General Electric Company

Calvin Levy Sims

Susan Marie Hyde

Robert Romany By

Jon Conrad Schaeffer

William Scott Zemitis

Melbourne James Myers

Richard Ryan Pilson

John Zhiqiang Wang

Gary Michael Itzel

Abdul-Azeez Mohammed-Fakir

Keith Cletus Belsom

Iain Robertson Kellock

Charles E Steber

Judd Dodge Tressler

Ariel Caesar Prepena Jacala

Doyle Clyde Lewis

Daniel Robert Tegel

Henry Joe Wiersma

Michael Ernest Boisclair

Jon Conrad Scaeffer

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

Turbine blades having damper pin slot features

Turbine blades having damper pin slot features and methods of fabricating the same

Methods and apparatus for cooling rotor blades of a gas turbine are provided. The turbine blade has an airfoil connected to the platform and a dovetail extending from the platform. A main cooling circuit extends through the dovetail and into the airfoil. The main cooling circuit includes an exit for main cooling flow from the airfoil to exit out through the dovetail. In one aspect, the method includes the steps of extracting a portion of the coolant flowing through the main cooling circuit into a platform cooling circuit. After cooling a portion of the platform, the platform cooling flow splits with one portion of the flow rejoining the main cooling circuit and is used to cool the airfoil. The rest of the platform cooling flow continues to cool the platform and then returns to the main cooling circuit to flow through the exit.

Methods and apparatus for cooling gas turbine rotor blades

Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 0.938 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 &#xb1;0.150 inches in directions normal to the surface of the airfoil.

Airfoil shape for a turbine bucket

Fourth stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 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 envelope of &#xb1;0.150 inches in directions normal to the surface of the airfoil.

A damper pin for a bucket damper slot in a turbine includes slot insertion ends shaped to fit into the bucket damper slot, and at least a first scallop section formed or machined between the slot insertion ends and shaped to receive a bucket shank pocket radial contour at bucket Hi-C. A second scallop section may also be formed or machined diametrically opposed and anti-symmetrical to the first scallop section between the slot insertion ends.

Turbine bucket damper pin

The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X and Y values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket. The second-stage wheel has sixty buckets.

Second-stage turbine bucket airfoil

In a combustor having an axis, a flow sleeve and a liner, a plurality of circumferentially spaced supports interconnect the upstream ends of the liner and flow sleeve to limit wear on the supports and accommodate relative thermal expansion of the liner and flow sleeve. Each support includes a flow sleeve stop having an angled surface, a groove and a female threaded aperture and a liner stop having a complementary angled surface, a rib and an enlarged opening. By inserting the liner axially through the open upstream end of the flow sleeve, the rib of the liner stop engages the slot of the flow sleeve stop. By passing a bolt having a spring through the enlarged opening of the liner stop and threading the bolt to the flow sleeve stop, the liner is biased for axial downstream movement to maintain the complementary inclined surfaces of the stops in contact with one another, thereby limiting wear and accommodating relative thermal expansion of the flow sleeve and liner.

Supports for connecting a flow sleeve and a liner in a gas turbine combustor

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Mauldin, SC, United States of America

Calvin Levy Sims