FIELD: mechanical engineering; turbomachines.
SUBSTANCE: proposed cooled blade of turbomachine contains blade feather with successively connected cooling channel of leading edge of blade feather and intermediate channel, discharge channel communicating with discharge holes of blade feather trailing edge, root and cooling medium supply channel connected with cooling channel of blade feather leading edge. Root is provided with flange having outlet holes. Space is made in blade root communicating with output of intermediate channel and with input of discharge channel and with outlet holes of blade root flanges. Invention is aimed by reducing flow rate of coolant at simultaneous increasing reliability of blade owing to reduction of heat stresses in blade, providing simplified geometry of cooling channels and increased manufacturability of blade as a whole.
EFFECT: reduced requirements to design of cooling air supply system for cooling of blades and parameters of cooling air.
6 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE COOLED BLADE | 2008 |
|
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RU2297537C2 |
