ratio, 5.6 expansion ratio(9.8 cm exit diameter), 283 sec Burn Time.
Three main parts
The chamber. Looking downward through the chamber towards the nozzle.
Injector. Lox flows through top, kerosene through side holes.
LOX dome
Injector installed on chamber.
The whole engine.
