CFE CFE738

The CFE738 is a two -spool turbofan engine, which was developed for business jets and is used in the Dassault Falcon 2000. Manufacturer of this engine is the CFE Company, a joint venture between General Electric and Garrett / AlliedSignal (later Honeywell). Because it is marketed 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 creation of the CFE Company. As a basis the GE development of a turboprop engine was used under the name of 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 the fan, low pressure turbine and the gear for the auxiliary drives. During the year 1991, the turbine was first flight tested. On 17 December 1993, the FAA type certificate for the CFE738 -1 could be achieved. The engine is used together with the proven technology demonstrator in 1983 GE27 as the basis for a helicopter turbine named GE38 -1B for the Sikorsky CH -53K and could also come in the future European heavy -lift helicopter HTH used. Sikorsky selected the turbine against the AE 1107 Rolls- Royce and Pratt & Whitney Canada PW100 from in December 2006. The first run of this 5,595 -kW drive was planned for early 2009 and then was held in Lynn (Massachusetts ) on 19 June 2009. Series production is planned for spring 2011.

Meanwhile, more than 400 pieces of CFE738 - engine have been built.

Construction

The CFE738 consists of a single-stage fan 28 made ​​of titanium sheets which is driven by a three-stage low pressure turbine. When GE38 -1B compressor drives the output shaft instead of the fans. The five-stage axial compressor which is complemented 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 pass ratio is 5.3 and the takeoff thrust 24.9 kN (Rating ISA 15 C). The combustion chamber is an annular shape and has 15 injectors. The mixer has 20 mixing channels. It is possible to grow a thrust reverser. The engine is controlled by a two-fold redundant FADEC system. The life of a GE38 -1B is located at 6000 hours.

Specifications

• Fan / compressor stages 1/5 1 axially radially
• Hochdruck-/Niederdruck-Turbinenstufen: 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 ( altitude / cruise ): 10.54 / 18.27 mg / Ns
• Overall pressure ratio (sea level / cruising altitude ): 23:1 / 30:1
• Bypass ratio: 5.3
• Air flow rate: 109 kg / s