General Electric Company

Steven Eric Tomberg

Jennifer B Michenfelder

Michael James Dutka

Stephen Paul Wassynger

Carl Gerard Schott

John David Stampfli

Paul Griffin DeIvernois

Christopher Edward LaMaster

David Samuel Pesetsky

Steven Mark Schirle

Josef Scott Cummins

John Franklin Ryman

Nathan Stafford Race

Peter Gaines Cleveland

Nick Martin

Ronald Stuart Denmark

Venkata Siva Chaluvadi

William John Miller

Hani Ikram Noshi

Marvin Luther Neeley

Christopher David McGowan

Timothy Edward DeJoris

Venkata Siva P Chaluvadi

Roger Claude Beharrysingh

Adrian Mircea Mistreanu

Jeffrey Boyd

Jason Thomas Harrell

A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.

Turbine blade retention system and method

A method enables a stator assembly for a turbine engine to be assembled. The method comprises forming a recess within a portion of each base, and coupling the stator vanes within the turbine engine in a circumferentially-spaced arrangement such that the recessed portion of each base facilitates reducing excitation responses of each of the plurality of stator vanes during engine operation.

Methods and apparatus for controlling contact within stator assemblies

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Airfoil shape for a compressor

Eleventh stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.

Stator blade airfoil profile for a compressor

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S&#x2013;16S, 1R&#x2013;17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Air foil shape for a compressor blade

First, second and third sets of cooling holes are provided in a turbine airfoil. The first set of holes adjacent a leading edge have turbulators commencing at a predetermined distance from the root of the airfoil and terminating short of the airfoil tip. A second set of cooling holes have turbulators commencing at a greater distance from the platform than the turbulators of the first set and terminating short of the airfoil tip at a greater distance from the tip than the turbulators of the first set of holes. A third set of holes adjacent the trailing edge has smooth bores. The size, location, style and configuration of the cooling holes increases bulk creep part life and overall efficiency of the turbine.

Turbine bucket airfoil cooling hole location, style and configuration

A turbine bucket includes an airfoil having a tip shroud, a shank and an entry dovetail; a tip shroud seal projecting radially outwardly from the tip shroud and extending continuously between end edges of the tip shroud in a direction of rotation of the airfoil about a turbine axis; a cutter tooth carried by the tip shroud seal for enlarging a groove in an opposing fixed shroud, the cutter tooth having a center point located with reference to X, Y and Z axes, where the X-axis extends axially in an exhaust flow direction; the Y-axis extends in a direction of rotation of the turbine bucket; and the Z-axis extends radially through the intersection of the X and Y axes; wherein the center point is located about &#xbd; inch along the Y-axis from the X=0 position, and wherein the Z-axis is located 0.517 inches from an outside edge of a seal pin extending along said entry dovetail, as measured in a direction normal to the shank of the bucket.

Center-located cutter teeth on shrouded turbine blades

A turbine bucket airfoil has a conical fillet about the intersection of the airfoil tip and tip shroud having a nominal profile in accordance with coordinate values of X and Y, offset, offsetand Rho set forth in Table I. The shape parameters of offset, offsetand Rho define the configuration of the fillet at the specified X and Y locations about the fillet to provide a fillet configuration accommodating high localized stresses. The fillet shape may be parabolic, elliptical or hyperbolic as a function of the value of the shape parameter ratio ofat each X, Y location where Dl is a distance between an intermediate point along a chord between edge points determined by offsets Oand Oand a shoulder point on the fillet surface and D2 is a distance between the shoulder point and an apex location at the intersection of the airfoil tip and tip shroud.

Conical tip shroud fillet for a turbine bucket

A turbine bucket includes a bucket airfoil having a tip shroud with leading and trailing edges defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y at points 1-7 and 8-15, respectively, set forth in Table I. The X and Y values are distances in inches which, when respective points 1-7 and 8-15 are connected by smooth, continuing arcs, define the leading and trailing edge tip shroud profiles. An airfoil profile at 92% span is defined by Cartesian coordinate values of X, Y and Z in Table II having the same X, Y origin along the radial Z-axis as the origin of Table I. The profiled leading and trailing edges of the tip shroud relative to the airfoil profile afford optimum tip shroud mass distribution which maximizes creep life of the bucket. Stage efficiency is also improved by providing a tip shroud covering the airfoil throat.

Turbine bucket tip shroud edge profile

Second stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1 wherein X and Y values are in inches and the Z values are non-dimensional values from 0.088 to 0.92 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. 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 bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of &plusmn;0.160 inches in directions normal to the surface of the airfoil.

Growing community of inventors

Simpsonville, SC, United States of America

Steven Eric Tomberg