Matthew J Findlay

age ~55

from Omaha, NE

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Matthew Findlay Phones & Addresses

5809 174Th St, Omaha, NE 68135 • 402 891-7193
409 Two Gait Ln, Simpsonville, SC 29680 • 864 228-6603
Clifton Park, NY
Greenville, SC

Work

Company:

Canadian pacific railway
Jul 2012
Address:

Calgary, Canada Area
Position:

Director operations budgets

Education

Degree:

MBA
School / High School:

Carnegie Mellon University - Tepper School of Business
2001 to 2004
Specialities:

Finance, Strategy, HR

Languages

English • French

Industries

Transportation/Trucking/Railroad

Resumes

Director Operations Budgets At Canadian Pacific Railway

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Position:

Director Operations Budgets at Canadian Pacific Railway

Location:

Calgary, Alberta, Canada

Industry:

Transportation/Trucking/Railroad

Work:

Canadian Pacific Railway - Calgary, Canada Area since Jul 2012
Director Operations Budgets
Canadian Pacific Railway - Calgary, Canada Area Apr 2012 - Jul 2012
Advisor Costing and Profitability
Union Pacific Railroad Oct 2009 - Apr 2012
Manager - Cost & Profit Management
Union Pacific Railroad Apr 2008 - Sep 2009
Manager - Commercial Investments
GE Energy Oct 1998 - Nov 2004
Technical Leader

Education:

Carnegie Mellon University - Tepper School of Business 2001 - 2004
MBA, Finance, Strategy, HR The University of British Columbia 1993 - 1998
Ph.D., Mechanical Engineering University of Toronto 1990 - 1993
B.A.Sc., Engineering Science (Aerospace)

Languages:

English
French

Us Patents

Turbulator On The Underside Of A Turbine Blade Tip Turn And Related Method
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US Patent:

7137782, Nov 21, 2006
Filed:

Apr 27, 2004
Appl. No.:

10/832252
Inventors:

John Alan Eastman - Simpsonville SC, US
Matthew James Findlay - Simpsonville SC, US
Jon Allen Ebacher - Spartanburg SC, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/18
US Classification:

416 96R, 416 97 R
Abstract:

A turbine blade includes a shank portion and an airfoil portion with leading and trailing edges and a radially outer tip. An internal closed-loop cooling circuit is formed within the airfoil portion and includes at least one radial outflow passage and at least one radial inflow passage connected by at least one respective tip turn at the radially outer end of the airfoil portion. At least one tip turn is provided with a single turbulence-enhancement device on an underside of the radially outer tip, projecting into the tip turn.

Turbulator On The Underside Of A Turbine Blade Tip Turn And Related Method
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US Patent:

7544043, Jun 9, 2009
Filed:

Jul 25, 2006
Appl. No.:

11/491957
Inventors:

John Alan Eastman - Simpsonville SC, US
Matthew James Findlay - Simpsonville SC, US
Jon Allen Ebacher - Spartanburg SC, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/18
US Classification:

416 96R
Abstract:

A turbine blade includes a shank portion and an airfoil portion with leading and trailing edges and a radially outer tip. An internal closed-loop cooling circuit is formed within the airfoil portion and includes at least one radial outflow passage and at least one radial inflow passage connected by at least one respective tip turn at the radially outer end of the airfoil portion. At least one tip turn is provided with a single turbulence-enhancement device on an underside of the radially outer tip, projecting into the tip turn.

Film Cooling For The Trailing Edge Of A Steam Cooled Nozzle
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US Patent:

20050169746, Aug 4, 2005
Filed:

Feb 3, 2004
Appl. No.:

10/771195
Inventors:

Jason Fuller - Simpsonville SC, US
Gary Itzel - Simpsonville SC, US
Cathy Chiurato - Simpsonville SC, US
Matthew Findlay - Simpsonville SC, US
International Classification:

F03D011/00
US Classification:

415115000
Abstract:

A nozzle assembly () for a turbine engine includes an inner band () and an outer band () spaced apart from each other. An airfoil () installed between the bands has a leading edge () and a trailing edge (). The airfoil has cavities formed in it for fluid flow through the nozzle assembly. A plurality of film cooling holes (A-H) are formed in a sidewall of the airfoil on a concave side of the assembly, and a plurality of film cooling holes (J-R) are formed in a sidewall of the nozzle on a convex side thereof. The holes are formed on each side of the airfoil, adjacent the trailing edge of the nozzle, in a plurality of rows of holes including at least a forward row (C, J), an aft row (A, L), and an intermediate row (B, K). The spacing between the intermediate row and aft row is substantially closer than the spacing between the forward row and the intermediate row.