General Electric Company

Other

Mechanical Dynamics and Analysis, LLC

Fred Thomas Willett, Jr

Henry Grady Ballard, Jr

Xiaoqing Zheng

Michael Earl Montgomery

Daniel Mark Brown

Kenneth Michael Koza

Jason Winfred Jewett

Richard James Miller

Emad Andarawis Andarawis

Gary Michael Itzel

William Edward Adis

Paul Stephen DiMascio

Stephen Francis Rutkowski

Thomas Earl Dyson

Brian Gene Brzek

Larry W Plemmons

Michael Dennis Mack

Timothy Scott McMurray

Joseph Leonard Moroso

Eric David Roush

Ariel Caesar Prepena Jacala

Doyle Clyde Lewis

Kevin John Lewis Roy

Peter John Eisenzopf

Laurence Scott Duclos

Robert Gerard Baran

Paul S Dimascio

Roy Paul Swintek

Pepe Palafox

Timothy Michael Moricca

Ravi Shankar Venkata Kasibhotla

Howard Michael Brilliant

Anantha Padmanabhan Bhagavatheeswaran

Dimitrios Stathopoulos

James Edward Olson

Robert James Piechota

In one embodiment, an airfoil includes an airfoil body portion, an airfoil tip portion disposed radially outward of the airfoil body portion, an airfoil root portion, and a plurality of radial cooling passages extending through the airfoil body portion from the root portion to the tip airfoil portion. The airfoil body portion and the airfoil tip portion are joined at a braze interface or a weld interface. The airfoil tip portion includes at least one manifold fluidly connecting at least one radial cooling passage to at least one other radial cooling passage.

Cooled airfoil and method of making

A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.

Gas turbine and spacer disk for gas turbine

The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes an airfoil, a tip shroud having a side surface and a radially outer surface, and a transition portion coupling the tip shroud to the airfoil. The airfoil, the transition portion, and the tip shroud collectively define a primary cooling passage therein. The primary cooling passage includes a primary cooling passage outlet defined by the side surface of the tip shroud.

Cooling passage for gas turbine rotor blade

A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance.

Stator seal for turbine rub avoidance

A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.

Systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine

A method of forming a component having an internal passage defined therein includes positioning a jacketed core with respect to a mold. The jacketed core includes a hollow structure that includes an interior portion shaped to define at least one interior passage feature of the internal passage. The jacketed core also includes an inner core disposed within the hollow structure and complementarily shaped by the interior portion of the hollow structure. The method also includes introducing a component material in a molten state into a cavity of the mold to form the component, such that the inner core defines the internal passage including the at least one interior passage feature defined therein.

Method and assembly for forming components having an internal passage defined therein

A turbomachine blade may include an airfoil and a shank coupled to the airfoil. The shank may include a cover plate having a first circumferential face and a second, opposing circumferential face. A radial cooling groove is positioned in the first circumferential face and is configured to allow a cooling fluid to pass from a first radial position to a second, different radial position relative to the platform. The radial cooling groove provides cover plate and shank cooling. In addition, the radial cooling groove may deliver fluid for purging gaps between blade platforms and cover plates, which prevents the ingestion of hot gas from the turbine flowpath.

Turbomachine blade cover plate having radial cooling groove

A system and method for measuring and adjusting rotor to stator clearances is disclosed, as well as a turbomachine embodying the system and method. In an embodiment, a turbomachine is assembled, including a stator having an upper and a lower stator shell, and a rotor disposed within the stator. A cold clearance between the rotor and the stator is determined at each of a plurality of clearance measurement points using an in situ clearance sensor system. Each of the clearance measurement points is axially spaced from each other clearance measurement point. The cold clearance between the rotor and the stator is adjusted based on the determined cold clearances, by displacing one of the upper stator shell or the lower stator shell relative to a foundation, thereby changing a shape of the upper stator shell or the lower stator shell to accommodate a position of the rotor within the stator.

Turbomachine cold clearance adjustment

A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.

Turbine shell with pin support

A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.

Swirl interruption seal teeth for seal assembly

A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.

Adjustable turbine seal and method of assembling same

An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a dovetail, where the inner shell, the plurality of nozzle carriers and the nozzles and buckets define a steam path. A radial position of the dovetails in the nozzle carriers within its corresponding grooves is selectable according to the steam path, and an axial width of each of the nozzle carriers is selectable according to the steam path.

Steam turbine inner shell assembly with common grooves

Systems and devices adapted to retain dovetail components (e.g., buckets) in a turbine drum rotor and reduce rotor component displacement are disclosed. In one embodiment, a turbine bucket includes: a bucket base portion shaped to complement a bucket shank slot in a rotor of a turbine, the bucket base portion including: a forward portion shaped to extend upstream of a first stage circumferential slot of the rotor in to a first rotor post of the rotor; a circumferential protrusion formed in an aft end of the bucket base portion and shaped to connect to the rotor, and a set of axial protrusions formed on tangential sides of the bucket base portion and shaped to connect to the rotor; and a bucket platform extending radially outboard from the bucket base portion, the bucket platform configured to complement a vane.

Drum rotor dovetail component and related drum rotor system

A method and apparatus for determining axial clearance data between a rotor and a stator are disclosed. At least one radial clearance sensor is positioned on the stator and is configured to gather radial clearance data, i.e., measurements of a radial distance between the rotor and the stator taken at discrete time intervals. A computing device is operably connected with the at least one radial clearance sensor and is configured to use the radial clearance data to determine axial clearance data, i.e., an axial distance between the stator and the rotor. In one embodiment, the computing device uses, among other data points, an indication of a loss of signal from at least one radial clearance sensor to extrapolate the axial clearance data.

Growing community of inventors

Burnt Hills, NY, United States of America

Fred Thomas Willett, Jr