Volvo RM12
| RM12 | |
|---|---|
 |
|
| Type | Turbofan |
| National origin | Sweden/United States |
| Manufacturer | Volvo Aero/GKN Aerospace General Electric |
| First run | 1978 |
| Major applications | Saab JAS 39 Gripen |
| Developed from | General Electric F404 |
The Volvo RM12 is a low-bypass afterburning turbofan jet engine developed for the Saab JAS 39 Gripen fighter. A version of the General Electric F404, the RM12 was produced by Volvo Aero (now GKN Aerospace Engine Systems).
Contents
Design and development
Produced by Volvo Aero (now GKN Aerospace Engine Systems), the RM12 is a derivative of the General Electric F404-400. Changes from the standard F404 includes greater reliability for single-engine operations (including more stringent birdstrike protection), increased thrust, and the adoption of a full authority digital engine control (FADEC) system.[1][2] Several subsystems and components were also redesigned to reduce maintenance demands.[3] The air intakes of the engine were designed to minimize radar reflection from the compression fan, reducing the radar cross section of the aircraft overall.[2] The F404's analogue Engine Control Unit was replaced with the Digital Engine Control – jointly developed by Volvo and GE – which communicates with the cockpit through the digital data buses and, as redundancy, mechanical calculators controlled by a single wire will regulate the fuel-flow into the engine. These mechanical backup systems remain in the new Full Authority Digital Engine Control (FADEC) which Volvo began developing in 1996.[2] General Electric produces 50% of the engine. Elements such as the fan/compressor discs and case, compressor spool, hubs, seals, and afterburner are manufactured in Sweden, final assembly also taking place there.[2]
Applications
- JAS 39 Gripen
- IAI Nammer (as designed, not built)
Specifications (Volvo RM12)
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General characteristics
- Type: Afterburning turbofan
- Length: 4.04m (159 in)
- Diameter: 0.889 m (35 in)
- Dry weight: 1055 kg (2326 lb)
Components
- Compressor: Axial compressor with 3 fan and 7 compressor stages
- Combustors: annular
- Turbine: 1 low-pressure and 1 high-pressure stage
Performance
- Maximum thrust:
- Lua error in Module:Convert at line 1851: attempt to index local 'en_value' (a nil value). military thrust
- Lua error in Module:Convert at line 1851: attempt to index local 'en_value' (a nil value). with afterburner
- Overall pressure ratio: 27.5:1
- Bypass ratio: 0.31:1
- Air mass flow: 68kg/s
- Specific fuel consumption:
- Military thrust: 23.9 mg/Ns (0.844 lb/(lbf*hr))
- Full afterburner: 50.6 mg/Ns (1.79 lb/(lbf*hr))
- Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)
See also
- Related development
- Comparable engines
- Related lists
References
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