The adiabatic flame temperature of kerosene in air is 2093 C (source). Modern jet engines have a turbine inlet temperature (TIT) of 1700 to 1800 C. This is the max acceptable temperature before the turbine blades melt or weaken too much.
So how is the gas cooled to the lower temperature before it reaches the turbine stage?
Now I know the obvious simple answer is "air cooling". But I want to know some details about how it's achieved.
Is the cooling air coming from the core air, or is it coming from some ducts into the combustion zone?
Is the cooling air pumped by something (other than the compressor stages) near the core?
Is the cooling air redirected turbulantly by some geometry inside the combustion zone?
Is the cooling air expanded to achieve adiabatic cooling (again I'm only asking about inside the combustion zone)?
Is fuel circulated around the core to act as a coolant (like rocket engines)?
When searching this, I came across something called inlet air cooling. This is not what I'm asking about. Inlet air cooling is about cooling the air before it enters the engine, for example by evaporative cooling.
Also, there is technology to cool the turbine blades directly, such as drilling holes in them and passing some other air . This is not what I'm asking about either. I want to know how combustion gas is cooled before it reaches the first turbine stage.
I realize of course that I can't get a full teaching of fluid dynamics from any answer on this site. What I'm hoping for at the very least is pictures, diagrams, and preferably some numbers used in certain equations that relate temperature and mass flow of air.
One more thing. Old engines are okay. In fact, they might be better, because older engines have a lower TIT and therefore must achieve even more cooling in the combustion zone. I did try to research them, e.g. the Rolls Royce Nene here, where a paragraph about cooling is summarized in a final sentence: "This diluting air is consequently expanded and accelerated rearwards, but it also cools the products of combustion to the temperature required at the turbine inlet." But it has very few numbers and no diagrams or cutouts.