Kaveri engine has undergone development test of more than 1300 hours at Gas Turbine Research Establishment and has successfully completed phase I and II of high altitude testing at M/s CIAM, Russia.

First HAL manufactured engine K6 has run to maximum capacity.


Kaveri Engine is a technologically complex and vital system for the LCA as well as its future variants.

It incorporates state-of-the-art technologies and provides the required thrust for indigenous competence in this critical area.

Kaveri Three-Stage Transonic Fan, designed for good stall margin and bird strike capability, handles an air mass flow of 78 kg/s and develops a pressure Combustion Chamber Liner ratio of 3.4.

The six-stage variable capacity transonic compressor of Kaveri develops a pressure ratio of 6.4.

The variable schedule of inlet guide vanes and two rows of stator is through FADEC control system to open the stator blades in a predetermined manner.

High intensity low UD ratio annular combustor of Kaveri engine incorporates air blast injection of fuel for uniform outlet temperature profile and reduced carbon emission.

Kaveri-Special Characteristics :

Air-mass flow : 78 kg/s
By-pass ratio : 0.16
Overall pressure ratio : 21.5
Turbine entry temperature : 1487-1700 K
Maximum dry thrust : 52 kN (5302 kg)
Maximum dry SFC : 0.78 kg/hr/kg
After burner maximum power thrust : 81 kN (8260 kg)
After burner maximum power SFC : 2.03 kg/hr/kg
Thrust-to-weight ratio : 7.8
Application : Indian LCA