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Matthew S Gleiner

from Redondo Beach, CA
Age ~41
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Also known as:
Matthew Steven Gleiner, Matthew S Gleavey, Matthew Gliener
Phone and address:
2402 Graham Ave #B, Redondo Beach, CA 90278
Related to:
Michael W Wilson, 63
Connected to:
Andrea M Gleis, 32Eric I Gleiser, 30Marcelo C Gleiser, 30Christen M Gleisinger, 40Scott F Gleisle, 52Daniel L Gleisner, 33Greta Gleissner, 50Jane A Gleissner, 31Jesse R Gleissner, 33Paul T Gleissner, 63

Matthew Gleiner Phones & Addresses

  • 2402 Graham Ave #B, Redondo Beach, CA 90278
  • Hawthorne, CA
  • Norwalk, CT
  • 39 Overbrook Dr, Vernon Rockville, CT 06066
  • Vernon, CT
  • Potsdam, NY
  • Stowe, VT
  • Kaibeto, AZ
  • 6 Rudolf Ln, Norwalk, CT 06851

Work

Company: Pratt & whitney Mar 2015 Position: Production transition engineer

Education

School / High School: UNIVERSITY OF CONNECTICUT- Storrs, CT Aug 2011 Specialities: MASTER OF ENGINEERING in MECHANICAL ENGINEERING

Resumes

Resumes

Matthew Gleiner Photo 1

Matthew Gleiner Norwalk, CT

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Work:
PRATT & WHITNEY

Mar 2015 to 2000
PRODUCTION TRANSITION ENGINEER
PRATT & WHITNEY

Apr 2008 to Mar 2015
SENIOR MECHANICAL ENGINEER
PRATT & WHITNEY

Jul 2006 to Apr 2008
MECHANICAL ENGINEER
PRATT & WHITNEY

Jun 2005 to Jul 2006
ASSOCIATE MECHANICAL ENGINEER
PRATT & WHITNEY

Jan 2004 to Aug 2004
DESIGN ENGINEERING CO-OP
Education:
UNIVERSITY OF CONNECTICUT
Storrs, CT
Aug 2011
MASTER OF ENGINEERING in MECHANICAL ENGINEERING
CLARKSON UNIVERSITY
Potsdam, NY
May 2005
BACHELOR OF SCIENCE in MECHANICAL ENGINEERING

Publications

Us Patents

Ceramic Core Tapered Trip Strips

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US Patent:
8353329, Jan 15, 2013
Filed:
May 24, 2010
Appl. No.:
12/786066
Inventors:
Matthew S. Gleiner - Vernon CT, US
Matthew A. Devore - Cromwell CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B22C 9/10
US Classification:
164369, 164516
Abstract:
A core for creating an airfoil has a ceramic material that forms a body. The body has an outer dimension, a slot extending through the outer dimension and into the body for receiving an insert, the slot disposed at an angle to the outer dimension, and a trip strip having a first portion disposed in the outer dimension. The first portion is in register with the slot wherein a constant dimension such as minimum thickness is maintained between the trip strip and the slot along a length of the slot and wherein said first portion tapers towards said outer dimension.

Turbine Airfoil Platform Cooling Core

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US Patent:
8356978, Jan 22, 2013
Filed:
Nov 23, 2009
Appl. No.:
12/623666
Inventors:
Jeffrey S. Beattie - South Glastonbury CT, US
Matthew A. Devore - Manchester CT, US
Matthew S. Gleiner - Vernon CT, US
Douglas C. Jenne - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/00
US Classification:
416193A, 415115, 416 97 R
Abstract:
A gas turbine engine component has a platform and an airfoil extending from the platform. The platform has a pressure side and a suction side. A cooling passage is formed within the platform, and extends along a pressure side of the platform. Air leaves the passage through an air outlet on a suction side of the platform.

Serpentine Cored Airfoil With Body Microcircuits

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US Patent:
8511994, Aug 20, 2013
Filed:
Nov 23, 2009
Appl. No.:
12/623703
Inventors:
Matthew A. Devore - Manchester CT, US
Matthew S. Gleiner - Vernon CT, US
Douglas C. Jenne - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97R
Abstract:
A gas turbine engine component has an airfoil that extends from a leading edge to a trailing edge, and a suction side and has a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage extending from the root toward the tip and adjacent the leading edge. A serpentine passage has at least three connected paths and is spaced from the straight passage toward the trailing edge. A cooling circuit is provided between the pressure wall and each of the three serpentine paths, and the straight path. A cooling circuit is provided between the suction wall and the straight passage. There is no cooling between at least a downstream one of the at least three paths of the serpentine passage and the suction wall.

