Authors: Michele Marconcini Roberto Pacciani Andrea Arnone
Publish Date: 2015/11/10
Volume: 24, Issue: 6, Pages: 526-534
Abstract
The aerodynamic performance of a gas turbine nozzle vane cascade was investigated over a range of Mach and Reynolds numbers The work is part of a vast research project aimed at the analysis of fluid dynamics and heat transfer phenomena in cooled blades In this paper computed results on the “solid vane” without cooling devices are presented and discussed in comparison with experimental data Detailed measurements were provided by the University of Bergamo where the experimental campaign was carried out by means of a subsonic wind tunnel The impact of boundary layer transition is investigated by using a novel laminar kinetic energy transport model and the widely used LangtryMenter γRe θt model The comparison between calculations and measurements is presented in terms of blade loading distributions total pressure loss coefficient contours downstream of the cascade and velocity/turbulenceintensity profiles within the boundary layer at selected blade surface locations at midspan It will be shown how transitional calculations compare favorably with experiments
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