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PowerJet SaM 146


PowerJet-SaM-146

 

The PowerJet SaM146 is a turbofan engine produced by the PowerJet joint venture between Snecma of France and NPO Saturn of Russia. Snecma is in charge of the core engine, control system (FADEC), transmissions (accessory gearbox, transfer gearbox), overall engine integration and flight testing. The SaM146 design is based on the CFM56 and has been conceived to meet customer requirements regarding fuel burn, cost of operation and dispatch reliability.

The core was developed by Snecma, drawing on its M88 ‘hot section’ military engine experience and the DEM21 core demonstrator project – with its six-stage compressor and single-stage, high-pressure turbine with active blade-tip clearance control – and various other modern design features (such as single-piece bladed disks).

The SaM146 provides 62 to 77.8KN of thrust (6,200 to 7,700 kg). 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. 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.

First run in 2008, the SaM146 utilizes 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.

Blisk technology is used to improve fuel economy and lower maintenance.
 
On 23 June 2010, it was announced that EASA certified PowerJet for its SaM146 engine. It gained Russian certification in August 2010.

 

Applications:
SaM146 1S15
Sukhoi Superjet 100/75

SaM146 1S17
Sukhoi Superjet 100/95

SaM146 1S18
Sukhoi Superjet 100/95LR

 

Specifications:
SaM146-1S17
Type: Twin spool, High-bypass turbofan
Length: 86 in (2.2 m)
Diameter: 48.2 in (1.22 m)
Dry weight: 1,708 kg (3,765 lb)
Compressor: 1 stage fan, 3-stage low pressure, 6-stage high pressure axial compressor
Combustors: Annular
Turbine: 1-stage high pressure, 3-stage low pressure
Fuel type: Jet A, Jet A-1, TS-1, RP
Maximum thrust: 76.84 kN (17,270 lbf) (Maximum takeoff thrust)
Overall pressure ratio: 23.8:1
Bypass ratio: 4.43:1
Specific fuel consumption: 0.374 lb/lbf-hr (Dry) and 0.629 lb/lbf-hr (Cruise)
Thrust-to-weight ratio: 5.3:1

 

 

 

 

 

 


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