Dead Ended Bulbed Rib Geometry For A Gas Turbine Engine

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US Patent:
8562286, Oct 22, 2013
Filed:
Apr 6, 2010
Appl. No.:
12/754704
Inventors:
Matthew S. Gleiner - Vernon CT, US
Douglas C. Jenne - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
415115, 416 96 R
Abstract:
A component within a gas turbine engine includes a dead ended rib which at least partially defines an internal cooling circuit flow path, the dead ended rib defines a bulbed rib profile.

Anti-Rotation Slot For Turbine Vane

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US Patent:
20110243722, Oct 6, 2011
Filed:
Mar 30, 2010
Appl. No.:
12/749971
Inventors:
Richard M. Murphy - East Hampton CT, US
Matthew S. Gleiner - Vernon CT, US
International Classification:
F01D 9/02
B23P 15/02
US Classification:
4152081, 298897
Abstract:
A fixed vane section for a gas turbine engine includes an anti-rotation slot that receives a pin for maintaining a desired position while providing for movement encountered during operation. The example anti-rotation slot includes a compound radius on inner surfaces to reduce stresses encountered during operation.

Turbine Airfoil With Body Microcircuits Terminating In Platform

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US Patent:
20110274559, Nov 10, 2011
Filed:
May 6, 2010
Appl. No.:
12/774771
Inventors:
Douglas C. Jenne - West Hartford CT, US
Matthew S. Gleiner - Vernon CT, US
Matthew A. Devore - Cromwell CT, US
Assignee:
UNITED TECHNOLOGIES CORPORATION - Hartford CT
International Classification:
F01D 5/18
B23P 15/02
US Classification:
416 97 R, 29889721
Abstract:
A turbine engine component includes a platform and one or more microcircuit cooling passages embedded within one or more walls of an airfoil portion of the component. Each microcircuit cooling passage terminates within the thickness of the platform so as to provide cooling to the initial 10% span of the airfoil portion. Each microcircuit cooling passage has an inlet for receiving cooling fluid, which inlet is also embedded within the platform.

Casting Core Assembly Methods

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US Patent:
20120168108, Jul 5, 2012
Filed:
Dec 30, 2010
Appl. No.:
12/981650
Inventors:
John R. Farris - Bolton CT, US
Douglas C. Jenne - West Hartford CT, US
Matthew S. Gleiner - Vernon CT, US
Peter H. Thomas - West Hartford CT, US
Assignee:
UNITED TECHNOLOGIES CORPORATION - Hartford CT
International Classification:
B22C 9/10
B22D 25/02
US Classification:
164 15, 164137, 164 72, 164 6, 164271
Abstract:
A casting core assembly includes a metallic core and a ceramic core. The process for forming the casting core assembly includes inserting a ceramic plug of a metallic core and ceramic plug core subassembly into a compartment of the ceramic core. The ceramic plug is secured to the ceramic core.

Ceramic Core Tapered Trip Strips

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US Patent:
20130195675, Aug 1, 2013
Filed:
Jan 16, 2013
Appl. No.:
13/742749
Inventors:
Matthew S. Gleiner - Vernon CT, US
Matthew A. Devore - Cromwell CT, US
Assignee:
UNITED TECHNOLOGIES CORPORATION - Hartford CT
International Classification:
B22C 9/10
US Classification:
416 97 R, 164271
Abstract:
A core die for creating an airfoil includes a first section, a second section mating with the first section, and an insert for creating a slot. The first section and the second section define a body having an outer dimension. The insert is disposed at an angle to the outer dimension. A trip strip includes a first portion disposed in the second section. The first portion is in register with the insert and a thickness is maintained between the first portion and the insert along a length of the insert. The first portion tapers towards the outer dimension and the thickness is filled by the ceramic material between the slot and the first portion.
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Matthew S Gleiner from Redondo Beach, CA, age ~41 Get Report