AERODYNAMIC LOSSES FROM TURBINE COMPONENTS WITHIN GAS TURBINE ENGINES

摘要

A survey of recent research on aerodynamic loss investigations for turbine components of gas turbine engines is presented.Experimental and numerically predicted results are presented from investigations undertaken over the past 60 plus years.Of interest are losses from the development of secondary flows from airfoil/endwall interactions,and from cambered airfoils.The most important of the airfoil/endwall secondary flows are passage vortices,counter vortices,and corner vortices.The structure and development of these secondary flows are described as they affect aerodynamic performance within and downstream of turbine passage flows in compressible,high speed flows with either subsonic or transonic Mach number distributions,as well as within low-speed,incompressible flows.In regard to profile losses,considered are cambered airfoils with no film cooling.Here,experimentally measured and numerically predicted variations of streamwise development,freestream turbulence intensity,and exit Mach number are addressed as they influence integrated total pressure losses,area-averaged loss coefficients,mass-averaged total pressure loss coefficients,and Integrated Aerodynamic Loss.