Patent ID: 8708652
Filing Date: 2014-04-29
Classification: F01D

Abstract:
1. A turbine rotor for a gas turbine engine comprising: a rotor disk having a central web which has an outer face spaced further downstream of a central axis than an outer face of a radially inner portion of the rotor disk; a cover plate secured to the rotor disk, said cover plate having an enclosed chamber for moving air from a radially inner portion towards a radially outer portion and into cooling air passages to be associated with a turbine blade, said enclosed chamber being at least partially aligned with the central web, and said radially inner portion of said cover plate having ribs extending toward the radially inner portion of said rotor disk; and said enclosed chamber defined by an upstream wall facing away from said rotor disk, and a downstream wall facing a surface of said rotor disk, said downstream wall ending radially outwardly of said radially inner portion of said cover plate, wherein an abutment on said rotor disk serves to direct air into said enclosed chamber, and further provides a positioning stop for said cover plate.