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Calvin W Sims

from Federal Way, WA
Age ~63
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Also known as:
Calvin Wayne Sims, Calvin Davis
Related to:
Michael Alan Davis, 72Alta DavisSimone Davis, 35Margaret Hammett, 70Gabriell SimsKeisha Rucker
Connected to:
Abdul Sims, 50Adriel Sims, 32Alfreda Sims, 57Alisha Sims, 42Allen Sims, 35Amaya T Sims, 34Amie E Sims, 48Amira Sims, 51Anastatia E Sims, 89Angela K Sims, 64

Calvin Sims Phones & Addresses

  • Federal Way, WA
  • Tacoma, WA
  • Spartanburg, SC
  • Canton, GA
  • Acworth, GA
  • Lithonia, GA
  • 6116 29Th St NE, Tacoma, WA 98422 (253) 952-2815

Work

Company: United forming - Austell, GA Sep 2010 Position: Lead crewman

Education

School / High School: southside high school- Atlanta, GA 1985

Skills

4000 hours in uphosltery

Resumes

Resumes

Calvin Sims Photo 1

Calvin Sims Atlanta, GA

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Work:
United Forming
Austell, GA
Sep 2010 to Jul 2012
lead crewman
dependable auto shipper
Morrow, GA
2007 to Nov 2011
lead supervisor
Dennis Taylor
Duluth, MN
Apr 2008 to Feb 2010
labor
Enterprise Rental Car
Conyers, GA
Oct 2006 to 2007
Driver
United forming company
Austell, GA
Jan 2005 to Oct 2006
Laborer
Georgia world congress center
Atlanta, GA
Oct 2001 to Mar 2004
Set-up Operator
Skills:
4000 hours in uphosltery

Publications

Us Patents

Second-Stage Turbine Bucket Airfoil

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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.

Turbine Bucket Damper Pin

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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.

Methods And Apparatus For Cooling Gas Turbine Rotor Blades

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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.

Frozen Confection

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US Patent:
D2565129, Aug 26, 1980
Filed:
Aug 3, 1978
Appl. No.:
5/930732
Inventors:
Calvin E. Sims - Atlanta GA
International Classification:
D0101
US Classification:
D 1 18

Supports For Connecting A Flow Sleeve And A Liner In A Gas Turbine Combustor

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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.

Turbine Blades Having Damper Pin Slot Features

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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.

Turbine Blades Having Damper Pin Slot Features And Methods Of Fabricating The Same

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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.
Control profile
Calvin W Sims from Federal Way, WA, age ~63 Get Report