Pressure Bifurcation Phenomenon on Supersonic Blowing Trailing Edges

Abstract

Turbine blades operating in transonic–supersonic regime develop a complex shock wave system at the trailing edge: a phenomenon that leads to unfavorable pressure perturbations downstream and can interact with other turbine stages. Understanding the fluid behavior of the area adjacent to the trailing edge is essential in order to determine the parameters that have influence on these pressure fluctuations. Colder flow, bled from the high-pressure compressor, is often purged at the trailing edge to cool the thin blade edges, affecting the flow behavior and modulating the intensity and angle of the shock waves system. However, this purge flow can sometimes generate nonsymmetrical configurations due to a pressure difference that is provoked by the injected flow. In this work, a combination of Reynolds-averaged Navier–Stokes simulations and a global stability analysis is employed to explain the physical reasons of this flow bifurcation. By analyzing the features that naturally appear in the flow and become dominant for some value of the parameters involved in the problem, an antisymmetrical global mode, which is related to the sudden geometrical expansion of the trailing-edge slot, is identified as the main mechanism that forces the changes in the flow topology.