Patent ID: 6923005

Claim:
System to feed cooling air to a gas turbine, wherein the cooling air is taken from a high-pressure source, inside the said gas turbine, and is conveyed to radial accelerators ( 12 ), which give rise to the tangential acceleration of the air in the direction of the peripheral motion of the rotor surface, after it has been accelerated to the peripheral speed of the rotor, the said cooling air enters radial holes ( 13 ), and whilst passing radially through the said radial holes ( 13 ), undergoes a reduction in the quantity of tangential motion, by means of the law of forced vortex, and, subsequently, the said cooling air is released into the hollow rotor, with a correspondingly reduced outlet radius ( 14 ), characterised in that it comprises a labyrinth seal combined with a brush seal ( 17 ) to separate the chamber to feed the air to the radial holes ( 13 ), from the chamber which communicates with the first rotor space in a way to form an intermediate chamber which prevents mixing of the leakage flow rate from the axial compressor, with the cooling flow of the accelerators.