General Electric Company

General Electric Technology Gmbh

Melbourne James Myers

William Scott Zemitis

Richard Ryan Pilson

Xiuzhang James Zhang

Jacob Charles Perry, Ii

Felipe Roman-Morales

Camilo Andres Sampayo

Martin James Jasper

Calvin Levy Sims

Zhirui Dong

Luke C Sponseller

Srikanth Chandrudu Kottilingam

Kevin Leon Bruce

Mark Steven Honkomp

Daniel Anthony Nowak

Sylvain Pierre

Michael Anthony Wondrasek

Ariel Caesar Prepena Jacala

Bryan David Lewis

Luke John Ammann

Adebukola Oluwaseun Benson

Bill Damon Johnston, Jr

Ajay Gangadhar Patil

Mary Virginia Holloway

Liming Xu

Jan Emeric Agudo

Kevin Lee Worley

Michael Gordon Sherman

Christopher William Kester

Peter Paul Pirolla

Joseph Block

Haiping Wang

Dustin Jaime Muller

Le Trong Tran

Dennis Scott Holloway

Brandon Joseph Kerins

Robert Joseph Testa, Jr

Joe Timothy Nowak

Xiuhang James Zhang

Claire Katherine Naioti

Stephen Douglas Shearer

Mahesh Pasupuleti

Stuart Samuel Collins

Christopher W Kester

Jan Agudo

An airfoil includes a root and a tip, which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The airfoil also includes a thermal barrier coating on the pressure side surface and the suction side surface. The thermal barrier coating includes a base layer and a top coat. A thickness of the base layer varies across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge.

Turbomachine airfoil having a variable thickness thermal barrier coating

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 turbine blade includes a root for fixing the turbine blade to a turbine rotor; and an airfoil coupled to the root, the airfoil including a suction side and a pressure side, and at least one internal wall defining a coolant chamber in the airfoil for delivering a coolant through the airfoil. A tip shroud is coupled to a radially outer end of the airfoil by a suction side fillet and a pressure side fillet. The tip shroud includes a shroud body defining a substantially trident-shaped shroud cooling passage including: a trunk cooling passage, a center cooling passage in fluid communication with the trunk cooling passage, a suction side cooling passage in fluid communication with the trunk cooling passage, and a pressure side cooling passage in fluid communication with the trunk cooling passage. The center cooling passage is fluidly coupled to the coolant chamber to receive a coolant.

Turbine blade with tip shroud cooling passage

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

Turbine blades having damper pin slot features

A turbine blade includes an airfoil that includes a root end and a tip end. The tip end is radially spaced from the root end. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. The shroud plate includes a plurality of undulating ridges.

Undulating tip shroud for use on a turbine blade

A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as 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 by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Airfoil shape for turbine rotor blades

A turbine rotor blade including an airfoil, tip shroud, and fillet formed therebetween. The fillet defines a fillet profile variable about the intersection for connecting the tip shroud and airfoil and facilitating aerodynamic airflow. The fillet includes a pressure side fillet. The pressure side fillet comprises a pressure side fillet profile per points within a first set of points of X, Y and Z coordinate values in a Cartesian coordinate system, as set forth in Table I, where X, Y and Z are distances in inches from an origin and, when the points are connected by smooth, continuing arcs, the points define the pressure side fillet profile of the pressure side fillet. The first set of points includes points between and including point 1 and point 50 of each reference plane between and including a reference plane H and a reference plane W, as set forth in Table I.

Tip shroud fillets for turbine rotor blades

A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.

Edge profiles for tip shrouds of turbine rotor blades

A method of modifying a shank of a turbine blade from an initial profile to an undercut profile includes removing a first portion of material from an underside of a downstream angel wing of the turbine blade. The downstream angel wing extends axially from a downstream cover plate of the shank. The method also includes removing a second portion of material from a generally axially-extending portion of the downstream cover plate adjacent a dovetail of the turbine blade.

Turbine blades having shank features and methods of fabricating the same

A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a first protrusion located adjacent to the tip end and a second protrusion located radially inward from the first protrusion.

Turbine blade having a tip shroud

Turbine blades having damper pin slot features and methods of fabricating the same

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a downstream cover plate and a downstream angel wing that extends axially from the downstream cover plate. A portion of the downstream cover plate radially outward of the downstream angel wing defines an approximately linear profile. The turbine blade also includes a dovetail region that extends radially inwardly from the shank. A profile of a portion of the downstream cover plate radially inward of the downstream angel wing is recessed relative to the linear profile.

Turbine blades having shank features

A turbine blade includes an airfoil that extends from a root end to a tip end, and a tip shroud extending from the tip end. The tip shroud includes a shroud plate that includes a pressure side edge. The pressure side edge includes a primary contact surface configured to couple against an adjacent tip shroud, and a notch extending at least partially downstream from the primary contact surface.

Turbine blade having a tip shroud notch

The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

Cooling passage for gas turbine system rotor blade

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Woodruff, SC, United States of America

Melbourne James Myers