FIELD: machine building.
SUBSTANCE: stator of aircraft gas turbine engine comprises annular row of fixed blades and annular row of posts, as well as annular row of blades with varying installation angle. Rear edges of fixed blades are located in first plane transverse to stator axis and located downstream of second plane transverse to stator axis and passing through front edges of posts. Front edges of fixed blades are in third plane transverse to stator axis and located upstream of second transverse plane. Circular row of blades with variable angle of installation is located downstream immediately after annular row of posts and comprises the first blades with variable angle of installation, which are in continuation of posts, and second blades with variable angle of installation, which are located between the first blades with variable angle of installation. First blades with varying angle of installation have aerodynamic profiles differing from aerodynamic profiles of the second blades with variable angle of installation. Another invention of the group relates to an aircraft gas turbine engine comprising the above stator.
EFFECT: group of inventions allows reducing the axial dimension of the stator, as well as reducing its weight and losses occurring when the gas flow passes through the stator.
8 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ANGULAR SECTOR OF STATOR WITH GAS TURBINE ENGINE BLADES WITH AXIAL COMPRESSOR (VERSIONS) AND GAS TURBINE ENGINE WITH AXIAL COMPRESSOR, WHICH CONTAINS SUCH ANGULAR SECTOR | 2015 |
|
RU2693671C2 |
| AIR INJECTION INTO GAS TURBINE ENGINE COMPRESSOR PATH | 2009 |
|
RU2482339C2 |
| CONTROL SYSTEM OF BLADES WITH VARIABLE ANGLE OF INSTALLATION FOR GAS TURBINE ENGINE | 2016 |
|
RU2700113C2 |
| GAS TURBINE ENGINE, FOR EXAMPLE AIRCRAFT TURBOJET ENGINE | 2005 |
|
RU2373402C2 |
| GAS-TURBINE ENGINE | 2013 |
|
RU2555933C2 |
| GAS TURBINE ENGINE AND STARTER-GENERATOR FOR GAS-TURBINE ENGINE | 2007 |
|
RU2406829C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
| GUIDE STAGE OF COMPRESSOR OF GAS-TURBINE ENGINE WITH BLADES WITH VARIABLE SETTING ANGLE, AND GAS-TURBINE ENGINE | 2008 |
|
RU2490476C2 |
| GAS TURBINE ENGINE | 2012 |
|
RU2687861C2 |
| CONTROL RING OF STAGE OF BLADES WITH VARIABLE ANGLE OF INSTALLATION FOR GAS TURBINE ENGINE | 2015 |
|
RU2705128C2 |
