Calvin W Sims

US Patent:

6450770, Sep 17, 2002

Filed:

Jun 28, 2001

Appl. No.:

09/892911

Inventors:

John Zhiqiang Wang - Greenville SC
Robert Romany By - Simpsonville SC
Calvin L. Sims - Mauldin SC
Susan Marie Hyde - Piedmont SC

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 514

US Classification:

416223A, 416243, 416DIG 2

Abstract:

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.

US Patent:

6776583, Aug 17, 2004

Filed:

Feb 27, 2003

Appl. No.:

10/373757

Inventors:

John Zhiqiang Wang - Greenville SC
Jon Conrad Scaeffer - Greenville SC
Iain Robertson Kellock - Simpsonville SC
Calvin L. Sims - Mauldin SC

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 526

US Classification:

416500

Abstract:

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.

US Patent:

7513738, Apr 7, 2009

Filed:

Feb 15, 2006

Appl. No.:

11/355213

Inventors:

Gary Michael Itzel - Simpsonville SC, US
Ariel Caesar Prepena Jacala - Simpsonville SC, US
Doyle C. Lewis - Greer SC, US
Calvin Levy Sims - Mauldin SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18

US Classification:

415115, 416 96 R, 416 90 R

Abstract:

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.

US Patent:

62164422, Apr 17, 2001

Filed:

Oct 5, 1999

Appl. No.:

9/412965

Inventors:

Keith C. Belsom - Stuart SC
Calvin L. Sims - Mauldin SC
Charles E. Steber - Simpsonville SC
Daniel R. Tegel - Simpsonville SC
Henry J. Wiersma - Simpsonville SC

Assignee:

General Electric Co. - Schenectady NY

International Classification:

F02C 720
F23R 360

US Classification:

60 3932

Abstract:

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.

US Patent:

20200277864, Sep 3, 2020

Filed:

Dec 23, 2019

Appl. No.:

16/725654

Inventors:

- Schenectady NY, US
Melbourne James Myers - Woodruff SC, US
Richard Ryan Pilson - Greer SC, US
Calvin Levy Sims - Mauldin SC, US

International Classification:

F01D 5/24
F01D 5/16
F01D 5/26
F01D 5/14
F01D 5/30
F01D 25/06
B21D 53/78
F01D 5/22

Abstract:

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.

US Patent:

20180230820, Aug 16, 2018

Filed:

Feb 14, 2017

Appl. No.:

15/431950

Inventors:

- Schenectady NY, US
Melbourne James Myers - Woodruff SC, US
Richard Ryan Pilson - Greer SC, US
Calvin Levy Sims - Mauldin SC, US

International Classification:

F01D 5/22
F01D 25/06

Abstract:

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.