Patent ID: 8192154
Filing Date: 2012-06-05
Classification: F01D,Y02T,Y10S

Abstract:
1. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: said inner peripheral wall (Ch) between a leading edge (LE) and a trailing edge (TE) of the inlet guide vane (V) comprises: said inner peripheral convex portion (Cv wherein each of said plurality of inlet guide vanes (V) includes a chord length in an axial direction that is larger relative to a span length in the radial direction with the leading edge being inclined to the upstream side at a tip side, outer side in the radial direction, as compared to the hub side, inner side in the radial direction.