General Electric Company

United Technologies Corporation

Ratheyon Technologies Corporation

Mark Broomer

Timothy M Davis

Mark John Rogers

Carson A Roy Thill

Craig R McGarrah

Victor Hugo Silva Correia

Russell E Keene

Robert Francis Manning

Anthony B Swift

Paul Hadley Vitt

Anthony P Cherolis

Tyler Frederick Hooper

Bhanu Mahasamudram Reddy

Brian Kenneth Corsetti

Wilson Frost

Kevin W White

Robert L Hazzard

Timothy A Dunbar

Conway Choung

Haidong Liu

Stephen Kin-Keung Tung

Jason Michael Ulberg

Victor Hugo Correia

Craig Mcgarrah

An apparatus for a nozzle assembly for a turbine engine and a method of forming the nozzle assembly are described herein. The nozzle assembly can include a set of nozzles including an inner band and an outer band, with one or more airfoils extending between the inner and outer bands. The nozzles can be coupled to adjacent nozzles at the inner and outer bands to form the nozzle assembly. A throat can be defined at the minimum cross-sectional area between adjacent airfoils in the nozzle assembly. A formed portion can be formed on either of or both of the inner or outer band at the throat.

Nozzle assembly for turbine engine

In one aspect, a sealing assembly for a turbine of a gas turbine engine includes a first turbine component having a first surface and a second surface positioned aft of the first surface. The first turbine component, in turn, defines a slot positioned between the first surface and the second surface. Furthermore, the sealing assembly includes a second turbine component positioned aft of the first turbine component such that the first component and the second component define a gap therebetween. Additionally, the sealing assembly includes a seal configured to seal the gap defined between the first turbine component and the second turbine component. The seal includes a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first component. Moreover, the seal further includes a second portion that exerts a sealing force on the second component.

Turbine snap in spring seal

A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.

Gas turbine engine seal

A turbine shroud for incorporation in a turbine of a gas turbine engine has a plurality of butted shroud segments circumferentially arrayed to form a ring. Each of the shroud segments has an arcuate main shroud body portion, a radially inward extending annular flange attached to a first end of the main body portion, and a radially outward extending flange with a plurality of mounting apertures attached to a second end of the main shroud body portion. A first mounting aperture is sized smaller than an adjacent second mounting aperture in the radially outward extending flange.

Low leakage duct segment using expansion joint assembly

A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.

Turbine band anti-chording flanges

An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.

Assembly for sealing a gap between components of a turbine engine

A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.

Gas turbine engine ring seal

An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

Low leakage multi-directional interface for a gas turbine engine

An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.

Flexible finger seal for sealing a gap between turbine engine components

A method for repairing a turbine nozzle segment includes providing a turbine nozzle segment having an enclosure with an integral discourager, removing the enclosure and/or the discourager from the turbine nozzle segment and attaching a new enclosure ad/or discourager to the turbine nozzle segment.

Method for repairing a turbine nozzle segment

A turbine nozzle includes outer and inner bands bounding nozzle vanes. The outer band includes an aft flange. An impingement baffle bridges the outer band and aft flange at the root thereof to provide impingement cooling.

Flange cooled turbine nozzle

A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.

Divergent turbine nozzle

A turbine nozzle segment includes a band having a flowpath side and a non-flowpath side and an enclosure disposed on the non-flowpath side of the band. A plenum may be defined between the band and the enclosure and a discourager may extend from the enclosure.

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Boston, MA, United States of America

Mark Broomer