FIELD: aircraft industry; aircraft and ground application gas turbines.
SUBSTANCE: according to invention, relief chamber is made at outlet in multistage gas power turbine with cantilever-mounted disks with blades on turbine rotor. Interdisk spaces at inlet are connected with relief chamber, and at outlet, with gas space through ring closed spaces formed by flanges installed over disk periphery, channels under feet of blade roots and slot spaces between flanges and rims of disks from side of gas flow inlet in disk and between flanges and roots of blades from side of gas flow outlet from disk. Ratio of area of slot spaces between flanges and rims of disks at gas flow inlet in disk to area of slot spaces between flanges and roots of blades from side of gas flow outlet from disk is 2-20.
EFFECT: improved reliability of gas turbine by provision of intensive cooling of power turbine disks and axial relief of turbine rotor.
3 dwg
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