General Electric Company

Jerome A Juenger

Ian Francis Prentice

Peter Wayte

Frederick C Herzner

Stephen C Peterson

Fredrick C Herzner

A blade retaining sub-assembly for use in a gas turbine engine which includes at least one radially extending blade mounted in a dovetail slot of a rotatable annular disk. The sub-assembly prevents the blade from migrating from the dovetail slot in an axially forward direction and includes a pair of circumferentially spaced lugs extending from a pair of adjacent disk posts such that each of the lugs are disposed axially forward of, and circumferentially adjacent to, respective ones of the lateral surfaces of the blade dovetail. The sub-assembly further includes a retainer plate disposed in each of the lugs and the plate restrained. The plate includes a body section and a contoured platform which is disposed in confronting relationship with the blade dovetail, wherein the contoured platform includes a periphery which is predeterminedly shaped and positioned so as to enhance a load carrying capability of the plate and lugs. The plate is restrained by a bracket attached to a spacer having an aft portion disposed in the dovetail slot inward of the blade, wherein the bracket includes a slotted mount hole which enhances a capability of the plate to flex about an axis which is generally parallel to a radially extending centerline passing through the hole.

Gas turbine engine blade retainer sub-assembly

A metallic reinforced shim is attached to the dovetail of turbine or compressor blades. The shim reduces frictionally induced wear damage to the rotor. In one form, a single ply shim reinforced with a metallic doubler has an anti-fretting layer deposited on the shim face contacting the dovetail slot pressure face, and a doubler layer fastened to the anti-fretting layer in the non-contacting regions to prevent slippage of the shim on the blade. In another form, a multi-layer shim has two layers interposed between the blade dovetail and the disk dovetail slot, with the layers treated so that they do not readily slip relative to the titanium pieces, but do slip relative to each other. The shim is also reinforced with a metallic doubler. Fretting is confined to the consumable shim, and therefore the disk dovetail slot and the mating blade dovetails are not subject to surface degradation with corresponding reduction in fatigue capability.

Turbine blade wear protection system with multilayer shim

To eliminate stress peaking at the bearing surface interface of the blade and disk slot dovetails in a gas turbine engine, the slot dovetail in undercut to remove disk material from contact with the blade dovetail radially inner edges where surface stress peaking would otherwise occur. The undercut contour radially inward of the blade dovetail is determined by analysis based on each engine design such as to achieve a substantially uniform distribution of surfaces stress along the dovetail slot fillet radius.

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Cincinnati, OH, United States of America

Jerome A Juenger