HIGH-TEMPERATURE TWO-STAGE GAS TURBINE Russian patent published in 2009 - IPC F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: high-temperature two-stage gas turbine with cooled second-stage blades comprises front and rear intermediate disks located in interdisk chamber. Transient curvilinear part of the rear intermediate disk rim has axial channels to communicate air chamber between intermediate disks with that feeding air to second stage cooled blade. The number of axial channels makes twice the number of second stage blades. Flow area of rear intermediate disk rim axial channels vs flow area of air feed chamber varies from 1.5 to 3.

EFFECT: higher reliability due to intensified cooling of second stage blade and rear intermediate disk.

3 dwg