CFE738
The CFE738 is a twin-shaft turbofan engine that was developed for business aircraft and is used in the Dassault Falcon 2000 . The manufacturer of this engine is the CFE Company , a joint venture between General Electric and Garrett / AlliedSignal (later Honeywell ). Because it is sold by General Electric, it is also referred to as General Electric CFE738 or GE38 .
history
The development of the engine began in 1987 after the establishment of the CFE Company. The basis was the GE development of a turboprop engine under the name T407 or GLC38 for the Lockheed P-7 with a maximum take-off power of 4475 kW. GE supplied the core engine and engine control and Allied Signal / Honeywell supplied the fan, the low-pressure turbine and the gearbox for the auxiliary drives. In the course of 1991 the turbine was tested for the first time in flight. On December 17, 1993, FAA type certification was achieved for the CFE738-1. More than 400 CFE738 engines had been built by 2007.
Together with the GE27 technology demonstrator, which was tested in 1983, the engine serves as the basis for a helicopter turbine named GE38-1B for the Sikorsky CH-53 K and could also be used in the future European heavy-duty helicopter FTH [obsolete] . Sikorsky selected the turbine against the AE 1107 Rolls-Royce and the PW100 of Pratt & Whitney Canada in December of 2006. The first run of this 5,595 kW engine was planned for the beginning of 2009 and then took place on June 19, 2009 in Lynn (Massachusetts) .
construction
The CFE738 consists of a single-stage fan with 28 blades made of titanium which is driven by a three-stage low-pressure turbine. In the GE38-1B, the low-pressure turbine drives the output shaft instead of the fan. The five-stage axial compressor, which is supplemented by a single-stage radial compressor , is driven by a two-stage cooled high-pressure turbine. The engine has a maximum total pressure ratio of 35: 1. The bypass ratio is 5.3 and the starting thrust is 24.9 kN (rating ISA + 15C). The combustion chamber is ring-shaped and has 15 injection nozzles. The mixer has 20 mixing troughs. It is possible to add a thrust reverser. The engine is controlled by a double redundant FADEC system. The service life of a GE38-1B is 6000 hours.
Technical specifications
- Fan / compressor stages: 1/5 axial + 1 radial
- High pressure / low pressure turbine stages: 2/3
- Fan diameter: ~ 0.9 m (0.69 m for the GE38-1B)
- Length: 2.51 m (1.46 m for the GE38-1B)
- Dry weight: 600 kg
- Thrust (at sea level): 26.33 kN
- Specific fuel consumption (sea level / cruise): 10.54 / 18.27 mg / Ns
- Total pressure ratio (sea level / cruising altitude): 23: 1/30: 1
- Sidestream ratio: 5.3
- Air flow: 109 kg / s