Main Annulus Gas Path Interactions - Turbine Stator Well Heat Transfer

This paper summarises the work of a five year research programme into the heat transfer within cavities adjacent to the main annulus of a gas turbine. The work has been sponsored by the European Union and several gas turbine manufacturers, also involving a number of universities working together in close collaboration. The principal objective of the study has been to develop and validate computer modelling methods of the cooling flow distribution and heat transfer management, in the environs of multi-stage turbine disc rims and blade fixings, with a view to maintaining component and sub-system integrity, whilst achieving optimum engine performance and minimising emissions. A fully coupled analysis capability has been developed using combinations of commercially available and in-house computational fluid dynamics and finite element thermomechanical modelling codes. A two-stage turbine test rig has been developed and improved to provide good quality heat transfer test data with which to validate the analysis methods. A cooling flow optimisation study has also been performed to support a redesign of the turbine stator well cavity, to maximise the effectiveness of cooling air supplied to the disc rim region. The benefits of this design change have also been demonstrated on the rig. A brief description of the test rig facility will be provided together with some insights into the successful completion of the test programme. Comparisons will be provided of disc rim cooling performance, for a range of cooling flows and geometry configurations.