The CFM LEAP (Leading Edge Aviation Propulsion) engine is a high-bypass turbofan engine developed by CFM International, a joint venture between General Electric (GE) and Safran Aircraft Engines. Propulsive efficiency for a turbofan engine like the CFM LEAP is a measure of how effectively the engine converts the thermal energy of combusted fuel into useful thrust.
For the CFM LEAP engine, specific details such as the specific impulse, mass flow rate, and combustion characteristics would need to be obtained from engine performance data or technical specifications. The efficiency of a specific engine can be influenced by design parameters, operating conditions, and other factors.
The propulsive efficiency is a crucial parameter in evaluating the performance of a rocket engine, indicating how well it converts propellant energy into useful thrust. Practical rocket engines often have propulsive efficiencies less than 100% due to factors like incomplete combustion, heat losses, and other inefficiencies in the propulsion system.
The propulsive efficiency () is defined by the following formula:
where,
- is the propulsive efficiency,
- is the thrust produced by the rocket engine,
- is the effective exhaust velocity of the rocket,
- ṁ is the mass flow rate of the propellants,
- is the specific impulse of the rocket engine,
- g0 is the acceleration due to gravity (approximately 9.81 m/s²).