General Electric F103
| CF6 | |
|---|---|
 |
|
| CF6 turbofan at the KLM engine shop | |
| Type | Turbofan |
| Manufacturer | GE Aviation |
| First run | 1971 |
| Major applications |
Airbus A300 Airbus A310 Airbus A330 Boeing 747 Boeing 767 McDonnell Douglas DC-10 McDonnell Douglas MD-11 Lockheed C-5M Super Galaxy |
| Developed from | General Electric TF39 |
| Developed into |
General Electric LM6000 CFM International CFM56 |
The General Electric CF6 is a family of high-bypass turbofan engines produced by GE Aviation. Based on the TF39, the first high-power high-bypass jet engine, the CF6 powers a wide variety of civilian airliners. The basic engine core also powers the LM2500, LM5000, and LM6000 marine and power generation turboshafts.
GE intends to replace the CF6 family with the GEnx.
After developing the TF39 for the C-5 Galaxy in the late 1960s, GE offered a more powerful variant for civilian use, the CF6, and quickly found interest in two designs being offered for a recent Eastern Airlines contract, the Lockheed L-1011 and McDonnell Douglas DC-10. The Lockheed eventually selected the Rolls-Royce RB211, but Douglas stuck with the CF6 and the DC-10 entered service in 1971. It was also selected for versions of the Boeing 747. Since then, the CF6 has powered versions of the Airbus A300, A310 and A330, Boeing 767, and McDonnell Douglas MD-11.
The high bypass of the CF6 represented a historic breakthrough in fuel efficiency.
The CF6-6 was a development of the military TF39. It was first used on the McDonnell Douglas DC-10-10.
This initial version of the CF6 has a single-stage fan with one core booster stage, driven by a 5-stage LP (low pressure) turbine, turbocharging a 16-stage HP (high pressure) axial compressor driven by a 2-stage HP turbine; the combustor is annular; separate exhaust nozzles are used for the fan and core airflows. The 86.4-in (2.19-m) diameter fan generates an airflow of 1,300 lb/s (590 kg/s), resulting in a relatively high bypass ratio of 5.72. The overall pressure ratio of the compression system is 24.3. At maximum take-off power, the engine develops a static thrust of 41,500 lb (185.05 kN).
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