FIELD: machine building.
SUBSTANCE: for the purpose of cooling the wall thermally loaded at its front, a coolable element of a gas turbine comprises a variety of pins distributed over the surface of the wall back as well as units to form directed cooling medium jets in the pin zone towards the wall back that are intended for impact cooling. Distribution of pins within the critical zones (Ac) of the element is of higher density than in other element zones. The units to form directed jets towards the wall back comprise an impact cooling plate with distributed impact cooling holes. The density of impact cooling holes is correlated with the density of pins.
EFFECT: invention is aimed at the design of a coolable gas turbine element with its cooling being optimally correlated with the locally changing thermal load without additional consumption of cooling air.
4 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| STEAM TURBINES HIGH-TEMPERATURE STUD PINS REFRIGERATION METHOD AND DEVICE FOR ITS ACTUALIZATION | 2016 |
|
RU2641782C2 |
| GAS TURBINE GUIDE VANE COOLED BLADE | 2017 |
|
RU2663966C1 |
| TURBINE VANE WITH COOLED FILLET | 2015 |
|
RU2675433C2 |
| TURBINE BLADE AND GAS TURBINE INCORPORATING THIS BLADE | 2005 |
|
RU2333364C2 |
| BLADE FOR TURBINE MACHINE AND TURBINE MACHINE WITH SUCH BLADE | 2011 |
|
RU2577688C2 |
| COOLED WALL | 2013 |
|
RU2634986C2 |
| COOLED TURBINE GUIDE BLADE AND TURBINE HAVING SAID BLADES | 2005 |
|
RU2308601C2 |
| GAS TURBINE ELEMENT WITH FILM COOLING | 2015 |
|
RU2666385C1 |
| HIGH PRESSURE NOZZLE VANE BLADE COMPRISING INSERT WITH VARIABLE GEOMETRY | 2016 |
|
RU2704511C2 |
| GAS TURBINE ENGINE BLADE EQUIPPED WITH A COOLING SYSTEM AND METHOD OF MANUFACTURING SUCH BLADE BY CASTING USING SMELTED WAX MODELS | 2020 |
|
RU2800619C2 |
