The Formation of Counter-Rotating Vortex Pair and the Nature of Liftoff-Reattachment in Film-Cooling Flow

Hao Li,Wahid Ghaly,Ibrahim Hassan

doi:10.3390/fluids1040039

Abstract

Traditionally, the formation of the Counter-Rotating Vortex Pair (CRVP) has been attributed to three main sources: the jet-mainstream shear layer where the jet meets with the mainstream flow right outside the pipe, the in-tube boundary layer developing along the pipe wall, and the in-tube vortices associated with the tube inlet vorticity; whereas the liftoff-reattachment phenomenon occurring in the main flow along the plate right downstream of the jet has been associated with the jet flow trajectory. The jet-mainstream shear layer has also been demonstrated to be the dominant source of CRVP formation, whereby the shear layer disintegrates into vortex rings that deform as the jet convects downstream, becoming a pair of CRVPs flowing within the jet and eventually turning into the main flow direction. These traditional findings are assessed qualitatively and quantitatively for film-cooling flow in gas turbines by simulating numerically the flow and evaluating the extent to which the traditional flow phenomena are taking place particularly for CRVP and for flow liftoff-reattachment. To this end, three flow simulation cases are used; they are referred to as 1—the baseline case; 2—the free-slip in-tube wall case (FSIT); and 3—the unsteady flow case. The baseline case is a typical film-cooling case. The FSIT case is used to assess the in-tube boundary layer. Cases 1 and 2 are simulated using the Reynolds-averaged Navier-Stokes equations (RANS), whereas Case 3 solves a Detached Eddy Simulation (DES) model. It is concluded that decreasing the strength of the CRVP, which is the case for e.g., shaped holes, provides high cooling performance, and the liftoff-reattachment phenomenon was thus found to be strongly influenced by the entrainment caused by the CRVP, rather than the jet flow trajectory. These interpretations of the flow physics that are more relevant to gas turbine cooling flow are new and provide a physics-based guideline for designing new film-cooling schemes.

Highlights

Advanced gas turbines operate at extremely high temperatures to achieve high engine performance
To assess the relative importance of each of the three sources that affect the formation and development of the Counter-Rotating Vortex Pair (CRVP), the flow fields for Cases 1–3 described in the previous section, are simulated numerically and used to visualize and analyze the CRVP formation and development in the main flow direction
Because in the present case the jet enters at 35◦ and at a blowing ratio of 1, these differences have a drastic impact on interpreting the flow physics as will be evident in what follows

Summary

Introduction

Advanced gas turbines operate at extremely high temperatures to achieve high engine performance. Cooling techniques are indispensable to ensure the durability of the turbine components by protecting them from the hot mainstream gases. Film cooling is a widely used cooling technique. While protecting the turbine blades, film cooling impacts the engine performance negatively, when the coolant penetrates the mainstream. Research efforts have been dedicated to improving film-cooling efficiency. Film cooling is accomplished by injecting jets of colder air bled from the compressor over the turbine blade vanes which gives rise to a series of fluid

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Conclusion