General Electric Company

Momentive Performance Materials Gmbh

Bruce J Badding

Andrew Joseph Colletti

Bryan Edward Williams

John Wesley Harris, Jr

Mark Philip D'Evelyn

Anthony John Dean

David Martin Johnson

Herbert Chidsey Roberts

Seyed Gholamali Saddoughi

Adam Rasheed

Glenn Curtis Taxacher

Brian Denver Potter

Anurag Gupta

Keith Cletus Belsom

Robert Arthur Giddings

Matthew Patrick Boespflug

George Hanna Ghanime

David Randolph Spracher

Zachary James Taylor

Grover Andrew Bennett, Jr

Larry Qiang Zeng

Linda Jean Farral

Govindarajan Rengarajan

Subhrajit Dey

Philippe Giguere

Mullahalli Venkataramaniah Srinivas

Christopher Farral

Ryan Zane Ziegler

Peter J R&ouml;hl

Julia A Wagener

A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.

Turbomachine component with surface repair

A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.

Turbine component assembly

Embodiments of the present disclosure provide surface treatment tools, methodologies, and/or repaired turbomachine components. A surface treatment tool according to the present disclosure can include a lathe assembly having a lathe chuck for receiving a component thereon, wherein the lathe chuck rotates the component about a first axis of rotation, and wherein the component includes an exposed axial target surface; and a sander or burnishing tool coupled to the lathe assembly and including a sanding or burnishing surface thereon, coupled to a drive system, wherein the sanding or burnishing surface rotates about a second axis of rotation substantially non-parallel with the first axis of rotation, such that the sanding or burnishing surface selectively contacts the target surface of the component to yield a polished target surface.

Surface treatment of turbomachinery

A retention device for maintaining a first rotary machine component axially loaded onto a second rotary machine component in a fixed axial position includes a lock block sized and configured to move between first and second aligned recesses in the first and second rotary machine components. The aligned recesses are shaped to prevent rotation of the lock block, and the lock block has a threaded bore extending therethrough. An actuator is threadably mounted in the bore, such that rotation of the actuator will, in use, move the lock block from the first aligned recess at least partially into the second aligned recess.

Turbine rotor rim seal axial retention assembly

Embodiments of the present disclosure provide surface treatment tools, methodologies, and/or treated turbomachine components. A surface treatment tool according to the present disclosure can include a lathe assembly having a lathe chuck for receiving a component thereon, wherein the lathe chuck rotates the component about a first axis of rotation, and wherein the component includes an exposed axial target surface; and a sander or burnishing tool coupled to the lathe assembly and including a sanding or burnishing surface thereon, coupled to a drive system, wherein the sanding or burnishing surface is oriented along a second axis substantially non-parallel with the first axis of rotation, such that the sanding or burnishing surface selectively contacts the target surface of the component to yield a polished target surface.

The present application provides a near flow path seal for a gas turbine. The near flow path seal includes a base, a pair of arms extending from the base, and a curved indentation positioned between the pair of arms.

Near flow path seal with axially flexible arms

A system for damping combustor nozzle vibrations includes an end cover and a combustion chamber downstream from the end cover. First and second sets of nozzles extend axially between the end cover and the combustion chamber. The second set of nozzles is adjacent to the first set of nozzles. The system includes means for damping vibrations between the nozzles with a gap between the means for damping vibrations. A method for damping combustor nozzle vibrations includes flowing a working fluid through first and second sets of nozzles, wherein the first set of nozzles includes a damping member attached to and circumferentially surrounding at least a portion of the first set of nozzles, and contacting at least one nozzle in the second set of nozzles with the damping member on at least one nozzle in the first set of nozzles.

System and method for damping combustor nozzle vibrations

A system for deicing a wind turbine blade includes an electrically powered active plasma actuator applied to a desired portion of a wind turbine blade. The activated plasma actuator energizes the air in the vicinity of the plasma actuator to increase the surface temperature of the wind turbine blade in the vicinity of the plasma actuator sufficiently to reduce or eliminate the collection of ice on a desired portion of the wind turbine blade.

System and method of deicing and prevention or delay of flow separation over wind turbine blades

An aircraft engine is provided with at least one pulse detonation device, and the operational frequency of the pulse detonation device is varied over an operational range of frequencies around a mean frequency value. The pulse detonation device can be positioned upstream, downstream or adjacent to a turbine section of the engine. An additional embodiment of the present invention is an aircraft engine provided with more than one pulse detonation device, and the operational frequency of one, or more, of the pulse detonation devices is varied over an operational range of frequencies around a mean frequency value.

Pulse detonation firing detuning and frequency modulated firing

A heater that may include an outer housing and an inner tube is provided. The inner tube is in a coaxial relation to and within the outer housing. An inward facing surface of the inner tube defines a volume sufficient to receive a reaction capsule, and the outward facing surface is radially spaced from an inward facing surface of the outer housing sufficient to define a gap. A filler material is disposed within the gap. The filler material responds to pressure such that the filler volume is reduced by less than 5 volume percent at greater than 500 MPa pressure and at greater than 500&#xb0; C. temperature. One or more heating elements are disposed in the gap. The heating elements are in thermal communication with the inner tube.

Heater, apparatus, and associated method

A system and method for analyzing a baseline geometry and, optionally, a modified geometry. The method can include generating a numerical representation of a baseline geometry having baseline elements identified with first identifiers or element identifiers, and then assigning second identifiers or analyzer identifiers to the elements. A selected characteristic of the geometry, such as structural loading, is analyzed with reference to the second or analyzer identifiers. At least one of the elements of the geometry can then be altered in a manner that at least partially automatically adjusts the surrounding geometry, and the same first identifier or element identifier is associated with the altered element as was associated with the baseline, unaltered element. The altered geometry can be analyzed with respect to a third identifier (or another analyzer identifier) and a correspondence between the identifiers, the baseline element, and the altered element can be established and maintained. Accordingly, the boundary conditions and/or the mesh applied to the baseline geometry can be automatically applied to the altered geometry by referring to the first or element identifiers. Therefore, the time and effort required to analyze the altered geometry can be reduced when compared to the effort typically required by conventional methods.

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Greenville, SC, United States of America

Bruce J Badding