General Electric Company

Raymond Edward Chupp

Farshad Ghasripoor

Mahmut Faruk Aksit

Osman Saim Dinc

Don Mark Lipkin

Brian Peter Arness

Warren Arthur Nelson

Nitin Bhate

Paul Thomas Marks

Jeffrey Reid Thyssen

Tara Easter McGovern

Dalero Winston Berkeley

Chek Beng Ng

Norman Arnold Turnquist

Canan Uslu Hardwicke

Ronald Ralph Cairo

Yuk-Chiu Lau

Kevin Leon Bruce

George Ernest Reluzco

Murtuza Lokhandwalla

Robert Anthony Fusaro, Jr

Ming Zhou

Alberto Jose Negroni

Donald Joseph Baldwin

Kenneth Lorenzo Parks

Hui Kuang

Gayle Hobbs Goetze

John Augustus Halbohm

A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

Pattern for the surface of a turbine shroud

An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

A compliant seal for use between rotating blades and a static shroud surrounding the rotating blades in a steam or gas turbine is disclosed. The seal includes a tip surface, substantially resistant to wear due to rubbing by the tip of the rotating blades, and an elastic biasing member, comprising a biasing element. The wear-resistant surface is thus biased against the tips of the rotating blades to seal a gas path between the rotating blades and the static shroud.

Sealing device and method for turbomachinery

A seal having a first seal mechanism adapted for insertion between a first structure and a second structure, wherein the first structure is in communication with a first medium and the second structure is in communication with a second medium. The seal also includes a second seal mechanism, which is pressuringly biasable against the first seal mechanism and against the second structure by the second medium. In certain embodiments, a system has a first structure in communication with a first medium and a second structure houses a seal assembly between the first and second structures. The seal assembly includes an interface seal disposed against the first structure and a flexible seal pressuringly biased against the second structure and the interface seal by a second medium.

Hybrid seal and system and method incorporating the same

Process of brazing an alumina-coated honeycomb and fiber metal material to a substrate, in which a mask material is applied to a portion of the honeycomb and fiber metal prior to deposition of the AlO, and the mask material is removed after deposition and prior to brazing to the substrate.

Brazing of alumina coated honeycomb and fiber metal

Method of producing a profiled abradable coating on a substrate in which an abradable ceramic coating composition is applied to a substrate using direct-write technology, or plasma sprayed onto the substrate through a mask or by use of a narrow foot-print plasma gun. These methods of producing abradable coatings are performed in the absence of a grid.

High temperature abradable coatings

Oxidation resistant sealant system comprising a honeycomb component coated with an aluminum oxide layer.

Aluminum oxide coated honeycomb for S2S and S3S sealing system with extended oxidation life

The present invention provides, in one embodiment, an annular turbine seal for disposition in a turbine between a rotatable component having an axis of rotation and a turbine housing about the same axis of rotation. The turbine seal has a plurality of arcuate seal carrier segments that have an abradable portion secured to the seal carrier segments. In addition, at least one spring is disposed on the seal carrier segment to exert a force and maintain the seal carrier segment adjacent to the rotatable component.

Spring-backed abradable seal for turbomachinery

The positions of brush seal segments are positively adjusted relative to a housing carrying the brush seal segments and the opposing sealing component by employing members formed of thermally responsive material. The members are heated by heating elements receiving controlled power. By increasing or decreasing the power provided to the heating elements, the members are expanded or contracted to move the brush seal segments toward or away from the opposing sealing component.

Brush seal with positive adjustable clearance control

A brush seal assembly is radially and axially repositionable relative to stationary and rotating components. Shim packs whose thickness can be reduced by peeling adhesively attached foil layers from the shim packs are used to provide both axial and radial repositioning. In another form, a plurality of set screws may be threaded into a mounting member for the brush seal assembly to controllably space the brush seal from the rotating component. In a further form, an eccentric cam is rotated to reposition the brush seal assembly radially inwardly or outwardly with shim packs being used to reposition the brush seal in an axial direction.

Repositionable brush seal for turbomachinery

A rotary machine includes a rotatable rotor, blades radially mounted on and spaced apart about the rotor, a stationary casing disposed about and radially outward from the rotor and blades defining an annular gap between the casing and tips of the blades, and a flexible abradable seal assembly attached on the casing and disposed within the annular gap such that during differential growth of the rotor and blades relative to the casing the seal assembly flexes and abrades in response to contact by the blade tips and thereby clearance between the casing and blade tips is controlled as to avoid contact by the moving blade tips with the casing.

Growing community of inventors

Glenville, NY, United States of America

Raymond Edward Chupp