What happens in a turbine high-temp combustion?
The biggest limiter of hot section temperatures in aviation gas turbines is moving hot section parts subject high stress loads under high temperatures and do so for very long periods of time.  Even the best nickel cobalt superalloys cannot maintain acceptable yield strengths past about 2000°F.  Some additional solutions have utilized to achieve even higher TIT levels such as novel single crystal casting techniques for the rotor buckets as well as using bleed compressor air to envelop the surface of the buckets to protect them against the high temperature exhaust gases.  Some military engines can operate with TITs as high as 2600-2700°F.  Another proposed option has been to manufacture the buckets, stators and hot section casings out of carbon composites, which hold the promise of increasing TITs as high as 4000°F.  However carbon composite blades are susceptible to oxidation before reaching these temps, making it difficult to realize this.  General Electric Aircraft Engines may be on the cusp of solving thes problems; if they do, a composite gas core would offer a quantum leap in power and efficiency.