FIELD: mechanical engineering; turbomachines.
SUBSTANCE: proposed device for ventilation of rotor of high-pressure turbine contains disk 3 and inlet flange 5. First blade cooling loop delivers first air flow C1 through main air nozzles 15 and holes 11 made in flange 5. Second cooling loop delivers second air flow C2 through outlet labyrinth 18 located after compressor. Part of said second air flow serves for cooling upper front surface of flange through second labyrinth 22 found under main air nozzles 15. Outlet provided between first loop and hollow space 23 behind second labyrinth 22 delivers third air flow C1a swirled preliminarily by additional air nozzles 30 made in form of inclined drillings. Invention provides reduction of temperature of flange front surface, simplifies designing for operation at supercharging speeds.
EFFECT: increased service life.
6 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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