1 Copyright © 2006 by ASME Proceedings of ASME Turbo Expo 2006 Power for Land, Sea and Air May 8-11, 2006, Barcelona, Spain GT2006-90959 UNSTEADY FLOW PHYSICS AND PERFORMANCE OF A ONE-AND-1/2-STAGE UNSHROUDED HIGH WORK TURBINE T. Behr, A. I. Kalfas, R. S. Abhari Turbomachinery Laboratory Swiss Federal Institute of Technology 8092 Zurich, Switzerland contact: behr@lsm.iet.mavt.ethz.ch ABSTRACT This paper presents an experimental study of the flow mechanisms of tip leakage across a blade of an unshrouded turbine rotor. It shows the design of a new one-and-1/2- stage, unshrouded turbine configuration, which has been developed within the Turbomachinery Laboratory of ETH Zurich. This test case is a model of a high work (∆h/u 2 =2.36) axial turbine. The experimental investigation comprises data from unsteady and steady probe measurements, which has been acquired around all the bladerows of the one-and-1/2-stage, unshrouded turbine. A newly developed 2-sensor Fast Response Aerodynamic Probe (FRAP) technique has been used in the current measurement campaign. The paper contains a detailed analysis of the unsteady interaction between rotor and stator blade rows, with particular attention paid on the flow in the blade tip region. It has been found that the pressure field of the second stator row has a influence on the development of the tip leakage vortex downstream of the rotor. The vortex is modulated by the stator profiles and shows variation in size and relative position to the rotor trailing edge when it stretches around the stator leading edge. Thereby a deflection of the tip leakage vortex has been observed, which expresses in a varying circumferential distance between two neighboring vortices of ±20% of a rotor pitch. Furthermore, a significant influence of quasi-stationary secondary flow features of the upstream stator row on the secondary flow of the rotor has been detected. The geometry data of the one-and-1/2-stage turbine will be available to the public domain for validation and improvement of numerical tools. NOMENCLATURE c Absolute flow velocity [m/s] c p Specific heat capacity at constant pressure [J/kg K] Cps Static pressure coefficient, Cps = p − p 3 p t0 − p 3 [-] Cpt Total pressure coefficient, Cpt = p t − p 3 p t0 − p 3 [-] h Enthalphy [kJ/kg] m & Massflow [kg/s] M Torque [N m] p Pressure [Pa] R Perfect gas constant [J/kg K] r Radius [m] T Temperature [K] u Rotational speed [m/s] Greek ε Turning angle [°] ψ Loading coefficient (ψ=∆h/u 2 ) [-] φ Flow coefficient φ=c x /u [-] φ Flow yaw angle (positive in rotor turning direction) [°] γ Flow pitch angle (positive towards casing) [°] κ Isentropic coefficient (κ=c p /c v ) [-] ω Rotational velocity [1/sec] Abbreviations 5HP 5-Hole Probe CFD Computational Fluid Dynamics CoG Center of Gravity FRAP Fast Response Aerodynamic Probe