Blade-forced vibration effects on turbomachinery rotor-stator interaction
Conference Paper
Overview
Identity
Other
View All
Overview
abstract
Understanding rotor-stator interaction is essential for the design of turbomachines with increased performance and improved reliability. The sources of unsteadiness currently modeled in the rotor-stator interaction studies include potential flow interaction, wake interaction, hot streak interaction, vortex shedding and shock/boundary layer interaction. The objective of this paper is to investigate the effects of blade-forced vibration on the rotor-stator interaction in turbomachinery. An existing parallelized solver of the Euler/Navier-Stokes equations for multi-stage compressors and turbines has been extended to model vibrating rotor blades. This numerical implementation can model rotor blades that vibrate with a plunging and/or pitching motion. The rotor blade vibration is superimposed on the blade rotation. The numerical algorithm has been used to simulate the flow in a two-stage turbine. Assuming that the first-stage rotor blades were plunging with an amplitude equal to 10% of the chord and the second-stage rotor blades were pitching with an amplitude of 5 deg, both rows vibrating with a frequency of 1230 Hz, the total-to-total efficiency decreased approximately 2 points compared to the rigid blade turbine. Consequently, blade-forced vibration can significantly affect the rotor-stator interaction in turbomachinery. 2001 by the American Institute of Aeronautics and Astronautics Inc.
