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| Abstract: |
| Successfully utilized non-axisymmetric endwalls to enhance turbine efficiencies (aerodynamic and turbine inlet temperatures) by controlling the characteristics of the secondary flow in a blade passage. This is accomplished by steady-state numerical hydrodynamics and deep knowledge of the field of flow. Because of the interaction between mainstream and purge flow contributing supplementary losses in the stage, non-axisymmetric endwalls are highly susceptible to the inception of purge flow exit compared to the flat and any advantage rapidly vanishes. The conclusions reveal that the supreme endwall pattern could yield a lowering of the gross pressure loss at the design stage and is related to the size of the top-loss location being productively lowered. This has led to diminished global thermal exchange lowered in the passage of the vane alone. The reverse flow adjacent to the suction side corner of the endwall is migrated farther from the vane surface, as the deviated pressure spread on the endwall accelerates the flow and progresses the reverse flow core still downstream. The depleted association between the tornado-like vortex and the corner vortex adjacent to the suction side corner of the endwall is the dominant mechanism of control in the contoured end wall. In this publication, we show that the non-axisymmetric endwall contouring by selective numerical shape change method at most prominent locations is advantageous in lowering the thermal load in turbines to augment the net heat flux reduction as well as the aerodynamic performance using multi-objective optimization. |
| Key words: endwall contouring turbine vane heat transfer phantom cooling coolant injection net heat flux reduction aerodynamic performance |
| DOI：10.11916/j.issn.1005-9113.2023037 |
| Clc Number:TH3 |
| Fund: |
