ROW OF LONG AND SHORT CHORD LENGTH AND HIGH AND LOW TEMPERATURE CAPABILITY TURBINE AIRFOILS

摘要

A gas turbine engine turbine stage (19) has an annular row of turbine airfoi ls (22) including a first plurality (41) of first airfoils (44) having a first chord length (CL1) and a second plurality (43) of second airfoils (46) having a second chord length (CL2) shorter than the first chord length. At least one of the second airfoils is circumferentially disposed between adjacent each pair (66) of the first airfoils. A second leading edges (47) of the second airfoils are located downstream of first leading edges (53) of the first airfoils. The first and second airfoils have different first and second temperature capabilities respectively and the first temperature capability is greater than the second temperature capability. The first and second airfoil s may be made from different alloys and/or the second airfoils may be constructed to use lower amounts of cooling airflow than the first airfoils. More than one of the second airfoils may be disposed between each pair (66) of the first airfoils.