General Electric Company

Scott Patrick Ryczek

Derek Thomas Dreischarf

Robert Paul Czachor

Courtland Earl Pegan, Jr

Gary Charles Liotta

Tod Kenneth Bosel

David A Niday

Kurt Thomas Hildebrand

James Patrick McGovern

Gianni Busso

Eric Robert Oswald

Michael R Hesselbrock

Courtland Earl Pegan

Jr Courtland Earl Pegan

David Andrew Niday

A system for use in limiting axial movement between a hanger and a fairing assembly within a turbine assembly is provided. The hanger includes an inner radial hanger bend portion that defines a hook channel therein. The fairing assembly includes an outer surface, a hook member extending from the outer surface to mate with the hook channel, and a circumferential groove defined in the outer surface such that at least a portion of the hanger bend portion is positioned between the circumferential groove and the hook member. The system includes a retention member sized for insertion into the circumferential groove, wherein the retention member is configured to extend from the circumferential groove and press against the hanger bend portion to facilitate maintaining the hook member within the hook channel.

System and method of limiting axial movement between components in a turbine assembly

A tripod joint assembly for connecting first and second overlapping panel segments of a flowpath liner in a gas turbine engine includes a threaded fastener extending through an opening in the first overlapping panel segment and adjacent to an outer segment edge of the second overlapping panel segment disposed on the first overlapping segment. The assembly further includes a tripod plate having first and second plate edges and an access hole therebetween. The first plate edge contacts the first overlapping panel segment, the second plate edge contacts the outer segment edge of the second overlapping panel segment. The access hole is disposed around the threaded fastener. First and second washers are disposed around the threaded fastener, the first washer on the tripod plate opposite to the overlapping panel segments, and the second washer on the first washer opposite to the tripod plate. A threaded locknut secures the assembly.

Wear resistant frame liner joint assembly for a gas turbine engine

A fairing for a turbine engine strut includes: inner and outer bands; a vane extending between the bands; the fairing is split along a generally transverse plane passing through the bands and the vane, defining nose and tail pieces; wherein the vane is defined by spaced-apart sidewalls extending between a leading edge and a trailing edge, each sidewall split into forward and aft portions by the transverse plane; wherein each sidewall portion carries a radially-inwardly extending post, the posts positioned such that pairs of the posts lie adjacent to each other when the nose piece and tail piece are assembled, wherein each pair of adjacent posts includes at least two non-parallel faces; and a pair of slotted buckles, wherein each slotted buckle surrounds and clamps together a pair of the posts, wherein each pair of adjacent posts contacts a slot of the corresponding buckle in a tripod contact configuration.

Tripod buckle for split fairing of a gas turbine engine

Gas turbine engine frames are disclosed. An example gas turbine engine frame may include a generally annular outer casing disposed coaxially about a hub; a plurality of circumferentially spaced apart struts joined to the hub and the outer casing, individual struts extending radially outwardly from the hub to the outer casing; and a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts. The stiffening rail may extend radially inward beyond the inner surface of the outer casing between the struts.

Gas turbine frame stiffening rails

A method enables a structural cover for a gas turbine engine to be manufactured. The method includes forming a torroidial body including an integrally-formed windage cover portion and a seal flange portion, and forming a plurality offastener openings extending from a forward side of the torroidial body to an aft side of the torroidial body, such that when installed in the gas turbine engine, the windage cover portion facilitates shielding the fastener openings from a gas flow path.

Structural cover for gas turbine engine bolted flanges

A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed between adjacent ones of the bands and circumferentially overlap the bands. The panels and bands are joined together at the respective overlaps using tripod plates and fasteners therethrough for allowing circumferential movement therebetween while providing sealing.

Tripod plate for turbine flowpath

A thermal radiation shield is joined to an annular casing through which combustion gases are axially flowable. The shield is spaced at least in part radially inwardly from the casing inner surface and includes axially spaced apart forward and aft edges and radially outer and inner surfaces extending axially therebetween. The shield includes a trough disposed in the outer surface which faces the casing inner surface, and the trough extends along the shield at least in part both axially and circumferentially. A flow conduit extends through the casing and in flow communication with the trough for channeling cooling air thereto. The shield protects the casing from thermal radiation, and the trough is effective for channeling the cooling air both circumferentially and axially for reducing thermal gradients.

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Cincinnati, OH, United States of America

Scott Patrick Ryczek