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Amandine A Miner

from Altamonte Springs, FL
Age ~37
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Also known as:
Amandine Bourlier
Phone and address:
615 Hattaway Dr, Altamonte Springs, FL 32701
(321) 277-8471
Related to:
Curtis Thomas Aldrich, 35Est R SeibertDuane A Miner, 63Rebecca Miner, 38Melja A Miner, 43Rhonda A Miner, 64Duane A Miner, 41
Connected to:
Alongeh A Miner, 44Andrew Miner, 45Ben F Miner, 93Brady L Miner, 31Casey C Miner, 62Cheree A Miner, 68Cheryl A Miner, 73Christen Miner, 56Christopher S Miner, 57Corey R Miner, 50

Amandine Miner Phones & Addresses

  • 615 Hattaway Dr, Altamonte Spg, FL 32701 (321) 277-8471
  • Altamonte Springs, FL
  • Maitland, FL
  • Brighton, CO
  • Tempe, AZ
  • Port Orange, FL

Resumes

Resumes

Amandine Miner Photo 1

Project Engineer

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Location:
615 Hattaway Dr, Altamonte Springs, FL 32701
Industry:
Aviation & Aerospace
Work:
Embry-Riddle Aeronautical University Jan 2010 - Dec 2010
Graduate Research Assistant
Snecma Jun 2009 - Aug 2009
Intern
Education:
Embry-Riddle Aeronautical University 2009 - 2010
MSAE, Aerospace Engineering EPF Ecole d'Ingénieurs 2005 - 2010
Engenieur, Aerospace Engineering Embry-Riddle Aeronautical University 2008 - 2009
BS, Aerospace Engineering
Skills:
Aerospace
Earned Value Management
Aerodynamics
Cfd
Propulsion
Six Sigma
Project Engineering
Aeronautics
Project Management
Ms Project
Project Planning
Aerospace Engineering
Fluid Dynamics
Sap
Turbines
Vibration Isolation
Dfss Green Belt
Patent Portfolio Management
Capital Management
Geometric Dimensioning and Tolerancing
Systems Engineering
Engineering Management
Engineering
Microsoft Office
Program Management
Testing
Translation
Gas Turbines
Customer Experience
Contract Negotiation
Matlab
Project Estimation
Customer Relationship
Cost Control
Cost Management
Cost Planning
Business Strategy
Power Systems
Project Coordination
Data Analysis
Siemens Nx
Interpersonal Skills
Technical Publication
Invention
Teamcenter
Project Leadership
Regulatory Documentation
Tso
Time Management
Problem Solving
Customer Satisfaction
Power Generation
Languages:
English
French
Spanish
Certifications:
Green Belt Dfss
Project Management Professional (Pmp)®
Amandine Miner Photo 2

Amandine Miner

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Publications

Us Patents

Axially-Split Radial Turbines And Methods For The Manufacture Thereof

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US Patent:
20130272882, Oct 17, 2013
Filed:
Apr 11, 2012
Appl. No.:
13/444070
Inventors:
Don Mittendorf - Mesa AZ, US
David K. Jan - Fountain Hills AZ, US
Jason Smoke - Phoenix AZ, US
Amandine Miner - Tempe AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
F01D 5/02
B23P 15/04
F01D 5/14
US Classification:
416175, 2988922
Abstract:
Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

Methods For Producing Gas Turbine Engine Rotors And Other Powdered Metal Articles Having Shaped Internal Cavities

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US Patent:
20200376561, Dec 3, 2020
Filed:
Aug 18, 2020
Appl. No.:
16/996569
Inventors:
- Morris Plains NJ, US
Amandine Miner - Tempe AZ, US
Harry Lester Kington - Scottsdale AZ, US
Anthony Martinez - Phoenix AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:
B22F 5/00
B22F 3/15
B23P 15/00
B22F 3/24
Abstract:
Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Diverging-Converging Cooling Passage For A Turbine Blade

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US Patent:
20170254209, Sep 7, 2017
Filed:
Mar 7, 2016
Appl. No.:
15/062952
Inventors:
- Morris Plains NJ, US
David K. Jan - Fountain Hills AZ, US
Amandine Miner - Tempe AZ, US
Deanna Pinar Chase - Tempe AZ, US
Michael Kahrs - Phoenix AZ, US
Lorenzo Crosatti - Phoenix AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:
F01D 5/18
F01D 5/04
Abstract:
A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

Dual Alloy Bladed Rotors Suitable For Usage In Gas Turbine Engines And Methods For The Manufacture Thereof

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US Patent:
20170138206, May 18, 2017
Filed:
Nov 12, 2015
Appl. No.:
14/939360
Inventors:
- Morris Plains NJ, US
David K. Jan - Fountain Hills AZ, US
Don Mittendorf - Mesa AZ, US
Brent Ludwig - Scottsdale AZ, US
Amandine Miner - Tempe AZ, US
Deanna Pinar Chase - Tempe AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:
F01D 5/30
B23K 26/342
B23K 20/22
B23K 15/00
F01D 5/02
B23K 20/02
Abstract:
Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.

Methods For Producing Gas Turbine Engine Rotors And Other Powdered Metal Articles Having Shaped Internal Cavities

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US Patent:
20160082510, Mar 24, 2016
Filed:
Sep 22, 2014
Appl. No.:
14/492302
Inventors:
- Morristown NJ, US
Amandine Miner - Tempe AZ, US
Harry Lester Kington - Scottsdale AZ, US
Anthony Martinez - Phoenix AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
B22F 5/00
B22F 3/15
B22F 3/24
F01D 5/02
F01D 5/28
Abstract:
Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Axially-Split Radial Turbines

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US Patent:
20150247409, Sep 3, 2015
Filed:
May 15, 2015
Appl. No.:
14/713220
Inventors:
- Morristown NJ, US
David K. Jan - Fountain Hills AZ, US
Jason Smoke - Phoenix AZ, US
Amandine Miner - Tempe AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
F01D 5/14
F01D 5/28
F01D 5/04
Abstract:
Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

Impingement-Cooled Turbine Rotor

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US Patent:
20140348664, Nov 27, 2014
Filed:
May 13, 2013
Appl. No.:
13/892828
Inventors:
HONEYWELL INTERNATIONAL INC. - , US
Amandine Miner - Tempe AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
F01D 5/08
US Classification:
416 96 R
Abstract:
An integral turbine includes a forward hub section and an aft hub section. The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.
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Amandine A Miner from Altamonte Springs, FL, age ~37 Get Report