General Electric Company

Roger Lee Doughty

Jason David Shapiro

Toby George Darkins, Jr

Michael John Franks

Mark Eugene Noe

Monty Lee Shelton

Joshua Brian Jamison

Richard William Jendrix

Samuel Ross Rulli

Ching-Pang Lee

Steven Robert Brassfield

Aaron Michael Dziech

Craig Alan Gonyou

John Peter Heyward

Mark Leonard Hopper

Victor H Correia

Elias Harry Lampes

Brian Kenneth Corsetti

Jacob Patrick Miller

Chad Daniel Kleinow

Cory Michael Williams

Justin Adam Masters

Robert Carella

Toby George Darkins

Toby George Darkins Jr

Jason David Shaprio

Victor Correia

A gas turbine engine having a damping system that includes features for optimizing the damping response to vibrational loads on a rotary component for a wide range of operational conditions is provided. In one aspect, the damping system includes a damper control valve. The damper control valve receives working fluid from a working fluid supply and has a valve plunger movable between a first position and a second position. When the valve plunger is in the first position, the damper control valve permits working fluid to flow to a first damper associated with a first bearing coupled with the rotary component and to a second damper associated with a second bearing coupled with the rotary component. When the valve plunger is in the second position, the damper control valve permits working fluid to flow to the first damper but not the second damper.

Damper control valve for a turbomachine

A shroud and shroud hanger are provided wherein at least the shroud is formed of ceramic matrix composite material. The shroud and hanger extend in a circumferential direction. A generally C-shaped clip extends radially to retain the hanger and shroud together.

CMC shroud support system

A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.

Mounting apparatus for low-ductility turbine shroud

A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.

Low-ductility turbine shroud

A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.

Turbine airfoil components containing ceramic-based materials and processes therefor

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.

An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.

Airfoil cooling circuits and method

A turbine nozzle baffle includes a plurality of apertures inclined through a shell for discharging a coolant tangentially therefrom. The baffle is disposed inside a nozzle vane and the tangentially discharged coolant flows generally parallel along the inner surface of the vane for convection cooling thereof.

Tangential flow baffle

A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.

End rail cooling for combined high and low pressure turbine shroud

A gas turbine engine hollow turbine airfoil, such as a first stage vane of a high pressure turbine of a gas turbine engine includes an outer wall surrounding a hollow interior. The outer wall extends radially outwardly in a spanwise direction from an airfoil base to an airfoil tip and has chordwise spaced apart leading and trailing edges and widthwise spaced apart pressure and suction side portions extending chordwise between the leading edge and a trailing edge block which terminates at the trailing edge. A plurality of trailing edge cooling air ducts extend chordwise through the trailing edge block aftwardly from the hollow interior and a plurality of trailing edge film cooling holes extend from the ducts through the trailing edge block. The cooling air ducts are preferably centered near a neutral axis of chordwise and spanwise bending of the trailing edge block. The trailing edge cooling air ducts converge aftwardly from the hollow interior and preferably converge in width with a substantially constant spanwise height. The invention is particularly suitable for turbine airfoils and vanes made with a ceramic matrix composite material such as one having a SiC matrix and, more particularly, with an SiC&mdash;SiC ceramic matrix composite. The airfoil is disposed between radially inner and outer segmented platforms that are, in one embodiment, integrally formed of a ceramic matrix composite (CMC) preferably a SiC&mdash;SiC CMC.

Ceramic turbine airfoils with cooled trailing edge blocks

A gas turbine engine hollow airfoil includes an airfoil outer wall having width wise spaced aparted pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of the airfoil and extending longitudinally from a root to a tip. At least one internal aft flowing serpentine cooling circuit inside the airfoil has an exit that is positioned aft of the entrance so as to have a chordal flow direction afterwards from the leading edge to the trailing edge within the serpentine circuit. At least one longitudinally extending first side wall impingement chamber is in downstream fluid communication with the serpentine cooling circuit within the airfoil and positioned between one of the side walls, preferably the pressure side wall, and a first inner wall bounding the serpentine cooling circuit. Impingement cooling apertures are disposed in the first inner wall between one of the serpentine channels and the side wall impingement chamber. A first plurality of side wall film cooling holes may extend out from the first side wall impingement chamber through the pressure side wall. At least one tip cooling hole extending out of at least one of the impingement chambers may be disposed through a longitudinally outer tip wall of the tip of the airfoil.

Growing community of inventors

Pleasant Plain, OH, United States of America

Roger Lee Doughty