FIELD: engines and pumps.
SUBSTANCE: proposed gas turbine blade comprises hollow root airfoil portion and shroud platform with sealing knife edges arranged on peripheral wall of aforesaid shroud platform. Blade root airfoil portion has inner chamber with radial rib accommodating web attached to the said peripheral wall of aforesaid shroud platform. Air outlet channels of this chamber are arranged behind aforesaid sealing knife edges, tight nearby shroud platform outlet edge.
EFFECT: higher reliability of shroud platform and efficiency of gas turbine engine.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TWO-STAGE TURBINE OF HAS TURBINE ENGINE | 2008 |
|
RU2369749C1 |
| GAS TURBINE ENGINE LOW-PRESSURE TURBINE (LPT) (VERSIONS), ROTOR SHAFT CONNECTION UNIT WITH LPT DISC, LPT ROTOR AIR COOLING PATH AND AIR FEEDING APPARATUS FOR COOLING LPT ROTOR BLADES | 2018 |
|
RU2684355C1 |
| TURBINE OF GAS TURBINE ENGINE | 1998 |
|
RU2151884C1 |
| COOLED TURBINE GUIDE BLADE AND TURBINE HAVING SAID BLADES | 2005 |
|
RU2308601C2 |
| GAS TURBINE ENGINE HIGH-TEMPERATURE TURBINE | 2013 |
|
RU2518766C1 |
| MOVING BLADE OF GAS-TURBINE ENGINE TURBINE | 2013 |
|
RU2529273C1 |
| NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS) | 2018 |
|
RU2691203C1 |
| GAS TURBINE BLADE WITH CONVECTIVE COOLING SYSTEM | 2016 |
|
RU2627879C1 |
| COOLING SYSTEM OF GAS-TURBINE ENGINE IMPELLER | 2012 |
|
RU2490473C1 |
| GAS TURBINE ENGINE COOLED TURBINE | 2013 |
|
RU2519678C1 |
