General Electric Company

James Louis Lawen, Jr

Osman Saim Dinc

Norman Arnold Turnquist

Robert Harold Cromer

Abdul-Azeez Mohammed-Fakir

George Ernest Reluzco

Ziqiang Hu

Kenneth Roger Conway

Ming Zhou

Saim Dinc

Onika Misasha Kerber

Henry Joe Wiersma

Salvadore Calabrese

One method empirically determines a stiffness value for each of two or more different subsets of the bristles of a brush seal, then calculates a variation in stiffness, and then identifies the brush seal as defective if the calculated variation in stiffness exceeds a predetermined stiffness variation criteria. One apparatus includes a load transducer having a contact head sized to contact less than twenty percent of the bristles, a displacement transducer which measures the displacement of the free ends of the contacted bristles, and a clamp for securing the brush seal and presenting the bristles for contact.

Method and apparatus for determining if brush seals are defective

In a gas turbine combustion system, liner stops mount a combustion liner within a flow sleeve. The liner stops are mounted on the outer surface of the combustion liner and the inner surface of the flow sleeve in a symmentrical array of liner stops. The liner stops have inclined contacting surfaces that support the liner within the sleeve, and provide rubbing contact between the two. These inclined surfaces are on a post of a male liner stop that fits into a channel of a female liner stop.

Combustion liner for gas turbine having liner stops

A fuel nozzle centering assembly and method employ bodies of a substantially wearable and sacrificial material mounted to an outer periphery of a tip of a burner fuel nozzle for a gas turbine combustor. The tip of the fuel nozzle extends through an opening of an annular collar attached to a liner of a main combustion chamber of the gas turbine combustor and an outer periphery of the tip is disposed radially inwardly from the annular collar such that the bodies of sacrificial material are disposed between the outer periphery of the fuel nozzle tip and the annular collar of the liner and space the fuel nozzle tip from the liner collar. The bodies of material prevent the fuel nozzle tip from contacting the liner collar during assembling of the fuel nozzle into the liner. The bodies wear away substantially upon initial operation of the combustor such that the bodies will reduce contact with the liner collar during further operation of the combustor and the fuel nozzle tip will remain spaced from and out of contact with the liner collar during operation of the combustor.

Fuel nozzle centering device and method for gas turbine combustors

A seal assembly and a rotary machine, such as a steam turbine, containing the seal assembly. A casing circumferentially surrounds a rotor and includes a circumferential channel open to the rotor. Seal segments are circumferentially arrayed in the channel and are movable between radially inward and outward positions. Circumferentially adjacent seal segments have circumferentially opposing surface grooves. A resilient and imperforate member is engaged in the grooves of circumferentially-adjacent seal segments circumferentially urging apart such segments and providing sealing between such segments.

Seal assembly and rotary machine containing such seal assembly

Growing community of inventors

White, GA, United States of America

James Louis Lawen, Jr