FIELD: manufacture of aircraft engines; compressors of gas-turbine engines.
SUBSTANCE: proposed blade ring of axial-flow compressor includes outer ring with radial holes; blades secured on this ring and on inner ring form inter-blade passages; holes in outer ring are located before leading edge of blades and behind trailing edge; each hole located before leading edge of blade is communicated by means of separate passage with one of holes located behind trailing edge of blade. Passages form waveguides together with holes; they may be made in form of tubes located above outer ring; length of waveguides exceeds distance between holes forming it.
EFFECT: reduction of amplitude of pressure fluctuation generated by rotor blades, thus reducing vibration stresses in compressor structural members.
3 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOMACHINE OVERROTOR DEVICE | 2001 |
|
RU2199680C2 |
| TURBO-MACHINE STAGE | 1998 |
|
RU2148732C1 |
| AXIAL-FLOW COMPRESSOR STAGE | 2004 |
|
RU2269680C1 |
| TURBOMACHINE OVERROTOR DEVICE | 2000 |
|
RU2192564C2 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| DEVICE FOR AERODYNAMIC SEALING OF CLEARANCE BETWEEN BUTT ENDS OF AXIAL-FLOW COMPRESSOR ROTOR BLADES AND TURBINE SHELL | 2004 |
|
RU2261372C1 |
| COMPRESSOR FAN STAGE (VERSIONS) | 2005 |
|
RU2294461C1 |
| VORTEX COMPRESSOR | 1992 |
|
RU2032836C1 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
| CENTRIFUGAL COMPRESSOR RADIAL DIFFUSOR | 0 |
|
SU879047A1 |
