PowerJet SaM146
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The PowerJet SaM146 (Двигатель SaM146) is a turbofan engine produced by the PowerJet joint venture between Snecma of France and NPO Saturn in the Russian Federation.[1] Snecma is in charge of the core engine, control system (FADEC), transmissions (accessory gearbox, transfer gearbox), overall engine integration and flight testing. NPO Saturn is responsible for the components in the low pressure section and engine installation on the Sukhoi Superjet 100 regional aircraft and ground testing.
The SaM146 has been designed from the ground up to power regional jets. In keeping with the design and development of jet engines from manufacturers like Pratt & Whitney Canada, General Electric and Rolls Royce, the engine has been conceived to meet customer requirements regarding fuel burn, cost of operation and dispatch reliability. The SaM146 is technologically on a par with rivals from General Electric and Rolls Royce.
The SaM146 is a 14,000 to 17,500 pounds of thrust/62 to 77.8 kN thrust class engine, which means it can power regional aircraft in the 60 to 100 seat class. In April 2003, Sukhoi Civil Aircraft Company selected the SaM146 for its Superjet 100 regional aircraft, to be produced in 75 and 95-seat versions.
Snecma's participation in the project has brought a design that has much in common with the CFM56 jointly developed by Snecma and General Electric. The SaM146 utilises a single-stage turbine and as a new design has been developed to meet current and projected environmental standards, including regulations of the ICAO Committee of Aviation Environmental Protection Sixth Session (CAEP VI), set to become effective in 2008 [2].
As is the norm with modern jet engines - even those destined for regional jets - PowerJet intends to offer the usual range of support services for operators.
[edit] Specifications
General characteristics
- Type: axial flow, twin-shaft, high-bypass turbofan engine
- Length: 2,070 mm (81.5 in)
- Diameter: overall: - ; fan: 48.2 in (1,220 mm)
- Dry weight:
Components
- Compressor: axial: 1 fan, bypass ratio 4.43, 3 low pressure stages, 6 high pressure stages
- Turbine: axial: 3 low pressure stages, 1 high pressure stage
Performance
- Thrust: 14,000 to 17,500 lbf (62.3 to 77.8 kN)
- Specific fuel consumption: 0.629 lb of fuel/hour per pound of thrust at cruise
- Power-to-weight ratio:
[edit] References
[edit] External links
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