General Electric Company

Transportation IP Holdings, LLC

General Electric Technology Gmbh

Suryarghya Chakrabarti

Nicholas M Daggett

Jing Li

Bugra Han Ertas

John McConnell Delvaux

Brian Denver Potter

Walter John Smith

James Tyson Balkcum, Iii

Drew Michael Capps

Gary W Bryant

Zachary Pebley

Charles Erklin Seeley

Daniel Edward Loringer

Narayanan Payyoor

Matthew John Malone

Changjie Sun

Abhijeet Jayshingrao Yadav

Andrew Joseph Wickersham

John Joseph Mihok

Andrew Clifford Hart

Shawn Patrick Riley

Balaraju Suresh

Markus Feigl

Abhishek Goverdhan

Claire Fridtjof Lang

Ricardo Hernandez Pandeli

Andrew Grafitti

Kevin E Turner

Youngwon Shin

Yashwanth Tummala

Amarnath Kakarla

Illya Emmanuel Arcos Perez

Ashish Rajput

Waad Hussain Subber

Letian Wang

John Mcconnell Delvaux

James Tyson Balkcum Iii

A variable pitch airfoil assembly for an engine includes a disk having an annular shape extending about an axial direction, an airfoil coupled to the disk via a platform, and at least one damping element disposed between the platform and the disk. The airfoil extends outwardly from the disk in a radial direction and is rotatable relative to the disk about a pitch axis. The at least one damping element is configured to provide vibration damping by friction between the at least one damping element, the disk, and the platform while also allowing for a pitch change of the airfoil.

Variable pitch airfoil assembly for a gas turbine engine

An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.

Rotating airfoil assembly for an aircraft engine

A variable pitch airfoil assembly for an engine includes a disk having an annular shape extending about an axial direction and an airfoil coupled to the disk via a platform. The airfoil extends outwardly from the disk in a radial direction and is rotatable relative to the disk about a pitch axis. The variable pitch airfoil assembly further includes a damping element positioned at least partially within the disk exterior of and adjacent to a perimeter of the platform so as to provide vibration damping by friction between the damping element, the platform, and the disk while also allowing for a pitch change of the airfoil.

Variable pitch airfoil assembly for an open fan rotor of an engine having a damping element

A rotating airfoil including a body and a vibration absorber located within the body. The body has a root end and a tip. The rotating airfoil has a natural frequency, and the vibration absorber has a natural frequency. The natural frequency of the vibration absorber is different than the natural frequency of the rotating airfoil.

Rotating airfoil assembly

A rotating airfoil assembly including a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis. Each rotating airfoil of the rotating airfoils includes a leading edge, a trailing edge, a suction surface between the leading edge and the trailing edge, and a pressure surface between the leading edge and the trailing edge. The suction surface and the pressure surface are positioned on opposite sides of the rotating airfoil such that, when airflows over the suction surface and the pressure surface of the rotating airfoil as the rotating airfoil rotates about the rotation axis, the rotating airfoil generates lift. At least one opening is located on one of the suction surface or the pressure surface. The at least one opening is configured to eject air or to draw air into the opening.

Rotating airfoil assembly with opening formed therein to eject or to draw air

A turbine damper may be provided that may include an elongated body sized to fit inside a turbine blade, the elongated body elongated along a radial direction of the turbine blade relative to a rotation axis of the turbine blade, and plural dampening masses coupled with the elongated body and disposed at different locations along the radial direction. The plural dampening masses may be one or more of sized to dampen different vibration modes of the turbine blade, or moveable relative to and along the elongated body in the radial direction.

Turbine damper

A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations of the component. The vibrational dampening element includes a mass. The mass includes a main body and a member extending from the main body. A casing that encapsulates the mass. A fluidic chamber defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member. A second fluidic portion is disposed between a second side of the mass and the casing. The second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.

Vibrational dampening elements

A rotor blade assembly includes a first rotor blade and a second rotor blade positioned adjacent to one another. The first rotor blade and the second rotor blade each include a platform and an airfoil extending radially outward from a root coupled to the platform to a tip. The airfoil includes a part-span shroud. The part-span shroud extends from the airfoil and is disposed between the root and the tip. The part-span shroud includes a pressure side portion extending from the pressure side surface and a suction side portion extending from the suction side surface. A damper is in contact with both the part span shroud of the first rotor blade and the part span shroud of the second rotor blade at an interference joint. The damper is movable relative to the part span shroud of both the first rotor blade and the second rotor blade.

Rotor blade damping structures

A turbine blade includes an internal vibration damping system having a plurality of unit cells. Each unit cell includes: an impacting structure; and a cavity encapsulating the impacting structure. The cavity, which includes a first hemisphere and a second hemisphere, is disposed within a substrate, which forms an outer casing of the cavity. At least one fluid is disposed in each of the first and second hemispheres between the impacting structure and the outer casing.

Distributed hybrid damping system

The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.

Blade and airfoil damping configurations

A system and method are provided for operating and maintaining a wind turbine. Accordingly, a plurality of data inputs are received. The plurality of data inputs represent a plurality of monitored attributes of a component of the wind turbine. A consolidated risk index for the component is determined using the plurality of monitored attributes, and a range of potential risk indices is forecasted. A remaining-useful-life distribution is determined based on the damage potential and an end-of-life damage threshold. The wind turbine is shut down or idled if the remaining-useful-life distribution is below a shutdown threshold.

System and method for operating a wind turbine

A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

Distributed nested cell damping system

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 blade vibration damping system impacts a pressurized damping fluid on a surface of at least one of a plurality of blades of a turbine in opposition to a vibratory movement thereof to cause damping of vibration of the blade(s) during operation of the turbine. The system includes a fluid injection nozzle in a stationary component adjacent the plurality of blades. A valve selectively admits the pressurized damping fluid to the fluid injection nozzle from a source of pressurized damping fluid, and a control system controls the valve to operate the fluid injection nozzle in response to an operational parameter exceeding a threshold during operation of the turbine. A related turbine casing and method are also provided.

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Niskayuna, NY, United States of America

Suryarghya Chakrabarti