FIELD: gas turbine construction.
SUBSTANCE: invention relates to the field of gas turbine construction, namely to cooled turbine blades used in aircraft gas turbine engines, as well as in stationary gas turbine installations. Cooled working blade consists of a shank and a profile working part, consisting of a hollow profile with convex and concave thin walls, between which is located a power rod, made in one piece with the shank. Between the walls and the core are the cooling intensifiers. Profile working part is made of two parts, of which the root part is integrated with the shank, and the peripheral part is integral with the power rod.
EFFECT: invention makes it possible to increase the reliability of the working blade.
1 cl, 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBINE WORKING BLADE OF GAS TURBINE ENGINE AND GAS TURBINE ENGINE | 2019 |
|
RU2716097C1 |
| COMPOSITE WORKING BLADE OF TURBOMACHINE | 2023 |
|
RU2822437C1 |
| GAS TURBINE CERMET BLADE | 2012 |
|
RU2510463C2 |
| 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 |
| GAS TURBINE BLADE WITH CONVECTIVE COOLING SYSTEM | 2016 |
|
RU2627879C1 |
| HIGH-PRESSURE TURBINE ROTOR OF A GAS TURBINE ENGINE (VERSIONS) | 2018 |
|
RU2691868C1 |
| GAS TURBINE COOLED WORKING BLADE | 2012 |
|
RU2506429C1 |
| HIGH-PRESSURE TURBINE (HPT) NOZZLE APPARATUS OF GAS TURBINE ENGINE (OPTIONS), NOZZLE CROWN OF HPT AND HPT NOZZLE APPARATUS BLADE | 2018 |
|
RU2683053C1 |
| TURBOMACHINE ROTATING BLADE | 1995 |
|
RU2118462C1 |
| NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS) | 2018 |
|
RU2691203C1 |
