TJ-160 Turbojet Engine

Description

The TJ-160 turbojet delivers at least 160 daN of thrust in a system weighing no more than 17 kg, with fuel consumption of ≤1.2 kg/(daN·h). It is optimized for high-altitude, high-speed flight up to 12,000 m and Mach 0.9. Dedicated jet fuel operation requires no additional lubrication.

The TJ-160 is a turbojet engine specifically designed for aircraft propulsion. Featuring a compact, lightweight design and a simplified structure, it delivers excellent fuel efficiency and reliable operation. The engine is optimized for high-altitude and high-speed flight, offering broad environmental adaptability as well as excellent overload capability (≥ 6 g) and inlet flow distortion tolerance (DC60 ≥ 0.3). It operates on dedicated jet fuel without requiring additional lubrication, and its service life is designed to meet the operational requirements of flight missions. With a maximum thrust of at least 160 daN, an engine system weight of no more than 17 kg and a diameter of no more than 274 mm, the TJ-160 achieves a maximum operating altitude of 12,000 m and a maximum Mach number of 0.9. One-button starting is supported at elevations from 0 to 4,500 m across an ambient temperature range of -40 °C to +55 °C.

Key specifications: Maximum Thrust: ≥ 160 daN; Engine Diameter: ≤ 274 mm; Engine System Weight: ≤ 17 kg; Specific Fuel Consumption: ≤ 1.2 kg/(daN·h); Maximum Operating Altitude: ≥ 12,000 m; Maximum Mach Number: ≥ 0.9.

Specifications

All specifications are taken from the manufacturer’s current datasheet.