FIELD: engines and pumps.
SUBSTANCE: invention relates to turbomachines and, in particular, to annular element (13) of a turbomachine casing. Inner face (14), delimits a flow channel for the flow of a working fluid of the turbomachine. Said element comprises outer face (15), and damper (18). Damper (18) comprises plurality of adjacent elastic coils (18a, 18b, 18c) clamped around surface of revolution (15a) of outer face (15), in such a way as to exert pressure against said surface of revolution (15a) and between adjacent coils.
EFFECT: enabling damping of acoustic and vibration loads.
10 cl, 5 dwg
Title | Year | Author | Number |
---|---|---|---|
GAS TURBINE ENGINE STATOR AND GAS TURBINE ENGINE WITH SUCH STATOR | 2008 |
|
RU2486351C2 |
METHOD OF CREATING FREQUENCY INCONSISTENCY BETWEEN BLADES OF THE VANE WHEEL OF A GAS TURBINE ENGINE AND CORRESPONDING VANE WHEEL | 2016 |
|
RU2689489C1 |
COMPRESSOR OF AXIAL GAS-TURBINE ENGINE WITH ROTOR OF OPPOSITE ROTATION | 2015 |
|
RU2703888C2 |
LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
IMPROVED METHOD FOR MANUFACTURING SHELL MOULD FOR PRODUCTION BY LOST-WAX CASTING OF BLADED ELEMENTS OF AN AIRCRAFT TURBINE ENGINE | 2015 |
|
RU2685614C2 |
DEVICE FOR STOPPING ROTATION OF VANE SECTORS OF STRAIGHTENING CASCADES BY STRAPS IN CONNECTING PLANES OF HOUSING AND TURBINE WITH SUCH DEVICE | 2004 |
|
RU2293187C2 |
SYSTEM FOR ROTATING THE ROTOR OF A GAS TURBINE ENGINE AND ROTOR OF A GAS TURBINE ENGINE | 2018 |
|
RU2767258C2 |
DEVICE FOR AERODYNAMIC SEALING OF CLEARANCE BETWEEN BUTT ENDS OF AXIAL-FLOW COMPRESSOR ROTOR BLADES AND TURBINE SHELL | 2004 |
|
RU2261372C1 |
DEVICE TO BRAKE TURBINE OF GAS TURBINE ENGINE IN COLLAPSE OF TURBINE SHAFT, AND DOUBLE-STEP GAS TURBINE ENGINE | 2008 |
|
RU2469194C2 |
Authors
Dates
2018-11-15—Published
2014-11-04—Filed