| 摘要 |
A system to feed cooling air to a gas turbine, wherein the cooling air is taken from a high-pressure source, inside the gas turbine, and is conveyed t o radial accelerators (12), which give rise to the tangential acceleration of the air in the direction of the peripheral motion of the rotor surface. Afte r it has been accelerated to the peripheral sepped of the rotor, the cooling a ir enters radial holes (13), and, whilst passing radially through the radial holes (13), undergoes a reduction in the quantity of tangential motion, Subsequently, the cooling air is released into the hollow rotor, with a correspondingly reduced outlet radius (14). A series of labyrinth seals combined with brush seals separate the chamber for combined with brush seals separate the chamber for feeding of air to the radial holes (13), from the l ow- pressure environment around the pad #2 (15) of the said gas turbine.
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