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Edward F Pietraszkiewicz

from Southington, CT
Age ~74
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Also known as:
Edwards F Pietraszkiewicz, Ed F Pietraszkiewicz, Edward F Pietraszkiewi, Edward F Pietraszkiew, Alexandra Pietraszkiewicz, Anna Pietraszkiewicz, Pietraszkiewicz Edward Edwa
Phone and address:
1094 Pleasant St, Southington, CT 06489
(860) 621-6628
Connected to:
Aaron E Pietras, 54Agnieszka B Pietrasik, 78Alexandra M Pietras, 34Barbara A Pietraszkiewicz, 61Christine L Pietras, 71Daniel J Pietraszek, 87Denise A Pietras, 60Dennis F Pietras, 70Derek R Pietras, 35Dolores S Pietraszewski, 92

Edward Pietraszkiewicz Phones & Addresses

  • 1094 Pleasant St, Southington, CT 06489 (860) 621-6628
  • Plantsville, CT
  • 5223 Center St, Jupiter, FL 33458
  • Maineville, OH
  • Shelton, CT
  • Cincinnati, OH
  • Palm Beach Gardens, FL

Work

Company: Parametric solutions, inc. Jun 2016 Position: Chief engineer - turbine airfoils durability

Education

Degree: Master of Science, Masters School / High School: Rensselaer Polytechnic Institute - the Lally School of Management Specialities: Business Administration, Management, Business Administration and Management

Skills

Aerospace • Engineering Management • Manufacturing • Engineering • Root Cause Analysis • Systems Engineering • Mechanical Engineering • Continuous Improvement • Finite Element Analysis • Machining • Aerospace Engineering • Turbines • Six Sigma • Lean Manufacturing • Earned Value Management • Propulsion • Pro Engineer • Ptc Creo • Airfoil Heat Transfer • Catia

Emails

e***[email protected]

Industries

Aviation & Aerospace

Resumes

Resumes

Edward Pietraszkiewicz Photo 1

Edward Pietraszkiewicz

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Location:
Hartford, CT
Industry:
Aviation & Aerospace
Work:
Parametric Solutions, Inc.
Chief Engineer - Turbine Airfoils Durability
Pratt & Whitney 1995 - Dec 2015
Principal Engineer - Turbine Airfoils Durability
Ge 1990 - 1995
Lead Engineer - Ge90 Turbine Aero Thermal
Education:
Rensselaer Polytechnic Institute - the Lally School of Management
Master of Science, Masters, Business Administration, Management, Business Administration and Management Worcester Polytechnic Institute
Bachelors, Bachelor of Science, Mechanical Engineering Rensselaer Polytechnic Institute at Hartford
Master of Science, Masters, Business Administration, Management, Business Administration and Management
Skills:
Aerospace
Engineering Management
Manufacturing
Engineering
Root Cause Analysis
Systems Engineering
Mechanical Engineering
Continuous Improvement
Finite Element Analysis
Machining
Aerospace Engineering
Turbines
Six Sigma
Lean Manufacturing
Earned Value Management
Propulsion
Pro Engineer
Ptc Creo
Airfoil Heat Transfer
Catia

Business Records

Name / Title
Company / Classification
Phones & Addresses
Edward Pietraszkiewicz
President, Director
EPCO ENTERPRISES, INC
5223 Ctr St, Jupiter, FL

Publications

Us Patents

Hole-Drilling Guide And Method

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US Patent:
6844518, Jan 18, 2005
Filed:
Dec 22, 2003
Appl. No.:
10/743517
Inventors:
Todd Coons - Casa Grande AZ, US
Edward Pietraszkiewicz - Southington CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B23H 104
B23H 726
B23H 910
B23H 914
US Classification:
219 6915, 219 6911
Abstract:
A hole-drilling guide for directing a flexible hole-drilling instrument includes; a body made of an electrically insulating material, at least one inlet aperture penetrating a face of the body, at least one exit aperture penetrating a face of the body and a hollow, nonlinear raceway linking the inlet and exit apertures.

Airfoil With Three-Pass Serpentine Cooling Channel And Microcircuit

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US Patent:
7131818, Nov 7, 2006
Filed:
Nov 2, 2004
Appl. No.:
10/979597
Inventors:
Frank J. Cunha - Avon CT, US
Bret Teller - Meriden CT, US
Young Chon - Manchester CT, US
Dominic Mongillo - West Hartford CT, US
Edward F. Pietraszkiewicz - Southington CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/16
US Classification:
416 97R, 415115
Abstract:
An airfoil, and in a disclosed embodiment a rotor blade, has a serpentine cooling path. To best account for the Coriolis effect, the paths of the serpentine cooling channel have trapezoidal cross-sections. An area of the rotor blade between a smaller side of the trapezoidal-shaped paths, and a facing wall of the rotor blade has high thermal and mechanical stresses, and is a challenge to adequately cool. A microcircuit, which is a very thin cooling circuit having crossing pedestals, is embedded into the blade in this area. The microcircuit provides additional cooling, and addresses the challenges with regard to cooling these areas.

