Patent ID: 9091180
Filing Date: 2015-07-28
Classification: F01D,F05D,Y10T

Abstract:
1. An airfoil assembly for an axial flow gas turbine engine, the gas turbine engine including an axially directed flow path defining a passage for a working fluid and a source of pressurized fluid, the airfoil assembly including: an endwall having an upstream edge and a downstream edge axially spaced from the upstream edge; an airfoil extending from the endwall into the flow path, the airfoil having a leading edge and a trailing edge, and a pressure side and a suction side extending between the leading and trailing edges; the endwall is defined on a platform structure having a front surface adjacent to the upstream edge, the front surface extending parallel to a radial direction, along a direction of a thickness of the platform structure; at least one fluid injection passage extending through the platform structure in a direction from the upstream edge toward the downstream edge, and each fluid injection passage having an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source; each fluid injection passage extending through the platform structure at a shallow angle relative to a plane of the endwall wherein the extension of each fluid injection passage through the platform structure defines a passage axis passing through the front surface and the endwall, wherein the respective outlet opening of each fluid injection passage is located axially between the upstream edge of the endwall and the leading edge of the airfoil, and wherein the respective passage axis along which each fluid injection passage extends through the platform structure is oriented at an angle relative to the plane of the endwall that is in a range from about 10 to 20 degrees.