ROTOR FOR A GAS TURBINE

摘要

A rotor (10) for a gas turbine. Said rotor (10) comprises a plurality of disks (14, 15; 20, 21) which are welded to each other and are arranged successively on an axis of the rotor (11). The rotor extends between a compressor part (12) and a turbine part (13) and is provided with a central bore (19) which extends between both parts (12, 13) and has an inner diameter (D1). First means (16, 17,18) which enable the cooling air in the compressor part (12) to be diverted and radially guided through the rotor (10) towards the inside are provided. Second means which enable the air in the turbine part (13) to be radially guided from the central bore (19) through the rotor (10) towards the outside are also provided. According to the invention, a high low-loss flow of cooling air can be obtained, while at the same time providing good mechanical resistance. To achieve this, the first means comprise a plurality of radial bores (16) which extend from the outside to the inside through a first rotor disk (14) and lead to a first annular cavity (17) arranged in the first rotor disk (14) in a concentric position to the axis (11) of the rotor; the first cavity (17) has an outer diameter (D2) which is greater than the inner diameter (D1) of the central bore (19); and the first cavity (17) is divided into individual chambers (27) by a plurality of radially arranged ribs (18). .