Objectives
|
Design
and Develop
-
GE F404-F2J3
- Kaveri
- JFS
- Engine Test Facility
|
| Team |
|
|
| PD [P&GS] |
Mr. KG Vivek |
| Administrative
Setup/Office Setup |
Shri.V.Venugopalan
|
|
Ms.Saroja
Kushal |
|
|
| Project
Co-ordinators and Projects |
|
|
No
|
Co-ordinator
|
Project/Activities
|
| 1. |
Mr. BG Keshava Murthy (Sc/Engr - G) |
|
| 2. |
Mr. R Swaminathan ( GD [TD2] ) |
|
| 3. |
Mr. H Siddesha (GD [PV2] ) |
|
| 4. |
Mr.
KS John Britto (Sc/Engr - F) |
|
| 5. |
Mr.
B Ashok (Sc/Engr - F) |
|
| 6. |
Mr.
GP Ravi Shankar (Sc/Engr - F) |
|
| 7. |
Mr.
CS
Kumaraswamy
(Sc/Engr-F) |
|
| 8. |
Mr.
Premkumar
L
(Sc/Engr-F) |
|
| 9. |
Mr.
Mahesh
P
Padwale
(Sc/Engr-F) |
|
| 10. |
Ms.
Sasikala
Deivasigamani
(Sc/Engr-F) |
|
| 11. |
Dr.
Chennu
Ranganayakulu
(Sc/Engr-F) |
|
| 12. |
Mr.
HS
Nagaraj
(Sc/Engr-F) |
|
|
Propulsion
Systems
|
Kaveri,
a twin spool low bypass turbofan engine with flat rated thrust for tropical
conditions to enhance combat power, GE404F2J3 as interim power plant
Full authority digital
electronic control unit for engine control
External fuel tanks and inflight refueling capability enable long range
deployment
Jet Fuel Starter for ground starts and inflight relight.
|
Kaveri
Engine
|
Gas
Turbine Research Establishment is carrying out the design and development
of the KAVERI engine for powering he Light Combat Aircraft (LCA).
Kaveri
engine is a flat rated two spool turbofan engine
Air mass flow : 75.00 kg/sec
By pass ratio : 0.161
Overall pressure ratio : 21.00
TET : 1480 deg - 1688 deg K
Max (Dry) thrust : 50.6 kN
Max ( Reheat) :21.56 gm/s/kN
SFC (max reheat) : 54.52 gm/kg/sec
|
|
| |
JET
FUEL STARTER
|
The
GTSU - 110 turbo-starter is a two shaft turboshaft engine developed for
starting General Electric - F 404 or equivalent engine
|
Description
The starter comprises :
Single stage centrifugal compressor
Single stage axial gas generator turbine
Single stage axial free power turbine
Annular reverse flow combustor Eight fuel burners
Operating and starting control systems
|
|
Engine
Test Facility
|
Ground
test facility is used to carryout acceptance tests, back-to-back tests and for
trouble shooting of the power plant of LCA.
|
Features
Vertical air-intake with mesh-protected louvers provides weather barrier, noise
control and low-pressure drop.
Bell-mouth attachment at engine inlet streamlines airflow and enables mass flow
measurements. Facility to measure thrust directly using Load Cells
on Roof mounted thrust stand.
Engines up to 22,700 kg (50,000 lbs) thrust class can be tested
|
|
|
