Patent ID: 7048496

Claim:
A rotor system for a gas turbine engine, comprising: an outer rotor disposed about an axis, said outer rotor comprising an annular outer spool which includes at least one ring portion of increased thickness with respect to the remainder of said outer spool, said ring portion being attached to a relatively thinner, axially extending arm portion; a plurality of outer turbine blades which are attached to said ring portion of said outer spool and extend radially inwardly into a working gas flowpath of said engine, a casing surrounding said outer rotor and defining an annular cavity between said casing and said outer rotor, said casing having at least one inlet port formed therethrough for admitting a flow of cooling air to said annular cavity; a forward seal disposed at a forward end of said annular cavity; an aft seal disposed at an aft end of said annular cavity; and means for directing said flow of cooling air from said annular cavity to said ring portion of said outer spool, wherein at least one open inlet hole is formed through said arm portion of said outer spool such that said outer turbine blades are in fluid communication with said annular cavity.