Hello, here I am providing you the details of the Defence Research and Development Organisation jet engine as under:

GTRE GTX-35VS Kaveri
The GTRE GTX-35VS Kaveri is an afterburning turbofan project developed by the Gas Turbine Research Establishment (GTRE), a lab under the DRDO in Bangalore, India.

Applications
GTX-35VS Kaveri:
HAL Tejas (planned for production models)
HAL Advanced Medium Combat Aircraft

Derivatives:
Kaveri Marine Gas Turbine (KMGT), a recently developed derivative of the GTX-35VS Kaveri engine for ships.
Ghatak,a Kaveri derivative to be developed to power India's Unmanned Combat Air Vehicle DRDO AURA.

Specifications:
General characteristics
Type: afterburning turbofan
Length: 137.4 in (3490 mm)
Diameter: 35.8 in (910 mm)
Dry weight: 2,724 lb (1,235 kg) [Goal: 2,100-2450 lb (950-1100 kg)]

Components
Compressor: two-spool, with low-pressure (LP) and high-pressure (HP) axial compressors:
LP compressor with 3 fan stages and transonic blading
HP compressor with 6 stages, including variable inlet guide vanes and first two stators
Combustors: annular, with dump diffuser and air-blast fuel atomisers
Turbine: 1 LP stage and 1 HP stage

Performance
Maximum thrust:
Military thrust (throttled): 11,687 lbf (52.0 kN)
Full afterburner: 18,210 lbf (81.0 kN)(planned to be refined to >95 kN)
Specific fuel consumption:
Military thrust (throttled): 0.78 lb/(lbf•h) (79.52 kg/(kN•h))
Full afterburner: 2.03 lb/(lbf•h) (207.00 kg/(kN•h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)

Engine cycle
Airflow: 172 lb/s (78.0 kg/s)
Bypass ratio: 0.16:1 (it should be increased to 0.5:1)
Overall pressure ratio: 21.5:1 [Goal: 27:1]
LP compressor pressure ratio: 3.4:1 [Goal: 4:1]
HP compressor pressure ratio: 6.4:1
Turbine entry temperature: 2,218-2,601 °F (1,214-1,427 °C; 1,487-1,700 K) [Goal: 3,357 °F (1,847 °C; 2,120 K)]