why would there be anything unique about a Turbine Inlet Temp for a Concorde compare to other installations of the day?
I would think that the actual metal temp is a heat transfer thingie between the TIT out of the burner vs the cooling air temp from wherever you can tap enough pressure to flow to the turbine.
Is it not possible to move farther forward in the Concorde to get pressures and temperature for cooling the turbine in line with other installations of the same type engines?
Can't see any reason in principle why one should not tap cooling air earlier in the cycle, but I was under the impression that the Ol 593 cooling technology was state of the art for a 1960's engine
