초록 ▼

A preferred embodiment of the present invention is a gas turbine engine rotor assembly having axially spaced apart forward and aft disks circumferentially disposed about an axis. The forward disk has an aftwardly extending annular forward arm and the aft disk has a forwardly extending annular aft ar

A preferred embodiment of the present invention is a gas turbine engine rotor assembly having axially spaced apart forward and aft disks circumferentially disposed about an axis. The forward disk has an aftwardly extending annular forward arm and the aft disk has a forwardly extending annular aft arm. Forward and aft flanges are located at forward and aft ends of the forward and aft arms respectively. Forward and aft pluralities of aligned forward and aft bolt holes extending axially through the forward and aft flanges respectively. A scalloped annular ring having a plurality of circumferentially spaced apart tabs with spaces therebetween is disposed between the flanges. A plurality of ring bolt holes extend axially through the plurality of circumferentially spaced apart tabs such that corresponding ones of the ring, forward, and aft bolt holes are axially aligned. Forward and aft pluralities of apertures extend axially through the forward and aft flanges and the spaces are in fluid flow communication with corresponding forward and aft ones of the apertures. A plurality of bolts are preferably used to attach the forward and aft flanges together and each of the bolts is disposed through corresponding ones of the ring, forward and aft bolt holes.

대표청구항 ▼

[ What is claimed is:] [1.]1. A gas turbine engine turbine rotor assembly, said assembly comprising:axially spaced apart forward and aft disks having annular outer forward and aft rims attached by annular forward and aft webs to annular forward and aft bores and circumferentially disposed about an a

[ What is claimed is:] [1.]1. A gas turbine engine turbine rotor assembly, said assembly comprising:axially spaced apart forward and aft disks having annular outer forward and aft rims attached by annular forward and aft webs to annular forward and aft bores and circumferentially disposed about an axis,an annular interstage seal extending between and removably connected to said forward and aft disks by connections,an annular forward arm extending aftwardly from said forward web,an annular aft arm extending forwardly from said aft web, said arms having no fluid passage therein,forward and aft flanges removably attached to each other at forward and aft ends of said forward and aft arms respectively forming a radially outer annular interstage volume extending radially between said forward and aft flanges and said interstage seal and a radially inner annular interstage volume extending radially inwardly of said forward and aft flanges, anda means for passing cooling air between said forward and aft flanges from said inner annular interstage volume to said outer annular interstage volume. [2.]2. A gas turbine engine rotor assembly comprising:axially spaced apart forward and aft disks circumferentially disposed about an axis,said forward disk having an aftwardly extending annular forward arm,said aft disk having a forwardly extending annular aft arm,forward and aft flanges at forward and aft ends of said forward and aft arms respectively,said forward and aft flanges having respective forward and aft pluralities of aligned forward and aft bolt holes extending axially therethrough,a scalloped annular ring having a plurality of circumferentially spaced apart tabs with spaces therebetween is disposed between said forward and aft flanges,a plurality of ring bolt holes extending axially through said plurality of circumferentially spaced apart tabs such that corresponding ones of said ring, forward, and aft bolt holes are axially aligned,at least a first one of said flanges having a first plurality of apertures extending axially therethrough, andand said spaces are in fluid flow communication with corresponding ones of said apertures.