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- W4387126807 abstract "Abstract Single-stage axial pressure compound and two-row velocity compound supersonic turbines have a very high specific work, which allows for high power levels at high-pressure ratios and small flow rates in a very compact dimensional envelope. However, despite their mechanical simplicity, the supersonic aerodynamic effects in these turbines are very complex. There are many design and analysis methodologies for these turbines, which are currently used in the industry. Nevertheless, several important parameters are still insufficiently investigated. In an earlier paper (GT2022-83387), the authors considered the influence of convergent-divergent nozzle arrangement parameters on aerodynamic losses and overall supersonic turbine performance, which partially closed the knowledge gap. However, the flow at the nozzle ring’s exit is influenced by the rotor blades, especially by the geometry of the blades leading edge; axial clearance between the nozzle and rotor cascades; and a combination of other nozzle arrangement parameters at different Mach numbers. This is not well studied and needs to be further investigated, which will be the focus of this paper. This paper examines the qualitative and quantitative influence on aerodynamic losses of the rotor blade, such as the leading edge geometry; axial clearance; and meridional flow angle at the exit of convergent-divergent conical nozzles. The methods utilized to determine the influence of these parameters are provided and the results are discussed. An approach to incorporate the quantitative corrections of the nozzle loss models is presented and a comparison with experimental data is performed. The incorporated models allow for designing and analyzing the supersonic turbines considering more parameters enabling the opportunity to fine-tune the design to specific requirements with higher confidence and accuracy." @default.
- W4387126807 created "2023-09-29" @default.
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- W4387126807 date "2023-06-26" @default.
- W4387126807 modified "2023-10-18" @default.
- W4387126807 title "Influence of Rotor Blades on Convergent-Divergent Nozzle Aerodynamics and Overall Supersonic Turbine" @default.
- W4387126807 doi "https://doi.org/10.1115/gt2023-101760" @default.
- W4387126807 hasPublicationYear "2023" @default.
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