Nice find ...... but you missed this ,
Developed and Certified projects
- HJE-2500 engine
- PTAE-7 engine for Lakshya aircraft
- GTSU-110 starter engine for LCA (Tejas)
- Shakti engine co-development with Turbomeca, France
- Test Bed Projects
o TM 333-2B2 / Shakti Engine Test Bed
o Adour Engine Test Bed
o Pegasus Engine Test Bed
o Garrett Engine Test Bed
o R29B Engine Test Bed
o LM 2500 Engine Test Bed
o Pneumatic starter (HFES)
o Hydraulic pump (HHP)
athokke ariyavunnatha..but APU and turboprop engine..
HJE-2500 ETBRDC, HAL, INDIA:
HJE-2500 was the first turbojet engine designed and developed in India. The engine of 2500 lb (11.1 kN) thrust, developed by “Engine Design Bureau- EDB” of Hindustan Aeronautics Limited, was one of the most prestigious, indigenous engine development activities undertaken in India in the mid 1960s. HJE-2500 was developed for basic jet trainer aircraft, HJT-16 MK 2
Engine Design Bureau- EDB subsequently renamed as Engine and Test Bed Research and Design Center (ETBRDC), started functioning in the year 1960. Mr. T.V. Vareed, recruited from Rolls Royce, England was instrumental in starting the engine design bureau in HAL. Initially, the task of the division was to design engines and engine accessories for the indigenous aircraft designed by the Aircraft Design Bureau (ADB), HAL.
Mr.
T.V Vareed, as chief designer, launched India’s first indigenous turbojet engine design project, the Hindustan Jet Engine (HJE-2500), along with other talented designers, Mr. R. Ramakrishnan, Mr. V. Govindan, Mr. N.H. Balakrishna, Mr. Gururaja Rao, Mr. Rama Reddy, Mr. Srinivasan, in the year 1960.
A prototype development of the engine was taken up by the team and the first run of the engine was successfully achieved in April 1965 at the Casuarina test bed, on a modified Pegasus piston engine test rig, near the present day BEML complex.
HJE-2500 Specifications
Year 1965
Mass Flow 45.2 lb (20.5 kg)/sec at 12,500 RPM
Type Turbojet
SFC1.11 kg/kg thrust/hr
Compressor Seven stage axial (Pressure ratio 4.2:1)
Combustor Can-annular combustor with seven flame tubes
Turbine Single stage turbine
Frontal Area0.3 square meter
Takeoff thrust 2500 lb (11.1 kN) at 12,500 RPM
Length 2160 mm
Diameter 660 mm
Weight5 85 lb (265 kg)
Mallu ?