Turbine Airfoil Cooling Passageway

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US Patent:
7150601, Dec 19, 2006
Filed:
Dec 23, 2004
Appl. No.:
11/021152
Inventors:
Edward F. Pietraszkiewicz - Southington CT, US
John C. Calderbank - Glastonbury CT, US
Andrew D. Milliken - Middletown CT, US
Jeffrey R. Levine - Wallingford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97R, 415115
Abstract:
An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first leg extending from the inlet inboard through the airfoil to the first turn, and a second leg extending from the first turn. A dividing wall is in the passageway and has an upstream end in an outboard half of a span of the airfoil and has a plurality of vents. The vane may be formed as a reengineering of a baseline configuration lacking the dividing wall.

Cooled Rotor Blade

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US Patent:
7195448, Mar 27, 2007
Filed:
May 27, 2004
Appl. No.:
10/855188
Inventors:
Jeffrey R. Levine - Wallingford CT, US
Edward Pietraszkiewicz - Southington CT, US
John Calderbank - Glastonbury CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
415115, 416 96 R, 416 97 R
Abstract:
A rotor blade is provided that includes a root, a hollow airfoil, and a conduit disposed within the root. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a first radial passage, a second radial passage, a rib disposed between and separating the first radial passage and second radial passage, a plurality of crossover apertures disposed within the rib, and a plurality of trip strips disposed within the second radial passage. The trip strips are attached to an interior surface of one or both of the pressure side wall and the suction side wall. The trip strips are disposed within the first radial passage at an angle α that is skewed relative to a cooling airflow direction within the first radial passage, and positioned such that each of the plurality of trip strips converges toward the rib. The rib end of at least a portion of the plurality of trip strips is located between a pair of adjacent crossover apertures.

Heat Transferring Cooling Features For An Airfoil

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US Patent:
7217095, May 15, 2007
Filed:
Nov 9, 2004
Appl. No.:
10/984216
Inventors:
Edward F. Pietraszkiewicz - Southington CT, US
Christina Botnick - Stafford Springs CT, US
Todd Coons - Gilbert AZ, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97R
Abstract:
A turbine blade airfoil assembly includes a cooling air passage. The cooling air passage includes a plurality of impingement openings that are isolated from at least one adjacent impingement opening. The cooling air passage is formed and cast within a turbine blade assembly through the use of a single core. The single core forms the features required to fabricate the various separate and isolated impingement openings. The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.

Impingement Cooling Of Large Fillet Of An Airfoil

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US Patent:
7220103, May 22, 2007
Filed:
Oct 18, 2004
Appl. No.:
10/967557
Inventors:
Frank J. Cunha - Avon CT, US
Jason E. Albert - West Hartford CT, US
Edward F. Pietraszkiewicz - Southington CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97R, 416193 A
Abstract:
A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which, together with an impingement rib, defines a fillet cavity therebetween, and cooling air is provided to flow through impingement holes in the impingement rib and impinge on the rear surface of the fillet. The impingement holes are elongated in cross sectional shape with their elongations being orient in a direction generally transverse to a radial direction.

Dirt Separator For Gas Turbine Air Supply

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US Patent:
7284953, Oct 23, 2007
Filed:
Aug 29, 2005
Appl. No.:
11/214238
Inventors:
Richard Silverman - Tolland CT, US
Barry Beckwith - Coventry CT, US
Lisa O'Neill - Manchester CT, US
Edward F. Pietraszkiewicz - Southington CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F04D 29/70
US Classification:
4151212, 60 39092
Abstract:
A gas turbine engine is provided with a radially outer cooling air flow. A dirt separator is placed in the path of the radially outer cooling air flow, and includes a radially outer leg that defines a space to capture dirt or other impurities. A radially inner leg of the dirt separator includes open air flow passages to allow air to flow through the inner leg and downstream to cool various components within the gas turbine engine.

Manufacturable And Inspectable Microcircuits

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US Patent:
7311497, Dec 25, 2007
Filed:
Aug 31, 2005
Appl. No.:
11/217703
Inventors:
Om Parkash Sharma - South Windsor CT, US
Frank Cunha - Avon CT, US
Edward F. Pietraszkiewicz - Southington CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97A, 416232, 29889721, 298897
Abstract:
A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.
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Edward F Pietraszkiewicz from Southington, CT, age ~74 Get Report