General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

William Scott Zemitis

Melbourne James Myers

Richard Ryan Pilson

Felipe Roman-Morales

Jacob Charles Perry, Ii

Brian Stephen Gray

Derek Kanoa Tan

Kevin Leon Bruce

John Wesley Harris, Jr

Martin James Jasper

Calvin Levy Sims

Christopher Michael Penny

Michael Gordon Sherman

Luke C Sponseller

Kristen Barbara Coletti

Brad Van Tassel

Lauren Elizabeth Rogers

Aaron Ezekiel Smith

Craig Allen Bielek

Mark Steven Honkomp

Bradley Taylor Boyer

Brad Wilson Vantassel

Michelle Jessica Iduate

Travis J Packer

Alexander Stein

David Randolph Spracher

Ross James Gustafson

Randall Richard Good

Jason Douglas Herzlinger

Brad Wilson VanTassel

Xiaoyong Fu

Ariel Caesar Prepena Jacala

Dwight Eric Davidson

Bryan David Lewis

Srinivasa Govardhan Jayana

James Tyson Balkcum, Iii

Adebukola Oluwaseun Benson

Jason Adam Neville

Thomas James Brunt

Sze Bun Brian Chan

Ajay Gangadhar Patil

Jonathan Glenn Reed

Massimiliano Mariotti

Kevin Lee Worley

Holly Renae Davis

Peter Paul Pirolla

Adrian Lional Scott

Steve Paul Byam

Cody Jermaine Ford

Dustin James Hall

Michael James Gutta

Antonio Rodriguez

Dennis Scott Holloway

Daryl R Collins

Dustin Jaime Muller

Caitlin Hillary Swanson

Mahesh Pasupuleti

James Sutherland Stanley

Richard Gordon Rollings

Luke C Sponsellar

Luis Manuel Herrera

Babu Santhana Gopalakrishnan

Claire Katherine Naioti

Stephen Douglas Shearer

Robert Tomasz Liskiewicz

James Tyson Balkcum Iii

A gas turbine airfoil includes a trailing edge cooling hole that has an elliptical cross-sectional baseline shape. In addition, the exit passage wall leading to the trailing edge cooling hole has a surface that varies according to an exit passage profile. Applying an iterative method of embodiments can produce a final exit passage profile with significantly reduced thermal strain during operation as compared to the prior art, resulting in improved component life.

Aerodynamic turbomachine component with cooling features and method of making

Various embodiments include a turbine blade having an airfoil with a tip shroud having a forwardmost tip rail having one or more pressure side and suction side bevel surfaces and pressure side and suction side scallop surfaces. The surfaces have a nominal profile substantially in accordance Cartesian coordinate values of X, Y and Z set forth in various tables herein. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a tip rail length expressed in units of distance. The X, Y and Z values are connected by smooth continuing arcs that are joined smoothly with one another to form the nominal profile that defines the suction side scallop surface, the pressure side scallop surface, the suction side bevel surface, or the pressure side bevel surface.

Turbine blade tip shroud surface profiles

A turbine nozzle assembly includes at least one airfoil and an outer endwall coupled to a radial outer end of the at least one airfoil. A mounting rail is coupled to the outer endwall and extends at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall. A stress relief structure is defined in the mounting rail. The stress relief structure includes an end opening defined in a radial outer surface of the mounting rail, a slot defined through the rail thickness of the mounting rail and coupled to the end opening, and an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot. The oblong opening is arranged asymmetrically in a circumferential direction relative to the slot to relieve stress where prevalent in the mounting rail.

Turbine nozzle assembly with stress relief structure for mounting rail

A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.

Turbine blade tip shroud with axially offset cutter teeth, and related surface profiles and method

A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

Turbine blade tip shroud with protrusion under wing

A tip shroud may include a platform to couple to an airfoil having a pressure side and a suction side. A front tip rail and a rear tip rail extend radially from the platform with each including a downstream side, an upstream side, and an origin(s). Each of the downstream side and the upstream side of the rear tip rail and the downstream side of the front tip rail has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, Z set forth in a respective table and originating at a selected origin. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, Z values by a minimum rear tip rail X-wise extent expressed in units of distance. The X, Y, Z values are connected by lines to define each respective surface profile.

Surface profiles for tip rails of turbine blade tip shroud

A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.

Turbomachine rotor blade with a cooling circuit having an offset rib

A rotor blade is provided. The rotor blade includes a main body having a shank, an airfoil extends radially outwardly from the shank, and a platform. The main body includes a pressure side slash face and a suction side slash face. A slot is defined within each of the pressure side slash face and the suction side slash face. The slot of the pressure side slash face and the slot of the suction side slash face each include an upstream end portion that defines an end and a main body portion extending from the upstream end portion. The upstream end portion tapers from the end to the main body portion. The main body portion further includes a retention wall that covers a portion of the end and that defines an opening. The retention wall further includes an inner retention surface. The retention wall defines an offset from the opening.

Rotor blade sealing structures

A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or a downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

A tip shroud may include a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading and/or trailing Z-notch of the tip shroud, and/or upstream and/or downstream radially outer surfaces of a wing. The surface profiles may have a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and perhaps thickness, set forth in a respective table.

A tip shroud for a turbine blade of a gas turbine system includes a body coupled to a radial outer end of an airfoil of the turbine blade. The tip shroud may include at least one circumferentially extending tip rail. A first edge wall of the tip shroud extends axially and radially outwardly from the body along at least one of a leading circumferential-facing edge or a trailing circumferential-facing edge of the body and includes a circumferentially facing surface. Cooling passages are defined in the body and extend circumferentially therein to cool an area near the first edge wall. The tip shroud includes an exit surface adjacent the first edge wall, where the exit surface includes an exit opening through which at least one of cooling passages exits the body. The exit surface is angled relative to the circumferentially facing surface of the first edge wall in a range of 15&#xb0; to 80&#xb0;.

Tip shroud with exit surface for cooling passages

Turbine blade tip shroud surface profiles are disclosed. Embodiments of the tip shroud include a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end of the airfoil. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading and/or trailing Z-notch of the tip shroud, and/or downstream and/or upstream side radially outer surfaces of wings of the tip shroud. The surface profiles are stated as shapes having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table.

A turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a cooling circuit extending within the platform and the airfoil. The cooling circuit may include a root turn with an asymmetric shape to reduce stress concentrations therein. The asymmetric shape of the root turn may be asymmetrical along a path between a pressure side of the airfoil and a suction side of the airfoil. The asymmetric shape of the root turn may be asymmetrical within a plane defined by a radial direction and a circumferential direction.

Turbine bucket with a cooling circuit having an asymmetric root turn

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

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Simpsonville, SC, United States of America

William Scott Zemitis