Abstract

The main objective of the presented paper is the investigation of a flow structure and parameters distribution downstream of combustor simulator and its effect on turbine inlet. The investigations are carried out by means of numerical simulations for combustor and turbine nozzle guide vane configuration existing at test rig in DLR Goettingen. As the effect, the hot spot location for different relative positions of the swirler and nozzle guide vanes is shown. The presented results are obtained within a pre-test simulations supporting the final design of the test section and they allow to draw conclusions for the required limiting cases investigated experimentally. The location of the hot spot is highly important for thermal loading of the first stage rotor.