General Electric Company

Sergio Daniel Marques Amaral

Gary Michael Itzel

Xiuzhang James Zhang

Mark Steven Honkomp

Camilo Andres Sampayo

Scott Edmond Ellis

Jalindar Appa Walunj

Anthony Louis Giglio

Michael Adelbert Sullivan

Felipe Roman-Morales

Mark Stevens Honkomp

A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit. The bucket assembly further includes a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face and further includes a forward face, an aft face, and a top face. The bucket assembly further includes a plenum at least partially defined in the platform. The plenum is in fluid communication with the main cooling circuit and extends from the main cooling circuit towards the suction side slash face.

Bucket assembly for turbine system

A component is provided and includes a first surface, a second surface adjacent to and oriented transversely with respect to the first surface and having a pocket formed therein defining a rib along a periphery thereof and a thermal barrier coating (TBC) respectively applied to the first surface and to the second surface at the pocket such that the rib is interposed between the TBC of the first and second surfaces.

Component of a turbine bucket platform

A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity.

System and method for cooling a turbine bucket

A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component.

Bimetallic spline seal

A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from the root portion to the blade tip, and a squealer tip cavity formed at the blade tip, the blade tip comprising: a trailing edge trench originating at the squealer tip cavity, wherein the trailing edge trench generally extends toward the trailing edge of the blade tip.

Growing community of inventors

Simpsonville, SC, United States of America

Sergio Daniel Marques Amaral