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
cannular 10 flame tubes |
| 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
1 |
Bypass Ratio
—
|
Overall Pressure Ratio
—
|
Afterburner
No |
Pictures
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Airplanes
All data (15 fields)
- Name
- Rolls-Royce Olympus
- Aircraft Engine Manufacturer
- Bristol Engine Company (Bristol)
- Aircraft Engine Type
- Turbojet
- Dry Weight (kg)
- 1639.736
- Diameter (mm)
- 1016
- Length (mm)
- 3228.34
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/Rolls-Royce_Olympus
- Fuel
- AVTUR or AVTAG
- Geared Fan
- No
- Combustion Chamber
- cannular 10 flame tubes
- Afterburner
- No
- Streams
- 1
- Thrust To Weight
- 3.04
- Compressor Description
- axial 6 LP stages, 8 HP stages
- Turbine Description
- HP single stage, LP single stage