FIELD: engines and pumps.
SUBSTANCE: high-temperature turbine of gas turbine engine comprises turbine disks and spaces between them. The said spaces are sealed by the front and rear intermediate disks with cooling holes arranged at the front intermediate disk rim. There are recesses making axial ribs with holes arranged on the inner side of the front intermediate disk rim. The recess surfaces are formed by circumference arcs, while the number of recesses is equal to that of the holes.
EFFECT: lower weight, higher reliability.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| HIGH-TEMPERATURE TWO-STAGE GAS TURBINE | 2008 |
|
RU2369747C1 |
| TWO-STAGE HIGH-TEMPERATURE GAS TURBINE | 2007 |
|
RU2352791C1 |
| TWO-STAGE TURBINE OF HAS TURBINE ENGINE | 2008 |
|
RU2369749C1 |
| HIGH-TEMPERATURE DOUBLE-STAGE GAS TURBINE | 2007 |
|
RU2364727C1 |
| TURBINE OF GAS-TURBINE ENGINE | 1998 |
|
RU2141036C1 |
| DOUBLE-STAGE GAS TURBINE | 1998 |
|
RU2147689C1 |
| HIGH-TEMPERATURE TURBINE OF GAS TURBINE ENGINE | 2000 |
|
RU2193091C2 |
| MULTISTAGE GAS POWER TURBINE | 2004 |
|
RU2263790C2 |
| ROTOR OF TWO-STAGE TURBINE | 2000 |
|
RU2186991C2 |
| TURBINE OF GAS TURBINE ENGINE | 1998 |
|
RU2151884C1 |
