Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or...
Reexamination Certificate
1999-09-07
2001-09-04
Ryznic, John E. (Department: 3745)
Fluid reaction surfaces (i.e., impellers)
Rotor having flow confining or deflecting web, shroud or...
C415S115000
Reexamination Certificate
active
06283712
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to aircraft gas turbine engine turbine rotors and disks and, more particularly, to bolted flanges of adjacent turbine rotor disks.
2. Discussion of the Background Art
Gas turbine engines frequently multi-stage turbine rotors having adjacent turbine disks bolted together to form the turbine rotor. In the high pressure turbine rotors cooling air must be supplied to the roots of turbine blades through rims of the turbine disks. The adjacent disks have conical arms with flanges as their ends and the flanges are typically bolted together forming a conical wall assembly across which cooling air must be flowed to reach the rims and turbine blade roots.
Typically, holes have been placed in the arms of disks to allow cooling air to flow across the arms. It is desirable to avoid putting these holes through an arm of a disk, since these holes weaken the disk and limit its life.
SUMMARY OF THE INVENTION
A preferred embodiment of the present invention is a gas turbine engine rotor assembly having axially spaced apart forward and aft disks circumferentiaily 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. Preferably, each aperture of the pluralities of apertures is circumferentially located between each two of the forward and aft bolt holes. 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. At least one of the forward and aft bolt holes are different from the apertures such that the bolts cannot be disposed through the apertures.
A more specific embodiment of the gas turbine engine turbine rotor assembly further includes an annular interstage seal extending between the forward and aft disks. The forward and aft disks include annular outer forward and aft disk rims attached by annular forward and aft disk webs to annular forward and aft disk bores, respectively. The annular forward arm extends aftwardly from the forward web and an annular aft arm extends forwardly from the aft web. The forward and aft flanges are removably attached to each other at forward and aft ends of the forward and aft arms respectively forming a radially outer annular interstage volume extending radially between the forward and aft flanges and the interstage seal and a radially inner annular interstage volume extending radially inwardly of the forward and aft flanges. The invention provides apparatus for passing cooling air between the forward and aft flanges from the inner annular interstage volume to the outer annular interstage volume. A plurality of coolable turbine blades are mounted around a periphery of the aft rim. Each blade has a root mounted in the aft rim and a coolable airfoil extending radially outwardly from a platform attached to the root. Cooling passages are used for flowing cooling air from the outer annular interstage volume to the coolable airfoils. The cooling passages include cooling air passageways are formed in the aft rim leading from the outer annular interstage volume to the roots of the coolable blades and the airfoils.
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Albrecht, Jr. Richard W.
Bolt William Z.
Dziech Aaron M.
Reisenauer Daniel E.
Ward Steven D.
General Electric Company
Herkamp Nathan D.
Hess Andrew C.
Ryznic John E.
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