FIELD: turbo-machine manufacture; axial- flow compressors of gas-turbine engines. SUBSTANCE: blade has feather and dovetail root with slots accommodating damping inserts incorporating spiral sections which are arranged within them so that they are intersecting many times in all directions and are compressed to partially fill insert space with spiral material. EFFECT: improved service life and reliability.
Title | Year | Author | Number |
---|---|---|---|
TURBO-MACHINE STAGE | 1998 |
|
RU2148732C1 |
AXIAL COMPRESSOR BLADE MAKING METHOD | 1999 |
|
RU2176335C2 |
METHOD OF SEALING GAS-TURBINE ENGINE ASSEMBLIES | 1999 |
|
RU2164632C2 |
GAS TURBINE DRIVE OF LIQUID-PROPELLANT ROCKET ENGINE | 1999 |
|
RU2168051C2 |
CRYOGENIC PUMP TEST STAND | 2000 |
|
RU2213264C2 |
ANNULAR COMBUSTION CHAMBER | 1996 |
|
RU2161756C2 |
METHOD OF CHECKING TURBOPUMP SET BEARING FOR WEAR | 1999 |
|
RU2175411C2 |
GAS LIQUEFYING PROCESS | 2000 |
|
RU2204771C2 |
METHOD OF PRODUCING SLIDE BEARING | 2001 |
|
RU2267034C2 |
TURBOPUMP SET | 1999 |
|
RU2175407C2 |
Authors
Dates
2000-10-20—Published
1996-06-18—Filed