General Electric Company

James Stewart Phillips

Gregory Thomas Foster

David Richard Johns

Robert Walter Coign

Thomas Robbins Tipton

Frederic Woodrow Roberts, Jr

Edward Lee McGrath

Aaron Gregory Winn

Randall Gill

Ravichandran Meenakshisundaram

Niranjan Gokuldas Pai

Gerald Kent Blow

Michael John Brown

Raymond Allan Wedlake

Robert Carl Meyer

Ariel Harter Lomas

Jennifer Ann Morrow

Frederic Woodrow Roberts

The present invention is a coated article containing at least two adjacent cooling holes that are substantially uncoated. In an embodiment, the coated article includes a base material, an outer surface and a coating on a portion of the outer surface. Here, the adjacent cooling holes are arranged along an axis on the outer surface and extend within the base material at an angle to the outer surface. The coating may include at least one unfinished edge oriented substantially parallel to the axis and set off at an oblique angle and a distance from the adjacent cooling holes.

Coated article

The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.

Turbine nozzle cooling assembly

A hot gas path measurement apparatus is provided and includes a substrate having a coating applied on a surface thereof such that the coating is interposed between the substrate and a hot gas path; and a measurement device fixed in a recess formed in the substrate, the measurement device including a sensor, and a holder configured to position the sensor in an alignment condition with a plane of a surface of the coating or at least partially within a span of the hot gas path.

Hot gas path measurement

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 cooling system for the nozzle edges includes a chamber containing a cooling medium. First and second elongated plenums are disposed along opposite side edges of each platform. Inlet passages communicate cooling medium from the chamber into each plenum. Outlet passages from each plenum terminate in outlet holes in the side edges of the platform to cool the gap between adjacent nozzle segments. Passageways communicate with each plenum and terminate in film cooling holes to film cool platform surfaces. In each plenum, the inlet passages are not in direct line-of-sight flow communication with the outlet passages and passageways.

Cooling system for nozzle segment platform edges

Growing community of inventors

Easley, SC, United States of America

James Stewart Phillips