AG Turbo DigiTecT 3.3 : Robust axial compressor stages for axial-radial compressors
AG Turbo DigiTecT 3.3 : Robust axial compressor stages for axial-radial compressors
Project Manager: |
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Processor: |
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Financing: |
BMWK, Rolls Royce Germany |
scientific cooperation: |
AG TURBO, DigiTecT |
Duration: |
03/2023 - 02/2026 |
Description:
The combination of axial with a final radial compressor stage makes it possible to achieve high pressure ratios even in small compressors / gas turbine plants, while reducing the number of components. A final radial compressor stage leads to special requirements for the axial stages upstream. Due to the different characteristics of axial and radial stages, the stage matching has to be considered in more detail. This is where the planned project comes in and analyzes the interaction between axial and radial compressor stages. In particular, the last remaining axial compressor stage will be investigated with regard to its stability and the configuration of the guide vane. These investigations should enable a further increase in the compressor pressure ratio and thus an increase in overall efficiency in small flexible gas turbine plants.
The boundary conditions for an axial-radial compressor in a highly flexible small gas turbine are to be determined at the outset by simplified modeling at the system level. Based on these requirements, an axial-radial compressor is to be designed in terms of fluid mechanics. Detailed numerical analyses of the interaction of the axial compressor stages with the final radial stage with regard to the configuration of the last guide vane of the axial part and the channel contour at the transition to the radial impeller are to provide information on the optimum configuration. In parallel, experimental comparisons of the axial stage with a conventional guide vane and swirling discharge and a configuration with a tandem guide vane for swirl-free discharge with simultaneous deflection of the flow to a smaller radius are to be carried out on a test compressor. For the latter, an extensive design adaptation of the compressor at the discharge is required. The findings of the experimental tests are then to be transferred numerically to a realistic, compressible configuration at higher Mach numbers and evaluated in combination with the following radial compressor stage.