Patent attributes
A stage (10) of stationary vanes (12) of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (14); and an energy damping system (30) having a plurality of connection assemblies (32), each joining respective adjacent stationary vanes. A spring (34) is configured to circumferentially bias respective adjacent stationary vanes, and a damper (36) is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.
