aditp wrote:Wallah, Grand ayatollah mullah enqoob-ud-din-al-gas-turbiney may pardon the young SDRE mujahid's haraam attempt to tread on his turf.
You see, a turbojet / turbofan engine built for high speed flight employs axial flow compressor / turbine design for their relatively low drag. However, stage compression ratio being lower, several compressor stages are required ~ which increases the length before combustion chamber.
Aft of the combustion chambers, the axial turbine extracts the bare minimum work from the garam hawa that is required to keep the compressor or the turbo pankha running. This is followed by a longish tube called jet pipe to streamline the turbulent hawa from turine exit before nozzle entry.
Jihadi logic : lesser the work taken out of the hawa by the turbiney, lesser the prejjer drop, more garam the hawa at nojjle entry, more the scope for higher thrust = halal injun perphormance.
therephore --> axial combrejjar + turbiney (more length) = halal dejine for high speed flight
underlying priciple : Convert as much energy to mechanical work as possible to drive large pankha - whether for hawaijahaj or helikaptar.
Now, since much leeser amount of air passes through the the injun (okay it does, but only to the extent of 10% or so), drag induced by the compressor is not mucch of an issue. So one tends to use a centrifugal compressor for more compact front end dejine. Ditto for the turbiney - again centrifugal disc type turbiney. Now remember, dejine has been made to extract as much work as possible. This means the hawa at turbine exit will be very thandha and slow speed onree. No need to stabilize the flow through a jet pipe and no nojjle.
Overall shorter dejine onree, while ensuring all power of the jihad is being routed to the pankha by a halal shaft.
If you create a turboshaft out of the Kaveri, at best the turbine will be replaced. Replacing the compressor also, will be tantamount to an all new engine. No point there. Better start a new injun project with a separate jihadi team.
Yes and thank you.