The present study is the second half of a piece of work carried out in collaboration with SNECMA. It investigates shaped hole film cooling, numerically and experimentally. The aim of this paper is the experimental analysis of shaped hole film cooling on a large scale turbine blade (1.4 m chord).
The test section is a large scale turbine inlet guide vane cascade. The test airfoil is equipped with a row of nine 50° sloped shaped holes. They are located on the suction side at 20% of the curvilinear length of the blade from the stagnation point. The inlet film cooling hole diameter is 12 mm.
The test jet flow is heated to 55°C above the crossflow temperature. Velocity and temperature field measurements have been done to obtain mean and fluctuating values. The results are compared to those obtained by Béral1 on the same experimental apparatus and in the same test conditions, for a row of cylindrical holes.
The present study is the second half of a two part work carried out in collaboration with SNECMA which tends to investigate a shaped hole film cooling experimentally and numerically. The aim of this paper is the numerical study of 3D phenomena induced by cylindrical and shaped hole film cooling on a flat wall.
The two calculations show up classical structures such as horseshoe or kidney vortices and their differences according to the shape configuration. A detailed study demonstrates their influence on the jet behaviour. Comparing both cases reveals the impact of shaping on the velocity field and vortex motions.
The calculations were performed by resolving the 3D Navier‐Stokes equations associated with a k‐ε turbulence model. The solver is the CANARI code developed by ONERA.
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