Blade tip aerodynamic loss results from experimental and numerical investigations are presented for engine representative conditions downstream of a blade row with an exit Mach number Mexit of 1.0, and an exit Reynolds number Reexit of 1.27×106 (based on axial chord). These results are presented for three different tip gaps of 0.5, 1.0, and 1.5 percent relative to engine-equivalent blade span. Experimental data are obtained by traversing a specially-made and calibrated three-hole pressure probe as well as a single-hole probe one axial chord downstream of the blade within the Oxford High Speed Linear Cascade research facility. Three-dimensional RANS CFD numerical predictions are conducted using the Rolls-Royce HYDRA numerical prediction code for steady flow with the Spalart-Allmaras (SA) turbulence model. Included are detailed distributions of stagnation pressure losses, and pitch-wise flow angle. Local total pressure data and mass-averaged total pressure loss coefficients show that the strength of the tip leakage vortex decreases as the tip gap decreases. Magnitudes of the pitch-wise flow angle increase within over-tip leakage vortices, as these vortices become stronger and the tip leakage flow increases. The most important difference between experimental and numerical results is in relation to the passage vortex signatures, which are more apparent for all three tip gap values within the numerical results. The effects of relative casing motion and tip clearance are also examined and discussed, and show that the relative casing movement has a relatively small impact on the size of the over-tip leakage vortex at the medium (1.0% of span) and large (1.5% of span) tip gaps, with more noticeable impact at the smallest tip gap (0.5% of span).
This paper describes the development of heated double-sided thin film gauge configurations for transient heat transfer measurements. By heating the substrate it is possible to measure the heat flux over a range of surface temperatures and deduce the adiabatic wall temperature and the external heat transfer coefficient. The accuracy of the measurement depends on the stability of the regression of heat flux against wall temperature and can be improved by extending the range of wall temperature over which the regression is performed. In this paper we compare two methods of local heating: double-sided gauges with an underside thin film heater and self-heating double-sided gauges. Both arrangements have been used in the Oxford Turbine Research Facility to measure the heat transfer on the uncooled turbine shroud of the MT1 high-pressure turbine stage at engine-representative conditions. These measurements yield improved regressions compared to conventional techniques to determine the adiabatic wall temperature and the heat transfer coefficient.
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