FIELD: engine devices and pumps.
SUBSTANCE: seal for the gas turbine engine comprises a main portion located at the base of the turbine blade and a wing portion axially extending from said main body portion of the seal. The wing portion has a first portion substantially parallel to the central axis of the engine and an upwardly extending portion. The angle (A) between the central axis of the engine and said upwardly extending portion is approximately from 0° up to 90°.
EFFECT: increase the efficiency of the seal.
7 cl, 4 dwg
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|---|---|---|---|
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|
RU2617037C2 |
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| ANGULAR SECTOR OF STATOR WITH GAS TURBINE ENGINE BLADES WITH AXIAL COMPRESSOR (VERSIONS) AND GAS TURBINE ENGINE WITH AXIAL COMPRESSOR, WHICH CONTAINS SUCH ANGULAR SECTOR | 2015 |
|
RU2693671C2 |
| GAS TURBINE DEVICE | 2016 |
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RU2678861C1 |
| BLADE WITH NARROW MIDDLE PART | 2000 |
|
RU2219377C2 |
