FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application. Novelty is that, in rotor of compressor with working blades secured by leaf lock with bending of lock shank to rotor axle behind disk rim, said lock arranged on last working blade of last disk of compressor is made with T-shaped projection from side opposite to bend, and cavity with surfaces enclosing lock shank bend is made in working ring adjoining disk rim.
EFFECT: improved reliability of compressor by excluding deformation of lock when engine is operating.
4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS-TURBINE ENGINE COMPRESSOR | 2002 |
|
RU2235919C2 |
| AXIAL COMPRESSOR STAGE | 2007 |
|
RU2347110C1 |
| GAS-TURBINE ENGINE COMPRESSOR STATOR | 1999 |
|
RU2156381C1 |
| HIGH-PRESSURE MULTISTAGE COMPRESSOR OF GAS-TURBINE ENGINE | 2005 |
|
RU2317447C2 |
| HIGH-PRESSURE COMPRESSOR OF GAS-TURBINE ENGINE | 2003 |
|
RU2243419C2 |
| GAS-TURBINE ENGINE | 2001 |
|
RU2204043C2 |
| AXIAL-FLOW MULTISTAGE COMPRESSOR OF GAS-TURBINE ENGINE | 2003 |
|
RU2243418C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
| COMPRESSOR | 2004 |
|
RU2253758C1 |
| GAS-TURBINE ENGINE COMPRESSOR | 2000 |
|
RU2189499C2 |
