G. K. Serovy

TL;DR: In this article, a model of the spanwise variation of the three-dimensional flow effects on deviation is proposed for middle-stage rotors and stators, which is taken as the difference above or below that predicted by blade element theory at any spanwise location.

TL;DR: In this article, a method for computing the flow field around an arbitrary airfoil cascade on an axially symmetric blade-to-blade surface was developed which takes into account the development and separation of the blade surface boundary layers and mixing in the wake.

TL;DR: In this article, the authors derived three-dimensional spanwise pressure loss and flow angle deviation variations from NASA, university, and industrial sources from middle-stage research compressors operating near design point.

TL;DR: A cascade geometry derived from a research program on high-throughflow, transonic, axial flow compressors was tested with similar supersonic entrance flow conditions in three linear cascade test facilities.