General Electric Company

Peter W Mueller

Joseph T Stevenson

Christopher Charles Glynn

Thomas G Wakeman

Edward Charles Vickers

George Eric Moertle

Dewey D Dunkman

Clifford Stephen Creevy

Stephen Eugene Melton

Michael Todd Summers

Elbert Stonom

Scott Brensike

Apostolos Pavlos Karafillis

Alfred Albert Mancini

Melvin Bobo

Daniel Edward Wines

Sang Yeng Park

Robert E Allen

John Dawson

Alan John Charlton

Thomas F Berry

John Robert Ramsey

Josef Panovsky

Larry R Samons

Thomas F McClure

A thrust bearing support assembly includes a first substantially trapezoidally-shaped side, and a second substantially rectangularly-shaped side coupled to the first side. The thrust bearing support assembly also includes a third substantially trapezoidally-shaped side coupled to the second side, and a fourth substantially rectangularly-shaped side coupled to the first and third sides.

Thrust bearing support assembly for a gas turbine engine

A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline to facilitate minimizing distortion of the core gas turbine engine casing, and supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground.

Gas turbine engine assembly and method of assembling same

A fuel nozzle for a gas turbine engine includes a fuel tube enclosed by a housing. The fuel tube and housing are connected by a movable joint including a tubular seat formed on the housing and a boss formed on the fuel tube so as to be disposed within the tubular seat. The boss includes a contact surface that is in sliding engagement with the tubular seat and is rotatable about an axis that is perpendicular to the seat's longitudinal axis. The fuel nozzle further includes a fixed joint that connects the housing to the same section of the fuel tube as the movable joint.

Thermally free fuel nozzle

A bearing housing includes inner and outer shells through which a rotor shaft may extend. A service tube is fixedly joined to the inner shell and extends through a service aperture in the outer shell. A flexible coupling sealingly joins the service tube to the outer shell at the service aperture for permitting differential thermal movement between the inner and outer shells at the service tube.

Flexibly coupled dual shell bearing housing

A fuel nozzle including a nozzle stem having an annular overhang and a heat shield secured to the overhang is described. More specifically, and in one embodiment, the nozzle stem includes an upstream end and a downstream end. The annular overhang is intermediate to the upstream end and the downstream end of the stem. The heat shield includes a first end and a second end, and the heat shield is welded to the annular overhang at the heat shield first end. An annular air gap is between the nozzle stem and the heat shield.

Methods for shielding heat from a fuel nozzle stem of a fuel nozzle

A fuel injector has at least two generally parallel feed strips. Each of the feed strips is constructed from a single bonded together pair of lengthwise extending plates, each plate having a single row of widthwise spaced apart and lengthwise extending parallel grooves. The plates in each strip are bonded together such that opposing grooves in each of the plates are aligned forming internal fuel flow passages through the length of the strip from an inlet end to an outlet end of the strip. The inlet ends are spaced apart from each other and the outlet ends are spaced apart from each other. Each of the feed strips has one or more convolutions along a length of the strip and the feed strips are not bonded together along the convolutions. The feed strips may be spaced apart from each other or may be in contact with each other.

Fuel injector fuel conduits with multiple laminated fuel strips

Methods and apparatus for shielding heat from a fuel nozzle stem of fuel

A transfer tube system includes a transfer tube, a spring, a pair of opposing seats, and a pair of end assemblies that provide independent axial spring loading of the opposing seats. The spring loading assures continuous sealing contact regardless of dynamic loading, dimensional stack-up, or geometry change resulting from interfaced wear. The transfer tube end assemblies include a spherical or conical seat for mating with the transfer tube. Particularly, the transfer tube has spherical ends for seating in the transfer tube end assembly seats. The conical/spherical seats permit angular motion of interfacing components without lift off and therefore assures minimal leakage.

Low leakage, articulating fluid transfer tube

A tube coupling assembly has independent primary and secondary sealing elements. The coupling assembly includes first and second coupling members which define a fluid passage therethrough. The coupling members are arranged relative to one another so as to define a contact seal therebetween. An annular fluid path extends between the contact seal and the fluid passage, and a seal element, such as an O-ring is disposed in said fluid path. Accordingly, the seal element is always in contact with, and thus cooled by, the fluid in the passage. The coupling assembly also includes a coupling nut disposed over a portion of one of the coupling members and threadingly engaging the other coupling member to retain the coupling members together. A plurality of resilient fingers is provided on one of the coupling members, and a plurality of grooves is formed in the coupling nut. The fingers are received in the grooves so as to oppose rotational displacement of the coupling nut from its assembled position.

