FIELD: machine building.
SUBSTANCE: turbine blade of gas turbine engine comprises back, bottom, front edge, rear edge and cavity at its apex. Cavity in vane root has inner rib extending from connection point of said casing on back side to point of connection of collar of said cavity from pressure trough side. Inner rib comprises section of leak load perception, which passes from back, and section forming reflector, which continues section of load bearing with bend and directs leakage flows towards pressure rubber. Other inventions of the group relate to the disc of a turbine and high-pressure turbine of a turbojet engine containing the above blades.
EFFECT: group of inventions allows reducing leakage through the top of gas turbine engine blades.
10 cl, 8 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBINE BLADE WITH END COVER | 2015 |
|
RU2704504C2 |
| TURBINE BLADE WITH IMPROVED STRUCTURE AND GAS TURBINE CONTAINING SUCH A BLADE | 2018 |
|
RU2772363C2 |
| GAS TURBINE ENGINE BLADE MADE ACCORDING TO THE RULE OF DEFLECTION OF THE BLADE PROFILE WITH A LARGE FLUTTER MARGIN | 2019 |
|
RU2792505C2 |
| GAS TURBINE ENGINE BLADE WITH MAXIMUM THICKNESS RULE WITH HIGH FLUTTER STRENGTH | 2019 |
|
RU2794951C2 |
| TURBINE BLADE COMPRISING COOLING SYSTEM | 2017 |
|
RU2741357C2 |
| COOLED TURBINE BLADE | 2017 |
|
RU2726235C2 |
| BLADE WITH IMPROVED COOLING CIRCUIT AND GAS TURBINE ENGINE CONTAINING SUCH A BLADE | 2018 |
|
RU2772364C2 |
| GAS TURBINE ENGINE BYPASS CHANNEL, CONTAINING CHANNEL CLOSURE GRATE WITH DIFFERENT MOUNTING ANGLES | 2016 |
|
RU2715766C2 |
| METHOD OF PRODUCING RIB ON VANE FREE END, VANE PRODUCED BY SAID METHOD AND GAS TURBINE ENGINE EQUIPPED WITH SAID VANE | 2006 |
|
RU2415003C2 |
| GAS TURBINE ENGINE AIRFLOW STRAIGHTENING ASSEMBLY AND GAS TURBINE ENGINE COMPRISING SUCH UNIT | 2016 |
|
RU2711204C2 |
