FIELD: mechanical engineering; turbines. SUBSTANCE: proposed turbine blade relates to cooled blades of gas-turbine engines of ground or aircraft application. It contains airfoil portion with leading and trailing edges, blade pressure surface and blade suction face, with cooled inner space. Inner space of airfoil portion is connected by channels with pocket arranged on trailing edge of blade from side of pressure surface. Ratio of size of blade profile chord to width of pocket along middle line of blade profile is 6-20. EFFECT: provision of effective cooling of blade trailing edge, increased efficiency of turbine. 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COOLED BLADE OF TURBINE | 2004 |
|
RU2263791C1 |
| TURBINE BLADE | 2007 |
|
RU2346164C2 |
| COOLED WORKING BLADE OF TURBINE | 1992 |
|
RU2043508C1 |
| ROTOR OF HIGH-TEMPERATURE GAS TURBINE | 2001 |
|
RU2200235C2 |
| HIGH-PRESSURE TURBINE (HPT) NOZZLE APPARATUS OF GAS TURBINE ENGINE (OPTIONS), NOZZLE CROWN OF HPT AND HPT NOZZLE APPARATUS BLADE | 2018 |
|
RU2683053C1 |
| GAS-TURBINE COOLED BLADE | 1995 |
|
RU2101513C1 |
| NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS) | 2018 |
|
RU2691203C1 |
| GAS TURBINE GUIDE VANE COOLED BLADE | 2017 |
|
RU2663966C1 |
| AIR COOLING PATH OF BLADE OF NOZZLE APPARATUS OF HIGH PRESSURE TURBINE OF A GAS TURBINE ENGINE (VERSIONS) | 2018 |
|
RU2686430C1 |
| COOLED GAS TURBINE BLADE | 1983 |
|
SU1152289A1 |
