General Electric Company

Thomas James Brunt

Alexander Stein

Victor John Morgan

Benjamin Paul Lacy

Hua Zhang

Gregory Thomas Foster

William Scott Zemitis

John Wesley Harris, Jr

Jeffrey Clarence Jones

Robert Walter Coign

Ibrahim Sezer

Adam John Fredmonski

Jason Anton Byers

Martin James Jasper

Richard William Johnson

Glen Arthur MacMillan

George Andrew Gergely

Jason Ray Gregg

Joe Timothy Brown

Brad Van Tassel

Stein Alexander

A rotary machine includes a rotatable member and a casing extending circumferentially over the rotatable member. The casing includes first and second target impingement surfaces. The cooling system includes first and second impingement plates. The first impingement plate is positioned over the first target impingement surface and at least a portion of the second target impingement surface. The first impingement plate defines a plurality of first impingement holes configured to channel a first flow of cooling fluid toward the first target impingement surface. The second impingement plate is positioned over the second target impingement surface. The second impingement plate defines a plurality of second impingement holes configured to channel a second flow of cooling fluid toward the second target impingement surface. A thickness of the casing in the first target impingement surface is different than a thickness of the casing in the second target impingement surface.

System and method for shroud cooling in a gas turbine engine

A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The airfoil body has an inner surface facing the radially extending chamber and an outer surface, a first corrugated surface on a portion of the outer surface, and a second corrugated surface on the inner surface paralleling the first corrugated surface. The corrugated surface on the outer surface of the airfoil provides wake mixing. The blade may also include an integrally formed impingement cooling structure having a third corrugated surface parallel to the second corrugated surface, which is made possible through additive manufacturing. The impingement cooling structure so formed provides improved cooling of the blade.

Blade with parallel corrugated surfaces on inner and outer surfaces

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

A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

Gas turbine nozzle trailing edge fillet

A system for recirculating a hot gas flowing through a gas turbine generally includes a transition piece having a downstream surface, a stationary nozzle having a leading edge surface adjacent to the transition piece downstream surface, a gap defined between the transition piece downstream surface and the stationary nozzle leading edge surface, and a projection having an inner arcuate surface radially separated from an outer surface. The projection generally extends from the stationary nozzle leading edge surface towards the transition piece downstream surface and at least partially decreases the gap. A seal extends across the gap and may be in contact with the transition piece and the stationary nozzle leading edge surface. A recirculation zone may be at least partially defined between the projection inner arcuate surface, the stationary nozzle leading edge surface and the transition piece downstream surface.

System and method for recirculating a hot gas flowing through a gas turbine

A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway into which a fluid flow is receivable to flow through the pathway; and a nozzle stage at which adjacent nozzles extend across the pathway between the opposing endwalls to aerodynamically interact with the fluid flow. The adjacent nozzles are configured to define a throat distribution exhibiting endwall throat decambering and pitchline throat overcambering.

Turbine of a turbomachine

A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein 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, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Turbine nozzle airfoil profile

A turbine nozzle attachment assembly includes an outer turbine component (a shroud or a turbine shell) formed with a circumferential groove open in a forward-facing axial direction; a nozzle segment including a vane extending between inner and outer bands, the outer band provided with an upstanding annular hook formed with a hook element extending in an aft-facing axial direction and received in the circumferential groove. The upstanding annular hook and hook element are formed with a circumferentially-oriented slot. An anti-rotation block is located in the circumferentially-oriented slot, and an anti-tipping plate having a circumferential width greater than a corresponding circumferential width of the circumferentially-oriented slot substantially covers a forward face of the anti-rotation block. The anti-rotation block and the anti-tipping plate are fastened directly to the outer turbine component.

Growing community of inventors

Greenville, SC, United States of America

Thomas James Brunt