General Electric Company

General Electric Technology Gmbh

Martin James Jasper

Jan Emeric Agudo

William Scott Zemitis

Melbourne James Myers

Srikanth Chandrudu Kottilingam

Neelesh Nandkumar Sarawate

Surinder Singh Pabla

Craig Allen Bielek

John Wesley Harris, Jr

Bradley Taylor Boyer

Brad Wilson Vantassel

Richard Ryan Pilson

Thomas James Brunt

Ajay Gangadhar Patil

Christopher William Kester

Charles Wesley Wells

Brad Van Tassel

Claire Katherine Naioti

Stephen Douglas Shearer

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 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 system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.

System for addressing turbine blade tip rail wear in rubbing and cooling

Rotor blades and turbomachines are provided. The rotor blade includes a main body having a shank, an airfoil extending radially outwardly from the shank, and a platform. The main body further includes a pressure-side slash face and a suction-side slash face. Each of the pressure-side slash face and the suction-side slash face includes a damper land and defines a slot. The damper land is disposed radially inward from the slot.

Rotor blade damping structures

The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface.

Cooling circuit for a turbomachine component

The present application provides a turbine rotor blade including an airfoil shape and a trailing edge 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, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., 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 rotor blade airfoil profile

A turbine nozzle segment includes a radially-inner endwall, a radially-outer endwall, and a pair of airfoil-shaped vanes extending between the radially-inner endwall and the radially-outer endwall. The back face of the radially-inner endwall and/or the back face of the radially-outer endwall has a pocket formed therein in an area between the pressure sidewall of the first vane and the suction sidewall of the second vane to enhance stiffness distribution between the second vane and the radially-inner endwall and/or radially-outer endwall.

Turbine nozzle with stress-relieving pocket

Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.

Alignment apparatus for coupling diaphragms of turbines

The present application provides a nozzle for a gas turbine engine. The nozzle may include a band, a seal slot positioned within the band, an airfoil extending from the band, a cavity within the airfoil, and an embossment positioned about the band and the cavity.

Growing community of inventors

Simpsonville, SC, United States of America

Martin James Jasper