Abstract
In this paper, we present the a three-dimensional time-linearized unsteady Euler solver for computing unsteady flows in multistage turbomachines. Using this approach, each blade row is modeled with a computational grid spanning a single blade passage. Within each blade passage, several time-linearized un- steady solutions are computed, one for each of several modes re- tained in the model. Each spinning mode has its own frequency and interblade phase angle. These various solutions are coupled together at the inter-row bound- aries between the blade rows. Results are presented for several geometries, and demonstrate the accuracy and efficiency of the method, as well as the impor- tance of multistage effects. In particular, we show that multistage effects can strongly affect the aerodynamic loads acting on a given blade row. Further- more, the method presented is highly efficient. For example, to perform a flutter calculation requires only about three times the CPU time of one steady flow computation for each interblade phase angle and frequency considered.
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