Given the graph in this answer, the temperature are quite high inside a jet-engine, even greater that many metal's melting point. I understand high core temperature are efficient. A jet engine is designed to work for several hours at those high temperature.

Moreover, starting the engine (i.e. going from ambient temperature everywhere inside the engine to more than 1500°C in the combustion chamber while not significantly changing the temperature at the first low pressure compression stage) may be quite stressful for material.

My question is in two parts:

  • How is the high temperature handled, especially in the combustion chamber and the high pressure turbine? I read somewhere that the turbine can be cooled by air flowing inside the blades but I cannot find the reference. I also wonder where this cooling air comes from.
  • How is the stress on material due to temperature changes (between full thrust and shut down, and maybe when changing thrust in mid-flight) handled?
  • $\begingroup$ I hope that the answer covers all the points. Unfortunately I do not think that going in greater detail would be feasible, as we are covering the arguments of 2-3 chapters of a good gas turbine book. $\endgroup$
    – Federico
    Commented Jul 13, 2015 at 19:33
  • $\begingroup$ @Federico you may still put some links to thoses chapters for further readings $\endgroup$
    – Manu H
    Commented Jul 13, 2015 at 19:35
  • 1
    $\begingroup$ My main textbook was "Gas Turbine Theory" from Saravanamuttoo, Rogers, Cohens and Straznicky. I do not think it can be legally found for free on the internet, and I have no direct links. $\endgroup$
    – Federico
    Commented Jul 13, 2015 at 19:40
  • 2
    $\begingroup$ Something I haven't seen mentioned yet - often the turbine blades themselves have air channels inside, and sometimes additional film cooling on their surfaces. See for example aviation.stackexchange.com/questions/14454/… and en.wikipedia.org/wiki/Turbine_blade#Methods_of_cooling $\endgroup$
    – Andy
    Commented Jul 14, 2015 at 8:14
  • 1
    $\begingroup$ @Andy it is mentioned in the question itself: I read somewhere that the turbine can be cooled by air flowing inside the blades and in my answer (point 2) $\endgroup$
    – Federico
    Commented Jul 14, 2015 at 15:49

1 Answer 1


1. The combustion chamber

Temperature here is usually controlled via design of the chamber shape, in particular of the location where combustion occurs vs the airflow.

Detail of combustion section

Image source

In the image above you can see that the fuel line (2) terminates in a nozzle. The nozzle will turn the fuel into tiny droplets to increase the surface area and hasten the combustion process.

Indicated with (6) are instead the main air holes: the cool air coming from the compressor (on the left side) enters the chamber with high pressure from these holes. Note that the holes are distributed in an annular pattern: high pressure air will be entering from all sides of the chamber.

  • The result is that the flame will not directly touch the walls of the chamber, we then got rid of conductive heat transmission.

  • Convective is a non-issue: cool air keeps coming and hot air goes into the turbine.

  • Radiative heat transmission might be an issue, but the new air incoming will cool the walls via conduction.

The engine can thus run without the combustion chamber melting. Note that the use of specific materials does greatly improve the conditions, as higher temperatures can be tolerated, and thus better efficiencies achieved.

2. The turbine cooling air

The air is usually bled from a stage of the compressor, usually a high pressure stage, in a similar manner as done for the air used for the passenger compartment.

3. Thermal stresses

a. Short term

Over the duration of a flight the blades will warm up when the engine is turned on and cool down at the end of the flight. Intermediate load variation do not have a significant impact.

Even the initial warming and the final cooling do not pose a significant problem. The only effect to be taken into account is that the rotating hot blades will become slightly longer: a special material is placed on the opposing stationary side so that the gap is minimal during operation and the losses due to the air going around the blades (instead of between them) are reduced.

b. Prolonged

The most problematic aspect here is the so called "creep": the blades, after prolonged use, will tend to change shape, because they tend to be more malleable at high temperatures, exactly when they are under high tensile load. This becomes a problem over the lifetime of an engine, not during a single flight.

To mitigate this problem the blades are nowadays manufactured as single crystals: each blade is a single solid block of metal and not made up af many tiny crystals as the metal tools we use everyday. This is because under tensile load each of the crystals can slide over its neighbors (and high temperatures facilitate this) changing the shape of the blade. To visualize it, think of a rubber band that does not go back to its original form.

Having a single crystal prevents this sliding, giving more strength to the blade.

  • $\begingroup$ What is the typical compressor exit (combustion chamber intake) temperature? I mean maximum temperature just before combustion. $\endgroup$
    – Kozuch
    Commented Nov 3, 2021 at 11:04
  • $\begingroup$ @Kozuch that will depend heavily on the engine. I don't have a number ready to give. $\endgroup$
    – Federico
    Commented Nov 3, 2021 at 11:12
  • $\begingroup$ I will actually be happy for any values for any engine. Do you know where to find some? My search is failing so far. $\endgroup$
    – Kozuch
    Commented Nov 3, 2021 at 11:19
  • $\begingroup$ @Kozuch no. but you can try asking in chat. $\endgroup$
    – Federico
    Commented Nov 3, 2021 at 11:44

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