Maximum Takeoff Thrust
76.4 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
—
|
| 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
Yes |
Pictures
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All data (14 fields)
- Name
- Lyulka AL-21
- Aircraft Engine Manufacturer
- Lyulka-Saturn
- Aircraft Engine Type
- Turbojet
- Dry Weight (kg)
- 1700
- Diameter (mm)
- 1000
- Length (mm)
- 5300
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/Lyulka_AL-21
- Geared Fan
- No
- Afterburner
- Yes
- Streams
- 1
- Maximum Takeoff Thrust (kN)
- 76.4
- Thrust To Weight
- 4.6
- Compressor Description
- Two-spool 14-stage axial compressor with variable stator vanes. 10 guide vanes with rotating blades (1 inlet vane, 4 first stages, 5 last stages.
- Turbine Description
- Two-stage high pressure, single-stage low pressure