General Electric Company

Frederic Woodrow Roberts, Jr

Victor John Morgan

Matthew Troy Hafner

Glenn Curtis Taxacher

Tyler Christopher Henson

Aaron Ezekiel Smith

John McConnell Delvaux

Paul Stephen DiMascio

Jason Robert Parolini

Brendon James Leary

Jacob John Kittleson

Herbert Chidsey Roberts, Iii

Brad Wilson Vantassel

Ibrahim Sezer

Russell Pierson DeForest

Peter De Diego

Neil Devin Ristau

James William Vehr

Evan Andrew Sewall

George Andrew Gergely

James Stewart Phillips

Michael John Brown

Brendan James Leary

A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.

Gas turbine component with ejection circuit for removing debris from cooling air supply

A gas turbine component includes a turbine component having an outer wall and an internal cooling passage; a cooling air supply hole through the outer wall in fluid communication with the internal cooling passage; and a filter mound disposed over the cooling air supply hole. The filter mound includes a filter mound wall projecting from the turbine component and defining an interior of the filter mound. At least one hole in the filter mound wall extending through the filter mound wall is configured to permit cooling air supply to pass therethrough while blocking debris from passing through the interior of the filter mound and clogging the cooling air supply hole in fluid communication with the internal cooling passage. The turbine component and the filter mound are formed during manufacturing of the turbine component.

Cooling hole filter configuration

A turbine shroud assembly including an outer shroud arranged within a turbine and further comprising opposed extending portions. The turbine shroud assembly further including an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The turbine shroud assembly further including a spline seal extending between the first and second arcuate portions and positioned between the inner shroud and the outer shroud. The turbine shroud assembly further including at least one of the inner shroud, the outer shroud and the spline seal including at least one protrusion for maintaining positive retention of the spline seal during non-operation of the turbine.

Turbine shroud assembly

The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Turbine nozzle airfoil profile

A turbine component including an outer shroud arranged within a turbine and including opposed extending portions. An inner shroud shields the outer shroud from a gas flowing along a gas path within the turbine during its operation and including opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud. A first pin and second pin have a respective first end and second end. The first arcuate portion having a first engagement region for engaging the first end, and second arcuate portion having a second engagement region for engaging the second end. In response to engagement of the first engagement region and the first end of the first pin, and engagement of the second engagement region and the second end of the second pin, the inner shroud is prevented from twisting relative to the outer shroud.

Turbine component and turbine shroud assembly

Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.

Cooling structure for hot-gas path components with methods of fabrication

A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.

Turbine shroud assembly and method for loading

A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.

A turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies includes a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the second shroud block.

Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arc segment adjacent to a second arc segment, each arc segment including an end surface and radially facing surfaces extending from opposite ends of the end surface; a slot located between the end surfaces of the first arc segment and the second arc segment; and a first seal disposed in the slot, the first seal contacting the first arc segment at the end surface and extending over the radially facing surfaces of the first arc segment, the first seal including: a shim contacting the first arc segment; a laminate material over the shim and covering the shim; and a conforming material coupling the laminate material to the shim.

Anti-corner-leakage seal in gas turbine

A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.

Gas turbine component and process for producing gas turbine component

A casing for a turbo-machine at least partially defines a flow path for a working fluid through or around one or more of a compressor section, a combustor assembly, or a turbine section. The casing defines an inner surface and the inner surface defines a plurality of debris routing channels. The plurality of debris routing channels are configured to route debris in a working fluid within the casing towards a debris collection mechanism.

Debris removal system

The present invention is a coated article containing at least two adjacent cooling holes that are substantially uncoated. In an embodiment, the coated article includes a base material, an outer surface and a coating on a portion of the outer surface. Here, the adjacent cooling holes are arranged along an axis on the outer surface and extend within the base material at an angle to the outer surface. The coating may include at least one unfinished edge oriented substantially parallel to the axis and set off at an oblique angle and a distance from the adjacent cooling holes.

Coated article

A turbine vane or blade segment includes at least one airfoil extending radially outwardly from a radially inner band. A plurality of cooling passages are formed in the radially inner band in fluid communication with an internal plenum in the airfoil and exiting the inner band via a plurality of exit holes in the one of the axially-extending side edges of the inner band. The plurality of exit holes are confined to a region along the one of the axially-extending side edges where static pressure Palong the one of the substantially axially-extending side edges lies in a pressure range substantially between the stage inlet total pressure Pand a pressure that is substantially about 1.5 times the dynamic pressure range &#x394;P, below the stage inlet total pressure.

Growing community of inventors

Simpsonville, SC, United States of America

Frederic Woodrow Roberts, Jr