| 摘要 |
Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (s/t distribution) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.
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