Maximum Takeoff Thrust
13.7 kN
Specific Fuel Consumption
3027.942 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 combustion chamber with 30 fuel supply pipes and vapouriser 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
No pictures yet for this family.
Similar reaction turbines
All data (17 fields)
- Name
- Ishikawajima-Harima J3
- Aircraft Engine Manufacturer
- IHI Corporation
- Aircraft Engine Type
- Turbojet
- Dry Weight (kg)
- 430
- Diameter (mm)
- 627
- Length (mm)
- 1661
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/Ishikawajima-Harima_J3
- Fuel
- JP-4 jet fuel
- Geared Fan
- No
- Combustion Chamber
- annular combustion chamber with 30 fuel supply pipes and vapouriser tubes
- Afterburner
- No
- Streams
- 1
- Maximum Takeoff Thrust (kN)
- 13.7
- Thrust To Weight
- 3.2
- Specific Fuel Consumption (g/(kN·s))
- 3027.942
- Compressor Description
- eight-stage axial compressor
- Turbine Description
- single-stage axial-flow