Abstract
The contribution deals with investigation of flow in the axial stage of the experimental turbine with reaction blading. The main intention is to evaluate an effect of the secondary flows on the efficiency. Most important source of the secondary flows is an outflow from the seal above the rotor shroud. Other sources of the secondary flows are axial gaps between the rotor disc and the side walls of the stator blade channel and the outlet diffuser. Results of the numerical simulation are compared with the experimental data. In this work there is also studied possibility of transfer the outlet dissipation structures at the inlet of the stage as an approach to modelling of the multistage configuration.
Highlights
Flow in an axial turbine stage of an experimental turbine is investigated under the project of applied research TA04020129 [1], which deals with research of flow in multistage configuration of the axial turbine stages
In case of multistage configuration of the axial turbine stage the inlet flow field to the stage is influenced by the flow through previous stages
The order of the axial turbine stage in multistage configuration was simulated through transferring of the radial distributions of the outlet flow field parameters on the inlet boundary of the computational domain
Summary
Flow in an axial turbine stage of an experimental turbine is investigated under the project of applied research TA04020129 [1], which deals with research of flow in multistage configuration of the axial turbine stages. The influence of previous stages is in this work simulated using transfer of the radial distribution of the outlet flow field parameters to the inlet boundary of the same stage. This approach is, feasible only using numerical simulation, but not experimentally. The axial distance between the stator trailing edge and the rotor leading edge (on the hub-diameter) is about 25% of the blade height This dimension corresponds to the experimental configuration, where the flow field behind the stator wheel was traversed by the pneumatic probes. The plane of evaluation of the radial distribution of the outlet flow field parameters was chosen in distance above 30% of the axial chord of the rotor blade behind the rotor trailing edge (on the hub-diameter). Distribution of the outlet flow field parameters in this plane is influenced by the flow across the axial gap between the rotor disc and the hub-wall of the outlet diffuser and in tip-region it is influenced by the stream from the above-shroud seal
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