Patent ID: 8961135
Filing Date: 2015-02-24
Classification: F01D

Abstract:
1. In a turbine engine defining an axial flow path for a working gas, an assembly of flow directing members comprising: a plurality of airfoils mounted to respective platforms, each airfoil including a span dimension extending radially outwardly through the flow path and a chord dimension generally extending in an axial direction of the flow path, and the platforms comprising endwalls facing the flow path and defining a circumferential boundary of the flow path; the platforms comprising an adjoining pair of platforms having side edges defining matefaces adjoining each other and forming a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms, wherein the mateface gap comprises a non-linear path; the working gas defining a flow field adjacent to the endwalls comprising streamlines extending generally transverse to the axial direction from a concave pressure side of a first airfoil toward an adjacent second airfoil; and the mateface gap comprising a transverse portion that traverses a direction of the streamlines generally perpendicular to the streamlines at the location of the transverse portion, and the mateface gap comprising an aligned portion extending from a curved or angled transition point between an upstream end of the transverse portion and the aligned portion that wherein the aligned portion is aligned generally parallel with the direction of the streamlines at the location of the aligned portion.