19 without the orifices 20 the situation of fig2 b is obtained on revving up of the turbo aero engine when the heating of the structures is much more sensitive in certain portions of the stator 2 and in particular close to the combustion chamber 4 where combustion is strengthened the pipes 11 undergo a longitudinal movement towards downstream with respect to the rotor 1 and the hot gases of the combustion chamber 4 expand freely into the chamber 21 so as to heat the bulb 12 by blowing onto it and thus reduce the heat gradient in the disk of the high pressure turbine 7 when the rate has stabilized the heat differential reduces the rotor 1 corrects its delay on heating and in turn expands towards upstream the joints 15 and 16 slide onto the wall 9 or its extension 17 the tongues 18 passing in front of the plate 22 and the orifices 23 and the heating of the bulb 12 ceases when it would be able to introduce a new heat gradient after having corrected the previous one reference is now made again to fig1 to explain in more detail on how the bulb 12 is heated a pair of plates 24 and 25 is picked up at one end between the radial and parallel ribs 26 and 27 of the wall 9 and of the.