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 combustion chamber, 12 cans |
| 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
No pictures yet for this family.
Airplanes
| Name |
Aircraft Engine |
Number of Engines |
Length (m) |
Flat Wing Span (m) |
|
Baade 152
|
Pirna 014 |
4 |
31.4 |
26.3 |
All data (15 fields)
- Name
- Pirna 014
- Aircraft Engine Manufacturer
- Pirna
- Aircraft Engine Type
- Turbojet
- Dry Weight (kg)
- 1060
- Diameter (mm)
- 981
- Length (mm)
- 3446
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/Pirna_014
- Fuel
- kerosene / jet fuel (specification T-1)
- Geared Fan
- No
- Combustion Chamber
- cannular combustion chamber, 12 cans
- Afterburner
- No
- Streams
- 1
- Thrust To Weight
- 2.97
- Compressor Description
- twelve stage axial flow
- Turbine Description
- two stage