초록 ▼

A turbine or compressor disk assembly comprises a plurality of blades attached to a central hub by means of the blade root of each blade engaging a corresponding slot in the hub. According to the principles of the present invention, a turbine or compressor disk assembly includes one or more locally

A turbine or compressor disk assembly comprises a plurality of blades attached to a central hub by means of the blade root of each blade engaging a corresponding slot in the hub. According to the principles of the present invention, a turbine or compressor disk assembly includes one or more locally bulging regions extending axially away from the surface of the disk in the vicinity of the bottom contact plane of the disk attachment firtree. The locally bulging regions reduce the peak Macke stress in the disk bottom fillet and blade attachment root. In an illustrative embodiment, two locally bulging regions are incorporated into the disk and the corresponding blades, one of which extends forward from the leading edge of the disk and the other of which extends rearward from the trailing edge of the disk. The rearward locally bulging region has an exaggerated extension which allows the stress reduction ring to form an aft flow discourager as well as functioning to reduce peak stress.

대표청구항 ▼

[ What is claimed is:] [1.] A gas turbine engine comprising:a turbine disk comprising a hub having an axial bore, a web extending radially from said hub and terminating in a rim section extending radially outward from said web, said rim section including first and second radial faces defining a firs

[ What is claimed is:] [1.] A gas turbine engine comprising:a turbine disk comprising a hub having an axial bore, a web extending radially from said hub and terminating in a rim section extending radially outward from said web, said rim section including first and second radial faces defining a first axial thickness;said rim section including a plurality of slots passing substantially axially from said first radial face to said second radial face defining a live rim radius of said disk, said slots each defining at least one disk fillet adapted to engage a corresponding blade lobe along a contact zone centered about a contact plane, for retaining a turbine blade to said disk;said rim section further including a first bulging region integral to and extending axially outward from said first radial face, said first bulging region having a maximum axial excursion proximal said contact plane; anda first inward taper, said first inward taper comprising a region tapering axially inward with decreasing radial dimension from said maximum axial excursion, said first inward taper beginning at a point radially outward of said live rim radius.