Cooled and wetted redundant seal tube fitting

The present invention provides a method and apparatus including a rotor mountable fixture for guiding a cutting tool powered by a hand held air motor to machine a gas turbine engine rotor without removing the rotor from its mountings in the engine. In one particular embodiment the fixture includes a root having the same contour as a blade root slot of a rotor, a base having a platform attached to the root, and a machining guide in the form of a bushing restrained in a guide slot operable to receive and guide a hand held air motor powered cutting tool for machining the rotor. The present invention provides an accurate means to machine a gas turbine engine rotor without removing the rotor from its mounting. In one particular embodiment a method for machining the rotor in the field is provided using a hand held air motor to power a machining tool to cut a blade damper pocket in the dovetail slot of a pressure compressor rotor.

Fixture and method for machining rotors

A turbine frame includes first and second coaxially disposed rings having a plurality of circumferentially spaced apart struts extending therebetween. A plurality of clevises join respective first ends of the struts to the first ring for removably joining the struts thereto. Each of the clevises includes a base removably fixedly joined to the first ring, and a pair of legs extending away from the base and spaced apart to define a U-shaped clevis slot receiving the strut first end. The strut first end is removably fixedly joined to the clevis legs by a pair of expansion bolts. The clevis base includes a central aperture aligned with a first port in the first ring for providing access therethrough.

Turbine frame

The present invention provides a phase independent damper and damper assembly capable of damping rotor blade vibrations in the axial, circumferential, and radial directions. One embodiment, particularly useful in an aircraft gas turbine engine compressor rotor, provides a damper and damper assembly including a generally axially extending blade damper operable to fictionally engage a generally axially extending circumferentially facing surface of a disk and axially extending angled surface under the platform of the blade. The invention provides an additional advantage of allowing simple and easy modification of existing engines to incorporate the damper of the present invention.

Blade damper

A process for identificaiton, evaluation and removal of microshrinkage of investment cast superalloy parts and parts produced by the process. Parts free of deleterious microshrinkage capable of longer life at existing stress levels or use at higher alternating stresses are produced by first subjecting the parts to hot isostatic pressing to eliminate nonsurface connected subsurface microshrinkage. Next, in order to expose near-surface microshrinkage microscopically connected to the surface, the parts are immersed in an acid solution for a time sufficient to uniformly remove at least about 0.005 inches of the original as cast surface. The exposed microshrinkage is evaluated for acceptability or removal by standard nondestructive techniques, such as liquid penetration evaluation.

Process for identification evaluation and removal of microshrinkage

A temperature-sensitive, deformable cylinder locknut for use in high temperature applications associated with the operation of a gas turbine engine provides a secure fastener lock which resists torsional and vibrational stresses which may otherwise act to unseat and disengage the bolt. The locknut includes an undeformed threaded portion, an unthreaded transitional cylindrical sleeve portion, and a deformable unthreaded cylindrical portion. A threaded shaft contacts the cylindrical sleeve with reduced surface engagement to minimize frictional interaction and define a spiral volume therebetween to ensure the establishment of a non-permanent lock.

Deformable cylinder locknut

A method of using a rotor mountable fixture for guiding a cutting tool powered by a hand held air motor to machine a gas turbine engine rotor without removing the rotor from its mountings in the engine is provided. In one particular embodiment the fixture includes a root having the same contour as a blade root slot of a rotor, a base having a platform attached to the root, and a machining guide in the form of a bushing restrained in a guide slot operable to receive a guide a hand held air motor powered cutting tool for machining the rotor. The present invention provides an accurate means to machine a gas turbine engine rotor without removing the rotor from its mounting. In one particular embodiment a method for machining the rotor in the field is provided using a hand held air motor to power a machining tool to cut a blade damper pocket in the dovetail slot of a pressure compressor rotor.

Growing community of inventors

Morrow, OH, United States of America

Peter W Mueller