FIELD: engines and pumps.
SUBSTANCE: gas turbine engine blade free end has end baffle wherefrom rim flange extends. Said rim flange comprises first section starting in the blade rear edge to run along blade top surface till joint zone, ad second section with closed outline and faired with aforesaid first zone at the level of said joint zone. Said second section makes continuation of the first section and is located along the blade top surface and, further on, along blade rib of attack to join to said joint zone.
EFFECT: higher efficiency.
10 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBINE | 2015 |
|
RU2677021C1 |
| GAS TURBINE ENGINE MOVING BLADE, TURBINE WITH SAID BLADE AND GAS TURBINE ENGINE | 2007 |
|
RU2457335C2 |
| FAN ROTOR BLADE OF AIRCRAFT JET ENGINE | 2013 |
|
RU2592365C2 |
| FAN ROTOR BLADE OF JET ENGINE FOR AIRCRAFT | 2013 |
|
RU2599219C2 |
| GAS TURBINE BLADE | 2011 |
|
RU2573085C2 |
| TURBINE BLADE, TURBINE DISK AND GAS TURBINE ENGINE TURBINE | 2015 |
|
RU2692938C1 |
| CONNECTING BLADE STRUCTURE AND JET ENGINE WITH SAID STRUCTURE | 2013 |
|
RU2601696C2 |
| MOVING BLADE OF GAS-TURBINE ENGINE TURBINE | 2013 |
|
RU2529273C1 |
| GAS TURBINE ENGINE COOLED TURBINE | 2013 |
|
RU2519678C1 |
| TURBINE BLADES AND GAS-TURBINE UNIT WITH SUCH TURBINE BLADES | 2018 |
|
RU2685403C1 |
