Patent ID: 7244104
Filing Date: 2007-07-17
Classification: F01D,F05D

Abstract:
1. A gas turbine engine including a forward stator assembly and a rotor assembly, the rotor assembly drivingly mounted to an engine shaft having an axis, the rotor assembly having a plurality of circumferentially distributed blades that extend radially outwardly into a working fluid flowpath, a leakage path leading to the working fluid flowpath being defined between the stator assembly and the rotor assembly, and an array of deflectors exposed to the flow of leakage fluid and defining a number of discrete inter-deflector passages through which the leakage fluid flows before being discharged into the working fluid flowpath, each of said deflectors having a leading end pointing into the oncoming flow of leakage fluid and a concave surface redirecting the leakage fluid from a first direction to a second direction substantially tangential to a direction of the working fluid, wherein each of said blades has an airfoil extending from a first side of a platform, and wherein a transversal row of side-by-side grooves is defined in a front end portion of the platform, each pair of adjacent grooves being spaced by a land, the lands forming said defectors.