FIELD: engines and pumps.
SUBSTANCE: device for feeding coolant to cooled working blades of high-temperature gas turbine contains a swirling unit of coolant and impeller with cooled moving blades, root of shank located receiving channels, in combination make annular receiving channel. Inlet part of receiving channel, located in leg shank of each cooled working blade is made between radial walls of blade shank legs located on blade pressure surface and back, and circumferential walls of legs of shank of said blade. Outlet part of receiving channel is interfaced with cooling channels of said blade.
EFFECT: such design allows supply of coolant in cooling channels of working blades with reduction of hydraulic losses and coolant heating, increasing efficiency of cooling of working blades.
3 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF COOLING THE ROTOR OF A HIGH PRESSURE TURBINE (HPT) OF GAS TURBINE ENGINE (GTE), HPT ROTOR AND HPT ROTOR BLADE COOLED BY THIS METHOD, KNOT OF THE DEVICE OF TWISTING OF AIR OF HPT ROTOR | 2018 |
|
RU2684298C1 |
| HIGH-PRESSURE TURBINE ROTOR OF A GAS TURBINE ENGINE (VERSIONS) | 2018 |
|
RU2691868C1 |
| GAS TURBINE GUIDE VANE COOLED BLADE | 2017 |
|
RU2663966C1 |
| TURBOJET TURBINE STAGE BLADES AIR-LIQUID COOLING SYSTEM | 2020 |
|
RU2735972C1 |
| DEVICE FOR STARTING GAS TURBINE ENGINE | 2016 |
|
RU2634444C1 |
| COOLING METHOD OF TURBINE WORK BLADE OF GAS-TURBINE ENGINE | 2014 |
|
RU2562361C1 |
| DOUBLE-FLOW GAS TURBINE ENGINE | 2011 |
|
RU2459967C1 |
| DUAL-FLOW TURBOJET ENGINE | 2015 |
|
RU2618993C1 |
| TURBINE BLADE | 2007 |
|
RU2346164C2 |
| COOLED BLADE OF GAS TURBINE | 2018 |
|
RU2686244C1 |
