David E Shapiro

US Patent:

6761537, Jul 13, 2004

Filed:

Dec 19, 2002

Appl. No.:

10/325426

Inventors:

David Elliott Shapiro - Niskayuna NY
Ian Darnell Reeves - Piedmont SC

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 530

US Classification:

416220R, 416248, 416218

Abstract:

A method of assembling a turbine comprises coupling at least one bucket to a rotor wheel. The bucket includes an upstream side, a downstream side, an airfoil extending therebetween and a dovetail extending radially inwardly from the airfoil to the rotor wheel. The method further comprises fixedly securing the bucket to the rotor wheel with a locking pin that extends from the bucket upstream side through the bucket dovetail to the bucket downstream side.

US Patent:

6786699, Sep 7, 2004

Filed:

Jun 26, 2002

Appl. No.:

10/179019

Inventors:

David Elliott Shapiro - Niskayuna NY
Steven Kerry Williams - Brewer ME
Charles Byron Adams - Olamon ME
Gregory Norman Fournier - Hermon ME
Gregory Lee Landry - Glenburn ME
Maurice David Fournier - Hermon ME

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 532

US Classification:

416216, 416218, 2988921, 2988922

Abstract:

Airfoils and grooves on the rotor or carrier for the airfoils have generally complementary dovetail shapes. The airfoils are installed in the grooves by sliding the bases of the airfoils along the circumferential grooves into final circumferential positions. At each circumferential position, a pin is driven between the base of the airfoil and the bottom of the groove to displace the airfoil radially into a final radially secured position taking up the clearance necessary to enable sliding movement of the airfoils about the groove. A first tool is used to drive each pin in a generally tangential direction by hammering on the end of the tool, transmitting an axial force to the pin. When the circumferential clearance of the last installed airfoil is insufficient to permit further use of a tangentially oriented tool to install additional airfoils, a second tool having an angled head is disposed into the groove to engage the pin. By hammering on the second tool, a component of the applied force drives the pins between the airfoil bases and the bottom of the groove to finally secure the remaining airfoils in a fixed radial position.

US Patent:

20020092190, Jul 18, 2002

Filed:

Jan 16, 2001

Appl. No.:

09/760293

Inventors:

Douglas Hofer - Clifton Park NY, US
Nicholas Mollo - Clifton Park NY, US
Alan Maddaus - Rexford NY, US
David Shapiro - Pittsburgh PA, US
Maurice Fournier - Hermon ME, US

International Classification:

G01B003/42

US Classification:

033/501450, 033/783000, 033/530000

Abstract:

Apparatus for measuring the trailing edge thickness of an airfoil in a turbine includes a plurality of tools; each tool having a main body portion and a forward end; an opening along a side edge and in proximity to a forward edge of the forward end, the opening including a slot of predetermined width adapted to engage the trailing edge of the airfoil; wherein each of the tools has a different predetermined slot width. A method for determining the trailing edge thickness of an airfoil in a turbine includes the steps of: a) providing a tool having an opening including a slot having a predetermined width, the opening adapted to receive the trailing edge of the airfoil; b) aligning the tool to receive the trailing edge of the airfoil in the opening; c) determining if a match exists between the trailing edge and the slot width; d) if no match, repeating steps a) through c) with a tool having a different predetermined slot width until a match is found; and e) recording the size of the tool, as identified by the predetermined slot width, as the actual trailing edge thickness of the airfoil.