FIELD: engines.
SUBSTANCE: invention relates to high-pressure compressors of gas turbine engines of aircraft and ground use. High-pressure compressor includes unshrouded blades of the rotary guide vanes installed with their external pins in a L-shaped circular rib of the outer housing. Internal annular ring of the L-shape circular rib is made with a front axial circular ledge. Circular ledge contacts in axial direction with an upstream rear axial circular ledge of the working ring. Working ring is installed inside the front external compressor housing. Working ring is connected with the L-shaped circular rib via a conical elastic element.
EFFECT: provided are higher reliability and efficiency of the compressor by reducing deflexion of the rotary guide vanes blades installed with their external pins in the outer housing of the compressor.
1 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AXIAL COMPRESSOR OF GAS-TURBINE ENGINE | 2005 |
|
RU2287093C1 |
| COMPRESSOR STATOR OF GAS TURBINE ENGINE | 2000 |
|
RU2186257C2 |
| GAS TURBINE ENGINE COMPRESSOR STATOR | 2015 |
|
RU2580249C1 |
| COMPRESSOR OF GAS-TURBINE ENGINE | 2003 |
|
RU2257493C2 |
| GUIDE STAGE OF COMPRESSOR OF GAS-TURBINE ENGINE WITH BLADES WITH VARIABLE SETTING ANGLE, AND GAS-TURBINE ENGINE | 2008 |
|
RU2490476C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| STATOR OF GAS TURBINE ENGINE COMPRESSOR | 2001 |
|
RU2199033C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
| GAS-TURBINE ENGINE | 2001 |
|
RU2204043C2 |
| GAS-TURBINE ENGINE COMPRESSOR STATOR | 2000 |
|
RU2175404C1 |
