NJ-5 Micro Gas Turbine Engine development was started off as a technology demonstrator. The engine development is complete and several hardware builds of the final prototype have been realized. The engine performance is demonstrated successfully at the design point generating the design thrust. NJ-5 is also flight tested on a small model aircraft.
Engine Performance Specifications
Design Sea-level Static Thrust: 50 N
Engine Speed: 1,00,000 rpm
Engine Pressure Ratio: 2.0
Mass Flow Rate: 0.20 kg/s
Specific Fuel Consumption: 0.234 kg/ N.h
Max. Diameter: 116 mm
Engine Weight: 1.2 kg Max. Thrust: 75 N
Year of Development
2019-2022
Salient Technical Features
• Centrifugal Compressor • Vaporizer Combustor • Axial Turbine • Convergent Nozzle• Integrated Bearing Housing • Two Bearing System • Bearing Lubrication: Fuel + 5% Lube • Starting: Propane Gas/Kero Start with Motor assist
Level/Scale of Development
TRL=9 Development is complete. Engine is Flight Tested. Production Ready.
Applications
For Jet Powered Micro UAVs & Model Aircraft
Commercialization
Under Progress
Available in Market
No Indigenous MGTs are available in the Indian market, but Imported MGTs in this class are available.
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