Maximum Takeoff Thrust
64 kN
Specific Fuel Consumption
25.492 g/(kN·s)
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
0.36 |
Overall Pressure Ratio
—
|
Afterburner
Yes |
Pictures
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Airplanes
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All data (17 fields)
- Name
- Snecma M53
- Aircraft Engine Manufacturer
- SNECMA
- Aircraft Engine Type
- Turbofan
- Dry Weight (kg)
- 1515
- Diameter (mm)
- 796
- Length (mm)
- 5070
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/Snecma_M53
- Geared Fan
- No
- Combustion Chamber
- annular
- Afterburner
- Yes
- Streams
- 2
- Bypass Ratio
- 0.36
- Maximum Takeoff Thrust (kN)
- 64
- Thrust To Weight
- 6.5
- Specific Fuel Consumption (g/(kN·s))
- 25.492
- Compressor Description
- 8-stage axial compressor
- Turbine Description
- 2-stage axial turbine