COMPRESSION SECTION FOR AN AXIAL FLOW ROTARY MACHINE

摘要

COMPRESSION SECTION FOR AN AXIAL FLOW ROTARY MACHINE A compression section of a gas turbine engine having an annular flow path is disclosed. Various construction details which increase the efficiency of an array of rotor blades in the compression section are developed. The annular flow path is contoured to cause the streamlines of the flow path to follow a pattern of varying radial curvature. In one embodiment, a conical surface extending between the base of each airfoil on the inner wall causes a flow path contraction and a cylindrical surface on the outer wall facing the tip of each airfoil enables close clearances.