Lankan Ranger
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JF-17 Expected to Powered by RM 12 Engine: Report
According to the news coming from several Asian Defense Analysts.
Pakistan Aeronautical Complex favors General Electric RM-12 Engine to replace Russian RD-93 Engine.
RM 12 Engine
The Volvo Aero modification of the F404 consists increased performance, greater resistance to bird strikes and designed for single engine use safety criteria.
60% of the engine parts are produced by GE and then shipped to Sweden for final assembly. The fan/compressor discs and case, compressor spool, hubs, seals and the entire afterburner are designed and produced in Sweden.
RM 12 Engine Specifications
General characteristics
Type: Afterburning turbofan
Length: 154 in (3,912 mm)
Diameter: 35 in (889 mm)
Dry weight: 2,282 lb (1,036 kg)
Components
Compressor: Axial compressor with 3 fan and 7 compressor stages
Bypass ratio: 0.34:1
Turbine: 1 low-pressure and 1 high-pressure stage
Performance
Maximum thrust:
11,000 lbf (48.9 kN) military thrust
17,700 lbf (78.7 kN) with afterburner
Overall pressure ratio: 26:1
Specific fuel consumption:
Military thrust: 0.81 lb/(lbf•h) (82.6 kg/(kN•h))
Full afterburner: 1.74 lb/(lbf•h) (177.5 kg/(kN•h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)
According to the news coming from several Asian Defense Analysts.
Pakistan Aeronautical Complex favors General Electric RM-12 Engine to replace Russian RD-93 Engine.
RM 12 Engine
The Volvo Aero modification of the F404 consists increased performance, greater resistance to bird strikes and designed for single engine use safety criteria.
60% of the engine parts are produced by GE and then shipped to Sweden for final assembly. The fan/compressor discs and case, compressor spool, hubs, seals and the entire afterburner are designed and produced in Sweden.
RM 12 Engine Specifications
General characteristics
Type: Afterburning turbofan
Length: 154 in (3,912 mm)
Diameter: 35 in (889 mm)
Dry weight: 2,282 lb (1,036 kg)
Components
Compressor: Axial compressor with 3 fan and 7 compressor stages
Bypass ratio: 0.34:1
Turbine: 1 low-pressure and 1 high-pressure stage
Performance
Maximum thrust:
11,000 lbf (48.9 kN) military thrust
17,700 lbf (78.7 kN) with afterburner
Overall pressure ratio: 26:1
Specific fuel consumption:
Military thrust: 0.81 lb/(lbf•h) (82.6 kg/(kN•h))
Full afterburner: 1.74 lb/(lbf•h) (177.5 kg/(kN•h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)