General Electric Company

Benjamin Arnette Lagrange

Edward Lee McGrath

Anthony Aaron Chiurato

Timothy Brian Lloyd

Robert Alan Brittingham

Craig Allen Bielek

Stephen Paul Wassynger

Robert Walter Coign

Kevin Lee Worley

James Bernard Fehlberg

Jeff Brian Thompson

A turbine bucket and wheelpost assembly reduces the number of buckets in the third stage of the turbine from ninety-two to ninety while reducing stresses at the assembly points of the buckets and wheelposts. The buckets and wheelposts are formed with complementary fillets and tangs that provide for the insertion of the bucket into the broach slot between two wheelposts. The angles of the fillets on both the bucket and wheelpost range from 50&#xb0; to 59&#xb0;. The upper surface of the wheelpost is scalloped to reduce weight and the tangs and fillets of both the bucket and wheelpost are formed from curved and straight surfaces to reduce stresses on the assembly.

Advanced firtree and broach slot forms for turbine stage 3 buckets and rotor wheels

A turbine bucket and wheelpost assembly reduces the number of buckets in at least one of the stages of the turbine from 92 to 60 while reducing stresses at the assembly points of the buckets and wheelposts. The buckets and wheelposts being formed with complementary fillets and tangs that provide for the insertion of the bucket into the broach slot between two wheelposts. The angles of the tang surfaces on both the bucket and wheelpost range from 50&#xb0; to 57&#xb0;. The upper surface of the wheelpost is scalloped to reduce weight and the tangs and fillets of both the bucket and wheelpost are formed from curved and straight surfaces to reduce stresses on the assembly.

Advanced firtree and broach slot forms for turbine stage 1 and 2 buckets and rotor wheels

An airfoil for a gas turbine includes a leading edge, a trailing edge a tip plate, a first sidewall extending in radial span between an airfoil root and the tip plate, and a second sidewall connected to the first sidewall at the leading edge and the trailing edges, to define a cooling cavity therein. The sidewall extends in radial span between the airfoil root and the tip plate. The airfoil also includes a plurality of longitudinally spaced apart trailing edge cooling slots arranged in a column extending through the first sidewall. The slots are in flow communication with the cooling cavity and arranged in a non-uniform distribution along the trailing edge so that the number of slots in at least one portion of the trailing edge is greater than a different portion of the trailing edge.

Method and apparatus for cooling gas turbine rotor blades

A turbine bucket comprising an airfoil portion, a shank portion and a dovetail mounting portion; an internal cooling circuit including inlet passages in the shank portion and the dovetail mounting portion connected to a cooling circuit in the airfoil portion, the inlet passages including a primary inlet passage on one side of a radial centerline of the bucket, and a secondary inlet cavity on an opposite side of the radial centerline; and a purge passage connecting the secondary inlet passage to the primary inlet passage.

Turbine bucket cooling passages and internal core for producing the passages

A damper pin is disposed between adjacent buckets of a turbine rotor. A first bucket has circumferentially extending supports defining a pair of axially spaced surfaces on which a damper pin rests in a cold condition of the turbine. The adjacent bucket is undercut adjacent its platform to provide an angled surface overlying a generally correspondingly angled surface of the damper pin. The damper pin fits slightly loose within the recess and, upon turbine rotation at speed, the angled surfaces of the damper pin and recess cooperate to bias the damper pin against the first bucket whereby the damper pin engages both buckets and dissipates vibratory action.

Vibration damper assembly for the buckets of a turbine

Second 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, Y and Z 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.

Airfoil shape for a turbine bucket

Second stage turbine buckets have internal core 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 bucket in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of &plusmn;0.039 inches in directions normal to any internal core surface location.

Internal core profile for a turbine bucket

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 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, Y and Z 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;0.060 inches in directions normal to the surface of the airfoil.

Growing community of inventors

Simpsonville, SC, United States of America

Benjamin Arnette Lagrange