Abstract:

As a result of the interaction with the main flow of the complex three-dimensional secondary flow structures formed in the wing roots and wing end areas of the axis turbines, high levels of aerodynamic losses are produced. In this study, gas turbine was studied by combining two methods used independently in literature in order to reduce the aerodynamic losses derived from secondary flow that occur in the flow between the wings. These methods are the methods of adding barriers to the inter-wings area and depleting the box geometry applied to the compressor wings in literature. In this direction first the barrier and yiv unapplicated rotor state were studied, then the flow areas and losses for geometries formed by combining the five different geometries of the barrier state and finally the two different yiv geometries, together with each barrier. In the assessment of losses, the method was applied for the differences seen in the total pressure of the entrance and exit of the inter-wings area and for the conversion of these differences into the mass average total pressure loss rate. The results of the analyses have shown that the barriers alone and if necessary with the yiv have reduced the loss rates. As a result, the maximum profit was achieved by the joint application of the 2.0x1.7 mm barrier and the 1.5x5.2 mm wide yiv geometry and a 3% improvement in the total pressure loss rate was achieved.

Keywords: