General Electric Company

General Electric Technology Gmbh

Travis J Packer

Brad Wilson Vantassel

Joseph Anthony Weber

Brad Wilson VanTassel

Evan Andrew Sewall

Zachary John Snider

Nicholas William Rathay

Jeffrey Clarence Jones

Bryan David Lewis

Michael Alan Hile

James Stuart Pratt

Benjamin Paul Lacy

Scott Alan Schimmels

William Scott Zemitis

Glenn Curtis Taxacher

Jacob John Kittleson

Jonathan Matthew Lomas

Christopher Donald Porter

Ibrahim Sezer

Jose Troitino Lopez

Gustavo Adolfo Ledezma

Robert William Davidoff

Richard William Jendrix

Raymond Michael Brown

Bradford Alan Tracey

Ian Darnall Reeves

Thomas Ryan Wallace

James Hamilton Grooms, Iii

James Grooms

Elisabeth Kraus Black

Keith Alan Lord

Joseph Daniel Franzen, Jr

David Fasig

Steven Paul Byam

William Charles Vincent

Dillon Mathew Smith

Brad Wilson Van Tassel

Jr Joseph Daniel Frazen

Keith Lord

Methods, apparatus, systems, and articles of manufacture are disclosed to implement a stator plenum with collet seal. The stator plenum for a gas turbine engine includes an outer shell circumscribing a centerline axis, a first end of the outer shell coupled to an engine casing at a first coupling, the first coupling to form a first seal, a second end of the outer shell coupled to the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, the second coupling to form a second seal, and a cavity formed by the outer shell, the cavity to contain cooling flow to reduce a temperature of a turbine.

Stator plenum for a gas turbine engine

A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

Clearance control assembly

A cooling assembly comprises a coolant source chamber inside an airfoil that directs coolant inside the airfoil that extends between a hub end and a tip end that includes a tip body and tip rail along a radial length. A first body cooling chamber and a second body cooling chamber are disposed inside the tip body. The second body cooling chamber is positioned between the tip end and the first body cooling chamber. At least one of the first or second body cooling chambers are fluidly coupled with the coolant source chamber. The coolant source chamber directs the coolant into the first or second body cooling chambers. A rail cooling chamber disposed inside of the tip rail is fluidly coupled with the first or second body cooling chambers. The first or second body cooling chambers directs coolant out of the body cooling chambers and into the rail cooling chamber.

Cooling assembly for a turbine assembly

A mask is provided for an additively manufactured part including a plurality of spaced openings in a surface of the part. The mask is made with the part and includes an attachment ligament configured to integrally couple to the part between the openings in a cantilever fashion. First and second cover members include a proximal ends integrally coupled to the attachment ligament and distal ends extending at least partially over a respective portions of the plurality of openings. A detachment member extends from each of the first and second cover members. The attachment ligament is the sole connection to the part. The mask may have an umbrella shape in cross-section.

Cantilevered mask for openings in additively manufactured part

A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickness wall from the internal cavity, the impingement plate including a plurality of apertures for directing the cooling fluid into an impingement cavity and against the variable thickness wall, wherein the impingement plate is configured to follow a contour of the variable thickness wall.

Integrated nozzle and diaphragm with optimized internal vane thickness

An impingement insert for HGP component may include a hollow body having a longitudinal extent, an exterior surface and an interior surface. The hollow body may include a first side wall, a second side wall contiguous with the first side wall at a first end of each, the second side wall is flexibly movable relative to the first side wall. A spring element is contiguous with a second end of each of the first side wall and the second side wall, and extends along at least a portion of the longitudinal extent of the hollow body and into the hollow body between the first side wall and the second side wall. The spring element biases the side walls to an expanded position from a compressed position of the hollow body. Cooling passages pass between the exterior surface and the interior surface of the hollow body in both side walls.

Impingement insert with spring element for hot gas path component

A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.

Shroud for gas turbine engine

Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.

Turbine shroud including plurality of cooling passages

A hollowed body component made by additive manufacturing is disclosed. The hollow body has a longitudinal extent, an exterior surface and an interior surface, the interior surface having a first side and an opposing, second side. A first set of curved supports are curved along lengths thereof and extend between the first side and the opposing, second side to support the hollow body at least during the additive manufacturing thereof. Some embodiments include cooling passages open to the interior surface. Here, the curved supports extend between opposing pairs of passage-free spaces on the interior surface to support the hollow body at least during the additive manufacturing thereof. In one example, the component is an impingement insert for a hot gas path component.

Additively manufactured hollow body component with interior curved supports

A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.

Shroud and seal for gas turbine engine

A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.

Vibration systems and systems including vibration systems for filling incomplete components with slurry material are disclosed. The vibration systems may include a vibration platform, and a component retention plate releasably coupled to the vibration platform. The component retention plate may include a plurality of component holders positioned on the component retention plate. Each of the plurality of component holders may receive a distinct, incomplete component in a predetermined orientation. The vibration systems may also include a motor operatively coupled to the vibration platform to vibrate the vibration platform at a predetermined frequency. The predetermined frequency may be based on characteristic(s) of each of the incomplete components.

Systems including vibration systems for filling incomplete components with slurry material

A turbine shroud segment including: a target exterior surface and target interior region; and a cooling configuration having first and second channel types. The first channel type includes: an inlet and outlet; a target section extending through the target interior region; lateral ports spaced lengthwise between first and second ends of the target section; and a path within the target interior region offset from the target exterior surface by a minimum offset. The second channel type includes: dead-ends disposed at first and second ends; lateral ports connecting to lateral ports of the first channel type; and a path through the target interior region that is variable between valleys and peaks. The second channel type resides closer to the target exterior surface at the valleys than at the peaks. At each of the valleys, the second channel type resides within the minimum offset.

The disclosure relates to a tip member configured to be coupled to a blade structure for a turbomachine. A body of the tip member includes: a first surface configured to engage a radially outboard end of the blade structure, a second surface positioned opposite the first surface, and at least one perimeter sidewall positioned between the first and second surfaces, wherein the at least one perimeter sidewall has an airfoil cross-section; and an opening passing through the body from the first surface to the second surface, and having a single directional orientation therebetween, wherein the opening is sized to receive a post positioned on the radially outboard end of the blade structure.

Tip member for blade structure and related method to form turbomachine component

An injection mold system for injecting slurry into an internal portion of an injection mold component core is disclosed. The system may include a fill clip for injecting slurry into an internal portion of an injection mold component core including a fill member for injecting slurry into the internal portion of the injection mold component core, and a latch member for removably coupling the fill member with the injection mold component core. The system may also include a fill reservoir for collecting excess slurry from the internal portion of the injection mold component core. The fill reservoir may also redistribute the excess slurry back into the internal portion of the injection mold component core.

Growing community of inventors

Simpsonville, SC, United States of America

Travis J Packer