Status: Hardware. Date: 2006-2009. Thrust: 614.70 kN (138,190 lbf). Specific impulse: 304 s. Specific impulse sea level: 275 s. Burn time: 169 s.
The Merlin 1C, was developed for the Falcon 9 and would also be used in the stretched Falcon 1e first stage from 2010. It differed from the Merlin 1A in that high pressure kerosene fuel flowed through the walls of the combustion chamber and exhaust nozzle before being injected into the combustions chamber. This provided significant cooling, permitting the engine to operate at a higher level of performance. The turbo-pump also provided the high pressure kerosene for the hydraulic actuators, eliminating the need for a separate hydraulic power system. Additionally, actuating the turbine exhaust nozzle provided roll control during flight. Combining these three functions into one device, and verifying its operation before the vehicle was allowed to lift off, provided significant improvement in system-level reliability.
Thrust (sl): 555.900 kN (124,971 lbf). Propellant Formulation: Lox/RP-1. Area Ratio: 14.5. Thrust to Weight Ratio: 150.