General Electric Company

Steven Mark Ballman

Nicholas Joseph Kray

Ravindra Shankar Ganiger

Brian Michael Davis

Andrew J Lammas

David Edward Bulman

David Lawrence Bedel

Mark Joseph Mielke

James Edwin Rhoda

Nageswar Rao Ganji

Arvind Namadevan

Daniel Edward Wines

Albert E McDaniel

Dharmaraj Pachaiappan

James Edward Gutknecht

Jeffrey D Carnes

Craig Patrick Burns

Charles Eric Lavender

Paul Michael Smith

Daniel G Suffoletta

Sean Patrick McGowan

Lawrence J Egan

Richard P Zylka

Daniel Gerard Suffoletta

Richard Patrick Zylka

A lock lug for inhibiting movement of a plurality of rotor blades includes a body and an engagement mechanism. The body is sized and configured to be received within the rim slot of the rotor disk and defines a dovetail receiving aperture. The engagement mechanism extends from the body and has a retracted configuration configured to allow entry and exit of a dovetail of at least one or more of the plurality of rotor blades into and out of the dovetail receiving aperture and an extended configuration configured to block the dovetail from entering the dovetail receiving aperture.

Methods and apparatuses for blade locking

A gas turbine engine defining a radial direction is provided. The gas turbine engine includes a tie shaft; a compressor section including a last rotor stage, the compressor section assembled to a first portion of the tie shaft; a separable shaft disposed between the compressor section and the tie shaft, the separable shaft having a radial outward portion and a radial inward portion, the radial outward portion of the separable shaft in contact with a portion of the last rotor stage at an interface; and a seal assembly operable with a portion of the separable shaft proximate the radial inward portion.

Gas turbine engine with separable shaft and seal assembly

A method of assembling a gas turbine engine that includes providing a rotor assembly including a rotor shaft, an air duct, and a rotor disk that includes a mounting arm, wherein the mounting arm extends radially inward from the rotor disk towards the rotor shaft and coupling a rotor impeller assembly to the mounting arm, wherein the rotor impeller assembly includes a carrier and a plurality of bleed tubes that each extend outwardly from the carrier and are configured to receive bleed air.

Methods and apparatus for operating gas turbine engines

A gas turbine engine rotor assembly including a rotor having a radially outer rim with an outer surface shaped to reduce circumferential rim stress concentration between each blade and the rim. Additionally, the shape of the outer surface directs air flow away from an interface between a blade and the rim to reduce aerodynamic performance losses between the rim and blades. In an exemplary embodiment, the outer surface of the rim has a concave shape between adjacent blades with apexes located at interfaces between the blades and the rim.

Reduced-stress compressor blisk flowpath

A blisk includes a disk having a rim from which extends a row of blades. The rim includes axially opposite overhangs one of which includes an arcuate balance land disposed eccentrically to the centerline axis of the disk for balancing the blisk.

Eccentric balanced blisk

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West Chester, OH, United States of America

Steven Mark Ballman