Product overview
The LX80 from Shanghai Ruirui Aviation Equipment Technology Co., Ltd. is a micro turbojet engine for thrust production. Its body measures 204 mm in diameter and 488 mm in length, with a body weight of 9100 g. These dimensions define the engine body’s physical envelope for installation planning. Maximum thrust is 785 N, accompanied by a thrust-to-weight ratio of 9.2 and a maximum rotational speed of 62000 RPM.
Fuel requirements are expressed as a maximum consumption of 2870 ml/min and a specific fuel consumption of 1.48 kg/daN.h. The LX80 has a starting-altitude range of 0–4000 m, a maximum flight altitude of 12000 m and a flight-speed range of Mach 0–0.8. The starting-altitude range is a separate operating parameter from the maximum flight altitude; the higher flight-altitude figure does not extend the stated altitude range for starting the engine.
Specifications
| Specification | Value & conditions |
|---|---|
| Manufacturer | Shanghai Ruirui Aviation Equipment Technology Co., Ltd. |
| Model and product type | LX80 Micro Turbojet Engine |
| Body diameter | 204 mm |
| Body length | 488 mm |
| Body weight | 9100 g |
| Maximum thrust | 785 N |
| Thrust-to-weight ratio | 9.2 |
| Maximum fuel consumption | 2870 ml/min |
| Specific fuel consumption | 1.48 kg/daN.h |
| Maximum rotational speed | 62000 RPM |
| Starting altitude | 0–4000 m |
| Maximum flight altitude | 12000 m |
| Flight speed | Mach 0–0.8 |
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