Maximum Takeoff Thrust
24.7 kN
Architecture
| Fan |
Fan Stages
—
|
Fan Blades
—
|
Fan Technology
—
|
Fan Pressure Ratio
—
|
| Gearbox |
Geared Fan
No |
Gear
—
|
Reduction Ratio
—
|
| LP compressor |
Low-Pressure Compressor Stages
—
|
Low-Pressure Compressor Technology
—
|
BP Compressor Pressure Ratio
—
|
| IP compressor |
Intermediary-Pressure Compressor Stages
—
|
Intermediary-Pressure Compressor Technology
—
|
IP Compressor Pressure Ratio
—
|
| HP compressor |
High-Pressure Compressor Stages
—
|
High-Pressure Compressor Technology
—
|
HP Compressor Pressure Ratio
—
|
| Combustor |
Combustion Chamber
Annular |
| HP turbine |
High Pressure Compressor Stages
—
|
High-Pressure Turbine Technology
—
|
| IP turbine |
Intermediary-Pressure Turbine Stages
—
|
Intermediary-Pressure Turbine Technology
—
|
| LP turbine |
Low-Pressure Turbine Stages
—
|
Low-Pressure Turbine Technology
—
|
| Whole engine |
Streams
2 |
Bypass Ratio
4.2 |
Overall Pressure Ratio
—
|
Afterburner
No |
Pictures
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All data (17 fields)
- Name
- Rolls-Royce RB401
- Aircraft Engine Manufacturer
- Rolls-Royce
- Aircraft Engine Type
- Turbofan
- Dry Weight (kg)
- 446.7885
- Diameter (mm)
- 822.96
- Length (mm)
- 1544.32
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/Rolls-Royce_RB401
- Fuel
- Hydromechanical with provision for electronic monitoring
- Geared Fan
- No
- Combustion Chamber
- Annular
- Afterburner
- No
- Streams
- 2
- Bypass Ratio
- 4.2
- Maximum Takeoff Thrust (kN)
- 24.7
- Thrust To Weight
- 5.6
- Compressor Description
- Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes
- Turbine Description
- Two-stage LP, single-stage HP with air-cooled blades