FIELD: turbine engines.
SUBSTANCE: compressor blade feather (70) for the turbine engine is claimed. Compressor blade feather (70) contains top section (100) containing top wall (106) that extends from input edge (76) of the blade feather to output edge (78) of the blade feather. Top wall (106) forms hollow (110) that continues between input edge (76) and output edge (78). On one of back surface wall (88) or trough surface wall (90), shoulder (104, 105) is provided, which extends between input edge (76) and output edge (78). Transition area (108) narrows from shoulder (104) towards top wall (106). The other of back surface wall (88) or trough surface wall (90) continues towards top wall (106).
EFFECT: rotor blade and/or stator blade for the compressor for the turbine engine is provided, designed to reduce the leakage flow at the top and, consequently, reduce the interaction force between the leakage flow and the main flow, which in turn reduces the overall loss of efficiency.
15 cl, 14 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COMPRESSOR BLADE | 2018 |
|
RU2729590C1 |
| AERODYNAMIC PROFILE OF COMPRESSOR | 2018 |
|
RU2728549C1 |
| COOLED BLADE OF ROTOR FOR INDUSTRIAL GAS-TURBINE PLANT (VERSIONS) | 2002 |
|
RU2275508C2 |
| TURBINE BLADE | 1993 |
|
RU2088764C1 |
| TURBINE BLADE AND METHOD OF ASSEMBLY OF TURBINE ROTOR WITH SUCH BLADE | 2009 |
|
RU2517992C2 |
| NOZZLE BLOCK FOR GAS TURBINE, COATED WITH MCrAlY COATING AND TUBE LININGS | 2013 |
|
RU2627997C2 |
| TURBOMACHINE TURBINE BLADE COMPRISING COOLING CIRCUIT WITH IMPROVED HOMOGENEITY | 2015 |
|
RU2674105C2 |
| TURBINE BLADE ROOT AND APPLICATION METHOD OF THERMAL-PROTECTIVE COATING | 2011 |
|
RU2585668C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| HEAT SHIELD FOR GAS TURBINE ENGINE | 2018 |
|
RU2748819C1 |
