Product overview
The Jinpengda LF125P Thunder turbojet engine provides propulsion for small and medium UAVs, civil light aircraft and gliders. It develops a maximum thrust of 125 kg with a thrust-to-weight ratio of 7. Its construction combines an annular, internally supported intake and integrally cast casing with four support struts and a flow-straightening cone. A single-stage centrifugal compressor feeds a reverse-flow annular combustor, followed by a single-stage axial-flow turbine and a non-adjustable convergent exhaust nozzle.
The engine incorporates electronic control, a starter-generator ahead of the compressor and one igniter plug. It uses RP-3 or JET A fuel, with open lubrication supplied by fuel mixed with 1–2% lubricating oil. Generator output is 2000 W at 28 V. The flight envelope extends from 0–0.9 Ma and 0–13000 m above sea level; starting is supported at 0–6000 m and 0–0.6 Ma. Dry weight is 17.8 Kg, and the first overhaul interval is 50 h or 200 starts.
