Is this true? I can't find any sources.
We do have a twin-cell test facility nearing completion at Rajankunte near Bangalore.
Is this true? I can't find any sources.
We do have a twin-cell test facility nearing completion at Rajankunte near Bangalore.
Confirmation of the first Kaveri derivative engine from the Godrej production line is now available. We finally have something that actually comes from a proper production line; we just need a solid afterburner. Kudos to DRDO, GTRE and Godrej 
Is it possible to make a high-bypass version of this? We have given all our transport aircraft needs on platter for imports, and subsequently platforms from AEW&CS, Aerial refuellers, ISTAR, EW/ELINT/SIGINT, Bombers, Maritime Patrol etc etc.Confirmation of the first Kaveri derivative engine from the Godrej production line is now available. We finally have something that actually comes from a proper production line; we just need a solid afterburner. Kudos to DRDO, GTRE and Godrej
I mean we can use kaveri's core.
But I don't think its a good idea.
The design is quite old, plus modern highbypass turbofan's also now have cores that do share tech with fighter jet cores but custom designs( i.e. different cores, may use same material) .
Plus if we're going for high bypass, beleive me it ain't gonna be ready before a decade even if kaveri's core is used, so new core is a better idea.
Basically if your thinking for relatively quick development, then realistically not possible in our scenerio.
What is possible is buying russian high bypass engines, if a need really arises.
And If specs are correct, then modern russian high bypass engines are pretty decent by current standards.
The KDE that Godrej Aerospace is making is 48kn right ? wonder if misprint or can be improved /
They are fitting a kaveri on tejas with a reheat module
Probably Could be this i guess.
F404-in20 used in tejas is also ~53kn dry and ~84kn afterburner.
( normal f404 is 48kn dry and 78kn afterburner).
Or probably talking about max unsustainable thrust.
48-49 kn is max sustainable thrust of KDE.
how do you define design is old?
kaveri is already pretty modern design.
what separates modern turbofan from old is higher bypass ratio >9:1(civilian), lower compressor stages, reduced weight, and high thermal efficiency of each part like high pressure compressor and turbine,
kaveri has it all,
Kaveri is still very much relevent and most modern turbofan design,
it has only 6 compressor stages and 3 Fan stages pretty much in line with all modern turbofans,
it just need maturity in design like wide chord Fan design and more pressure ratio in high pressure compressor, and higher TET,
which can be solved by BLING/ BLISkS and better coatings and materials.
no need to change design, just add more compressor stages and Turbine stages to increase thermal efficiency like civil high bypass turbofan do.
You do that & the weight goes for a toss in a TF already carrying the accusation of being too heavy.
Could be the age old problem of ISA specifications being used too .
CIVILIAN TURBOFAN ENGINES ARE CONSIDERABLY HEAVIER THAN THEIR MILITARY COUNTERPART DUE TO HIGH BYPASS AND MORE COMPRESSOR STAGES AS WELL AS TURBINES.
Take it easy will you ? Where's the need to get hyper ? Was under the impression you were referring to Low Bypass Military TFs.
The 49 kn of current dry kaveri is ISA no.
yes. earlier kaveri k9 produced 46kN,
improved dry produced 48.5kN in high altitude test in russia, but at sea level it should be able to produce more.
wasnt it 49kn at sea lmao, it was the exact opposite from what i can remember
There is a SiC single crystal growth related EOI issued
We need to start the development of the 65-70 KN Dry thrust engine right away. The MOD should allocate funds to establish all the testing facilities. This will benefit our AMCA engine as well.
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What's an estimated cost of buying an A340 and modifying it as a FTB for jet engines? And a C130 for turboprops testing?