General Electric Company

Randall Gill

Robert Walter Coign

Curtis John Jacks

Herbert Chidsey Roberts

Glenn Curtis Taxacher

Craig Allen Bielek

James Stewart Phillips

Margaret Jones Schotsch

Peter Galen Stevens

Raymond Allan Wedlake

John R Seymour

David Leo

Allison Ozarslan

A shroud dampening pin is disclosed including a shaft, a dampening portion at a first end of the shaft, and a cap at a second end of the shaft. The dampening portion includes a bevel having a bevel angle and a contact surface. A turbine shroud assembly is disclosed, including an inner shroud, an outer shroud, the shroud dampening pin, and a biasing apparatus. The outer shroud includes a channel extending from an aperture adjacent to the inner shroud at a channel angle from the aperture. The shroud dampening pin is disposed within the channel. The dampening portion extends through the aperture with the contact surface contacting the inner shroud. The biasing apparatus contacts the cap and provides a biasing force to the inner shroud through the contact surface. The bevel angle is about the same as the channel angle, and the contact surface is about parallel to the aperture.

Shroud dampening pin and turbine shroud assembly

The present disclosure is directed to a nozzle for a turbomachine. The nozzle includes an inner side wall, an outer side wall radially spaced apart from the inner side wall, and an airfoil extending radially from the inner side wall to the outer side wall. The airfoil defines a cavity that extends radially through the nozzle. The cavity is at least partially defined by a cavity wall. The cavity wall at least partially defines a pocket in fluid communication with the cavity. A cooling passage is defined by one of the inner side wall or the outer side wall. The cooling passage is in fluid communication with the cavity via the pocket.

Cooling pocket for turbomachine nozzle

A nozzle in which an airfoil includes a pressure surface and a suction surface that join at substantially opposing chordal ends of the airfoil to form a leading edge of the airfoil and a trailing edge of the airfoil. A trailing edge passage is defined through the airfoil through which coolant flows. The trailing edge passage is proximate to the trailing edge of the airfoil and has a contoured shape that conforms to that of the trailing edge.

Airfoil for nozzle and a method of forming the machined contoured passage therein

The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.

Turbine nozzle trailing edge cooling configuration

A turbine nozzle includes airfoil and sidewall surfaces. The airfoil and sidewall surfaces have profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Tables I&#x2013;IV for the pressure and suction sides of the airfoil, and the outer and inner sidewall surfaces, respectively. The X, Y and Z values are distances in inches. The X and Y values for the airfoil, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The X, Y and Z values of Tables III and IV define the outer and inner sidewall surfaces, respectively, of the gas flowpath.

Airfoil shape and sidewall flowpath surfaces for a turbine nozzle

The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of &plusmn;0.160 inches.

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Greenville, SC, United States of America

Randall Gill