Purge Flow Effects on Rotor Hub Endwall Heat Transfer with Extended EndwallContouring into the Disk Cavity

Abstract

Efficiency improvements for gas turbines are strongly coupled with increasing turbine inlet temperatures. This imposes new challenges for designers for efficient and adequate cooling of turbine components. Modern gas turbines use bleed air from the compressor to inject into the stator/rotor rim seal cavity to prevent hot gas ingestion from the main flow, while cooling the rotor disk. This purge flow interacts with the main flow field and static pressure field imposed by the turbine blades. The complex interaction causes nonuniform and jet-like penetration of the purge flow into the main flow field and therefore affects the endwall heat transfer on the rotor. In order to improve the understanding of purge flow effects on rotor hub endwall heat transfer, measurements in the 1.5-stage axial turbine facility LISA at ETH Zurich have been performed. An unshrouded, high-pressure representative turbine design with 3D blading and extended endwall contouring of the rotor into the cavity seal has been tested. A state-of-the-art measurement setup with a high-speed infrared camera and thermally managed rotor insert has been used to perform high-resolution heat transfer measurements on the rotor. Three different purge flow rates were investigated with regard to hub endwall heat transfer. Additionally, steady-state CFD simulations were performed to complement the experiments. It was found that the local heat transfer rate changes up to ±20% depending on the purge flow rate. The main part of the purged air is ejected at the endwall trough location and swept towards the rotor suction side caused by the interaction of main flow and the cavity extended endwall design. The presence of low momentum purge flow is locally reducing the heat transfer rate. Changes in adiabatic wall temperature and heat transfer depending on purge rate are observed from the platform start up to the cross passage migration of the secondary flow structures.

High-resolution heat transfer measurements on a rotating turbine endwall with infrared thermography

“…The experimental setup was first presented in Gazzini et al [16] and the sensitivity and uncertainty of the method was generally judged as adequate to meet the requirements in aero-thermal gas turbine studies with the focus on the rotor hub side region. A first technical study on the effect of different rim seal injection rates on the rotor endwall is documented in Gazzini et al [17] and continued by Hänni et al [18].…”