Evolution of Swirl Boundary Layer and Wall Stall at Part Load: A Generic Experiment

Abstract

The influence of Reynolds number, roughness and turbulence on the onset of wall stall is up to now not sufficiently understood. To shed some light onto the interdependency of near wall flow with growing swirl component, the simplest “machine” is tested. The apparatus we examine is a circular pipe at rest followed by a rotating co-axial pipe segment. In the sense of a generic experiment this machine represents a very basic model of the inlet of an axial machine. Due to the wall shear stress a swirl boundary layer is formed in the rotating pipe segment, interacting with the axial boundary layer. The evolution of the swirl velocity profile with increasing axial distance from the rotating pipe inlet is measured for various Reynolds numbers, flow numbers and degrees of turbulence by means of Laser Doppler Anemometry. We observe a self-similarity in the swirl velocity profile, for subcritical flow number and develop a scaling law for the velocity distribution in the transition section of a rotating pipe. At critical flow number the boundary layer is separating, resulting in a ring vortex at the inlet of the rotating pipe. Our work fills the gap of previous experimental works, with respect to high Reynolds numbers and low flow numbers. The parameter field we examine is most relevant for turbomachinery application and wall stall. In addition our boundary layer resolution is sufficient to resolve the swirl boundary layer thickness. Only this high resolution enables us to generalize the experimental findings by means of a similarity distribution of the velocity profile within the swirl boundary layer.

A Second Turbulent Regime When a Fully Developed Axial Turbulent Flow Enters a Rotating Pipe

“…When a thin laminar boundary layer enters a rotating pipe for ϕ > 0.71, the circumferential velocity profile transforms and both boundary layers are thickened at the inlet of a rotating pipe [6]. There, for a smaller flow number with a thin or fully developed turbulent or a thin laminar axial boundary layer, the circumferential velocity profile follows u φ = (1 − y/δ S ) 2 for an attached flow [1,2,4,5]. For the fully developed axial turbulent flow, the swirl boundary layer thickness follows…”

“…A strong influence of the swirl on the axial momentum balance is observable for small flow numbers ϕ 1. The swirl causes flow separation for a small flow number and a measured stability map for part load recirculation is given [1][2][3][4]. When the flow separates, the circumferential velocity profile differs from the parabolic one [1,2,4].…”

“…The swirl causes flow separation for a small flow number and a measured stability map for part load recirculation is given [1][2][3][4]. When the flow separates, the circumferential velocity profile differs from the parabolic one [1,2,4]. Stratford's criteria [20] is applied to derive the critical flow number for incipient separation analytically.…”

“…By rotating the pipe, a second boundary layer in circumferential direction is produced by viscosity and develops. It is the so called swirl boundary layer with thicknessδ S [1][2][3][4][5]; see Fig. 1.…”

High-Sensitivity Single Thermopile SOI CMOS MEMS Thermal Wall Shear Stress Sensor

“…Much of the drag force experienced by moving vehicles (aerial, terrestrial, and marine) is directly caused by the wall shear stress [1], [2]. Furthermore, measurements of τ may be used to study the complex physics of the near-wall boundary layers [3], [4], which may exhibit laminar, turbulent, separated or transitional flow [5], [6]. Wall shear stress sensors are also employed in industrial applications (e.g.…”