Patent ID: 8961132
Filing Date: 2015-02-24
Classification: F01D

Abstract:
1. A rotor for a gas turbine engine comprising: a rotor disk defined along an axis of rotation, the rotor disc including a rotor outer peripheral surface; a plurality of blades which extend from the rotor disk, wherein the blades are supported on platforms that have a blade inner surface that faces the rotor outer peripheral surface; at least one spacer positioned adjacent the plurality of blades to define a flow passage between the rotor disk and the blades and spacer, wherein the spacers include a spacer outer peripheral surface and a spacer inner peripheral surface that faces the rotor outer peripheral surface, and wherein the flow passage is defined between the rotor outer peripheral surface and the blade and spacer inner surfaces; and a plurality of inlets formed within the at least one spacer to pump air into the flow passage, wherein the inlets extend through the at least one spacer from at least one of the spacer outer and inner peripheral surfaces to an end face of the at least one spacer such that air flows in a generally axial direction in the flow passage from the at least one spacer toward the rotor disk.