General Electric Company

Ge Infrastructure Technology, LLC

Other

Transportation IP Holdings, LLC

Siemens Power Generation, Inc.

Brian Denver Potter

Matthew Robert Piersall

John McConnell Delvaux

John Wesley Harris, Jr

Michael James Healy

Christian Michael Hansen

Robert Alan Brittingham

Zachary John Snider

Gregory Thomas Foster

Gary Charles Liotta

Suryarghya Chakrabarti

Spencer Aaron Kareff

Michael Anthony Wondrasek

Ariel Caesar Prepena Jacala

James Tyson Balkcum, Iii

Aaron Ezekiel Smith

Daniel Jason Erno

Daniel Edward Loringer

Matthew John Malone

Alfred Paul Matheny

Ian David Wilson

Andres Jose Garcia-Crespo

Stephen Paul Wassynger

Walter John Smith

Robert Frank Hoskin

Bradley Taylor Boyer

Lisa Anne Wichmann

David Randolph Spracher

Zachary James Taylor

Brad Wilson VanTassel

Bruce J Badding

Dwight Eric Davidson

Nathan Stafford Race

Michael David McDufford

Stephen Joseph Balsone

Andrew Grafitti

Ryan Zane Ziegler

Yashwanth Tummala

Michael C Potter

Letian Wang

Wondrasek Michael Anthony

Bruce John Badding

James Tyson Balkcum Iii

Spencer A Kareff

John Wesley Harris

A vibration damping system includes a vibration damping element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade between the tip end and the base end thereof, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration damping element includes a plurality of stacked plate members within the body opening. Each plate member is in surface contact with at least one adjacent plate member to cause friction that dampens vibration of the nozzle or blade. The body opening has an inner dimension, and each plate member has an outer dimension sized to frictionally engage the inner dimension of the body opening to damp vibration. Plate members may each include a central opening therein, and a fixed elongated body or cable may extend through the central openings. The damping element may alternatively include a helical metal ribbon spring.

Vibration damping system for turbine nozzle or blade using stacked plate members

A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

Nested damper pin and vibration dampening system for turbine nozzle or blade

Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.

Damper stacks for turbomachine rotor blades

Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a damping passage defined in the main body, the damping passage extending radially through the main body. The rotor blade further includes a damper stack disposed within the damping passage, the damper stack including a plurality of damper pins, each of the plurality of damper pins in contact with a neighboring damper pin.

Damping members for turbocharger assemblies, methods for providing turbocharger assemblies, and turbocharger assemblies are described herein. The damping members include bodies having shapes to fit between a recess extending into a rotor disk of a turbocharger and laterally protruding shoulders of platforms in neighboring blades of the turbocharger. The bodies dampen vibrations of the blades during rotation of the blades. The damping members may include a variety of shapes, such as a sheet, a wedge, a tapered pin, a cylindrical pin, a bent sheet, or another shape.

Underplatform damping members and methods for turbocharger assemblies

A rotor assembly includes plural blades and damping inserts. The blades include a carrier shroud and a lid shroud extending from an airfoil of the respective blade in generally opposite directions. The carrier shrouds define pockets at distal ends thereof. The damping inserts are disposed in the pockets of the carrier shrouds of the blades and free-floating within the pockets. The damping inserts are configured to dampen vibrations of the blades during rotation of the blades and the rotor disk via engaging an interior surface within the corresponding pocket of the carrier shroud and engaging a distal end of the lid shroud of the neighboring blade. A contact force applied by each damping insert on the distal end of the lid shroud of the neighboring blade is based on a rotational speed of the blades and the rotor disk.

Damping inserts and methods for shrouded turbine blades

A rotor blade for a turbomachine includes an airfoil having a leading edge, a trailing edge, a root, and a tip. The airfoil defines a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip. A first particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord.

Turbomachine rotor blade

A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.

Damper pin for a turbine blade

A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.

A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length, which is less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material, the root segment material and the turbine wheel material having a lower heat resistance and a higher thermal expansion than the tip segment material.

Turbine bucket assembly and turbine system

A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a camber line rib having a wavy profile. The wavy profile may include at least one back-and-forth 'S' shape.

Structural configurations and cooling circuits in turbine blades

A turbine blade that includes an airfoil and a radially extending chamber therein for a coolant. The turbine blade may also include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include: a camber line rib that defines a near-wall flow chamber; and traverse ribs extending between the camber line rib and one of the outer walls so to divide the near-wall flow chamber into successively stacked flow passages that each include a segment of the camber line rib. The segment of the camber line rib of one of the flow passages may have a narrowing profile that includes a profile that narrows from opposing ends toward a neck disposed therebetween.

Interior cooling circuits in turbine blades

A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine.

Turbine interstage seal system

A compressor fairing segment includes a body having an upstream surface, a downstream surface, and opposing side surfaces between the upstream and downstream surfaces. A first detent on the upstream surface is shaped to conform to a first complementary fitting inside a compressor. A second detent on the downstream surface shaped to conform to a second complementary fitting inside the compressor.

Compressor fairing segment

Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection, the projection comprising a first surface and a second surface formed on the projection and configured to engage the inner surfaces, the first and second surfaces generally perpendicular to radial.

Locking spacer assembly

Growing community of inventors

Greer, SC, United States of America

Brian Denver Potter