General Electric Company

Exxonmobil Upstream Research Company

Donald Earl Floyd

Maruthi Prasad Manchikanti

Aaron Ezekiel Smith

David Martin Johnson

Victor John Morgan

Kenneth Damon Black

Brian Gene Brzek

Douglas Frank Beadie

Joseph Anthony Weber

John Wesley Harris, Jr

Michael James Healy

Gregory Allan Crum

Anthony Wayne Krull

Patrick Daniel Noble

Eugene Delano White

Wojciech Grzeszczak

Asish Uppath Naraparambath Ramesh

A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.

Turbomachine including clearance control system

Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.

Bearing housing

A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold.

System and method for a gas turbine engine sensor

A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.

Method and system for providing cooling for turbine components

A system includes a turbomachine that includes a stator and a rotor. The rotor is configured to rotate about a rotational axis relative to the stator. In addition, the rotor includes a least one rotary blade, and the at least one rotary blade has a patterned structure of beams and cavities.

Turbomachine blade with improved stiffness to weight ratio

A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component.

Connecting system for metal components and CMC components, a turbine blade retaining system and a rotating component retaining system

A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.

Growing community of inventors

Greenville, SC, United States of America

Donald Earl Floyd