General Electric Company

John Herbert Dimmick

Raymond Joseph Lecuyer

Matthew Ryan Ferslew

Andrew Clifford Hart

Gang Liu

Norman K Austin

Gary Charles Liotta

Roger C Walker

Daniel David Snook

Eric Richard Bonini

Ariel Caesar Prepena Jacala

Nicholas Simon Graham

Richard Francis Gutta

Srinivas Ravi

Raymond Andrew Vincent

Matthew Paul Forcier

Robert Craig Akin

Jonathan Michael Webster

David Arthur Butz

Ashok Kumar Haveri Murigeppa

Patrick Shawn Reilly

John Robert Sech

Tushar Sharadchandra Desai

Charles Alexander Smith

Bruce Carlisle McClintick

Chunlian Han

Kiran Sreeram

Rachel Jane Obermeyer

Katherine Courtlyn MacManus

Shaft assemblies, turbomachines, and methods of servicing a turbomachine are provided. A shaft assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending face and a first radially extending face. A second shaft coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending face and a second radially extending face. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a main body positioned between and in contact with the first axially extending face and the second axially extending face. A first arm extends radially outward from the main body, and a second arm extends radially inward from the main body.

Patch rings and methods of use

A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Rotor wheel and impeller inserts

A compressor blade mounting arrangement includes a compressor blade having an airfoil, a base attachment and a platform disposed between the airfoil and the base attachment. The base attachment includes a first root portion extending radially inwardly from the platform and a second root portion extending radially inwardly from the platform, the first root portion and the second root portion defining a hollow portion therebetween. The base attachment also includes a compression plate disposed within the hollow portion and in fitted engagement with the first root portion and the second root portion. The base portion further includes at least one tab protruding from at least one of the first root portion and the second root portion. The compressor blade mounting arrangement also includes a wheel including a channel extending from a base wall to a rim of the wheel, the channel having a varying opening width.

Compressor blade mounting arrangement

Load couplings, power trains, and methods for adjusting torsional natural frequencies of power trains are provided. In one embodiment, a load coupling includes a first flange, a second flange, and a shaft extending between the first flange and the second flange. The load coupling further includes an annular ring extending radially outward from one of the first flange, the second flange, or the shaft, the annular ring including a plurality of bore holes defined therein, each of the plurality of bore holes including a first opening. The load coupling further includes a first cap connected within one of the plurality of bore holes proximate the first opening, the first cap deformable such that an interference fit is created with the one of the plurality of bore holes.

Load coupling and method for adjusting torsional natural frequency of power train

A system includes a cover segment configured to mount in first and second grooves circumferentially along a blade mounting region of a turbine rotor. The cover segment includes a cover body and at least one fastener. The cover body includes first and second lips extending along first and second circumferential portions of the cover body at an offset from one another. The first lip is configured to mount circumferentially along the first groove and the second lip is configured to mount circumferentially along the second groove. The at least one fastener is configured to retain the cover body to the turbine rotor or at least one blade mounted in the blade mounting region.

System and method for covering a blade mounting region of turbine blades

The present application provides a self locking nut and bolt assembly for a stack of rotating wheels. The self locking nut and bolt assembly may include a tie bolt extending through the stack of rotating wheels, a locking nut positioned on a first end of the tie bolt, and a locking washer positioned on the one end of the tie bolt within the locking nut.

Self locking nut and bolt assembly

Systems and devices adapted to reduce disturbances and windage effects in a turbine during operation are disclosed. In one embodiment, a cap includes: a body portion having a shape complementary to an aperture in a turbine component, the body portion including an external surface which substantially covers the aperture; and a cap groove formed in a circumferential surface of the body portion, the cap groove configured to substantially align with a component groove formed in the aperture.

Turbine aperture cap system

A bolted flange assembly for securing rotating components in a gas turbine. The bolted flange assembly includes two rotating wheels, each wheel having at least one arm extending towards a spacer positioned partially between the two rotating wheels, wherein each arm has a flange surface facing the spacer. Either each flange surface or a surface of the spacer is conical, i.e., non-perpendicular to a centerline of the gas turbine, such that in an unconstrained state, a heel end of each flange surface is closer to the spacer than a toe end of each flange surface; and a bolt extending through the arm of each rotating wheel and the spacer.

Gas turbine conical flange bolted joint

A system includes a cover segment set configured to mount in first and second grooves circumferentially along a blade mounting region of a turbine rotor. The cover segment set includes a seal segment and a cover segment. The seal segment has a seal body with a lock feature, wherein the seal segment is configured to mount circumferentially along the second groove. The cover segment includes first and second lips extending along first and second circumferential portions of a cover body. The first and second lips are at an offset from one another. The first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove adjacent the seal segment, and the second lip includes a mating lock feature configured to couple with the lock feature of the seal body.

A system includes a rotor assembly with a first rotor component having a first set of bushing receptacles and a first set of bolt holes arranged about a first rotational axis of the first rotor component. The rotor assembly also includes a second rotor component having a second set of bushing receptacles and a second set of bolt holes arranged about a second rotational axis of the second rotor component. The rotor assembly includes a first set of bushings disposed in the first and second sets of bushing receptacles in a first installed configuration, wherein the first installed configuration of the first set of bushings is configured to align the first and second rotational axes with one another, and the first installed configuration of the first set of bushings is configured to bear at least a first portion of a torque during rotation of the rotor assembly. The rotor assembly also includes a first set of bolts extending through the first and second sets of bolt holes to retain the first rotor, the second rotor, and the first set of bushings in the rotor assembly.

System and method for coupling rotor components

A locking device arrangement for a rotating bladed stage is provided and includes a wheel formed to define a substantially circumferential slot and three slot sections, one of the slot sections including one radial slot and two lock slots to permit blade and blade lock installation along the circumferential slot, respectively, the other slot sections including a lock slot to permit blade lock installation along the circumferential slot, and the three slot sections being separated from one another with angular offsets such that the wheel is mass balanced substantially evenly about a desired center of rotation with the blade locks installed and to reduce accumulation of flowpath gaps.

Locking device arrangement for a rotating bladed stage

An attenuation bracket is provided and includes an annular body having an annular attenuation arm defining first through-holes and an annular base defining second through-holes. A cross-section of the attenuation arm includes a flange, a connector opposite the flange and a curvilinear section extending between the flange and the connector. A cross-section of the base includes a first side corresponding with the flange and a second side opposite the first side and corresponding with the connector. The second side is connectable with the connector such that each of the first through-holes is defined in positional alignment with a corresponding one of the second through-holes.

Impeller tube assembly

Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

Growing community of inventors

Greenville, SC, United States of America

John Herbert Dimmick