FIELD: engines and pumps.
SUBSTANCE: two-stage high-temperature gas turbine comprises nozzle vanes, front and rear intermediate disks arranged disk space and forming labyrinth seal with the second stage nozzle vane lower flange. At the turbine intake, the second stage nozzle vane communicates with high-pressure chamber and comprises the nozzle arranged on the labyrinth inlet flange integral with the said vain lower flange and connected with the inner space of its blade. The distance from nozzle edge to the front intermediate disk rim outer surface-to-nozzle diameter ratio varies from 0.5 to 3.
EFFECT: higher reliability of two-stage high-temperature turbine.
2 dwg
| Title | Year | Author | Number |
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| MULTISTAGE GAS POWER TURBINE | 2004 |
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RU2263790C2 |
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|
RU2141036C1 |
