FIELD: engines and pumps.
SUBSTANCE: high-temperature double-stage gas turbine includes interdisk cavity sealed with intermediate disks. Between rim of back intermediate disk and shank end of working blade on the side of inlet edge of specified blade there are radial plates installed, which create slot cavity with surface of lock joint "disk-blade". Slot cavity at the inlet is connected to interdisk cavity, and at the outlet - through slot channels of lock joint with gas cavity installed on the back side of second stage disk along with gas flow. Cooling matrices are arranged on radial plates from the side of slot cavity. Ratio of radial plate thickness to depth of slot cavity makes 1.5 - 10.0.
EFFECT: increased reliability of structure due to intensification of cooling of lock joint of working blades with turbine disks.
5 cl, 6 dwg
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