General Electric Company

Other

David Scott Stapleton

Robert Charles Groves, Ii

Robert Proctor

Victor Hugo Silva Correia

Jason David Shapiro

Wei Wu

Kevin Robert Feldmann

Jonathan David Baldiga

Michael John Franks

Bryce Loring Heitman

Dylan James Fitzpatrick

Christopher Paul Tura

Christopher Michael Ceglio

Laura Isabelle Armanios

Ricardo Carbajal Diaz

A turbine engine component assembly includes a first part comprising a ceramic matrix composite material and having a first flange defining a first borehole, a second part defining a second borehole, and a pin inserted, in an axial direction, through the first borehole and the second borehole to connect the first part to the second part. The pin includes a first contact portion positioned at a first axial location of the pin corresponding to the first borehole and an elongated portion extending axially from the first contact portion. The first contact portion includes a first chamfered section, a second chamfered section, and a first contact surface between the first chamfered section and the second chamfered section. The first chamfered section and the second chamfered section slope away from the first contact surface with decreasing diameters.

Engine component assembly with ceramic matrix composite component and connection pin

An identification assembly is provided having a tag assembly and a bracket assembly, the tag assembly comprising a front plate rotatably fixed to a tag body. In accordance with embodiments, the front plate has two identification surfaces and the tag body has one identification surface, and the tag assembly is configured to removably receive the bracket assembly.

Separable identification assembly

An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.

Spline for a turbine engine

Separable tag for a collar

In one aspect, the present disclosure is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a shield wall constructed from a first material that includes a first shield wall portion and a second shield wall portion. A spring constructed from a second material includes a first spring portion and a second spring portion. The first shield wall portion is adjacent to the first spring portion, and the second shield wall portion is adjacent to the second spring portion.

Advanced stationary sealing concepts for axial retention of ceramic matrix composite shrouds

Shrouds and methods for forming turbine components are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a cooling passage defined in the shroud, the cooling passage extending generally circumferentially through the shroud.

Shrouds and methods for forming turbine components

A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

According to some embodiments, a ceramic matrix composite (CMC) hanger sleeve is provided for retaining a ceramic matrix composite shroud panel. The sleeve may be connected to an upper hanger by a retainer or a casing. The hanger sleeve includes a radially inward opening with a flowpath panel disposed therein. When the CMC flowpath panel is worn due to time, rubs or both, the panel may be replaced without need to replace the entire assembly.

CMC hanger sleeve for CMC shroud

A shroud hanger assembly or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi-piece hanger including a shroud positioned in a cavity between a first hanger portion and a second hanger portion. A shroud may be formed of a low coefficient of thermal expansion material which may have a differing coefficient thermal expansion than the material defining the shroud hanger. The shroud is deflected by an axial force acting between the hanger and the shroud which also forms a seal. The seal compensates for differing rates of thermal growth between the shroud and the hanger throughout the engine operating envelope.

Multi-piece shroud hanger assembly

Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.

Shroud assembly for gas turbine engine

Shroud assemblies and shrouds for gas turbine engines are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a rib disposed between and in contact with the forward flange and the rear flange.

Shroud assembly and shroud for gas turbine engine

A shroud apparatus for a gas turbine engine includes: an annular shroud segment having an arcuate bottom wall defining an arcuate inner flowpath surface, spaced-apart forward and aft walls extending radially outward from the bottom wall, and spaced-apart side walls extending radially outward from the bottom wall and between the forward and aft walls, each side wall defining an end face which includes: an axial slot extending in a generally axial direction along the end face; a first radial slot extending in a generally radial direction along the end face, and intersecting the axial slot; an axial spline seal received in the axial slot; and a first radial spline seal having an L-shape with radial and axial legs, the radial leg being substantially longer than the axial leg, wherein the radial leg is received in the first radial slot, and the axial leg is received in the axial slot.

Asymmetric radial spline seal for a gas turbine engine

A blade of a gas turbine engine is provided having an airfoil, a platform, a shank, a dovetail, and a skirt. The airfoil may extend distally from the platform, and the shank may extend proximally from the platform. The dovetail may also be provided to extend proximally from the shank. The skirt may be disposed on an aft side of the shank and may extend from the shank in a direction at least partially axially aft from the shank.

Growing community of inventors

Boston, MA, United States of America

David Scott Stapleton