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Vladimir K Tolpygo

from Scottsdale, AZ
Age ~67
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Also known as:
Vlad Tolpygo
Phone and address:
5816 E Gelding Dr, Scottsdale, AZ 85254
(602) 293-3982
Related to:
Elena V Tolpygo, 45Gavin Cranley, 58Elena Vanegas, 45Elena Sanchez, 45Anastassia Tolpygo, 38Irina Tolpygo, 67
Connected to:
Katherine F Tolsdorf, 73Benjamin S Tolsky, 44Andy Tolsma, 74Jody L Tolsma, 52Lora L Tolsma, 48Ronald R Tolsma, 65Ryan J Tolsma, 88Tina N Tolsma, 49Aileen L Tolson, 60

Vladimir Tolpygo Phones & Addresses

  • 5816 E Gelding Dr, Scottsdale, AZ 85254 (602) 293-3982
  • 7620 Cathedral Oaks Rd, Goleta, CA 93117 (805) 685-7164
  • Maricopa, AZ

Resumes

Resumes

Vladimir Tolpygo Photo 1

Vladimir Tolpygo

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Location:
Phoenix, Arizona Area
Industry:
Research
Vladimir Tolpygo Photo 2

Principal Engineer At Honeywell Aerospace

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Position:
Principal Engineer at Honeywell Aerospace
Location:
Phoenix, Arizona Area
Industry:
Research
Work:
Honeywell Aerospace
Principal Engineer
UC Santa Barbara 1995 - 2006
post-doc, research assistant
Max Planck Institute for Iron Research Sep 1994 - Jun 1995
post-doc researcher
TsNIICherMet, Moscow Jul 1980 - Aug 1993
engineer, research scientist
Education:
Moscow Steel and Alloys Institute 1974 - 1980

Publications

Us Patents

Turbine Engine Components

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US Patent:
8449994, May 28, 2013
Filed:
Jun 30, 2009
Appl. No.:
12/495208
Inventors:
Vladimir K. Tolpygo - Scottsdale AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
F03D 11/02
F04D 29/38
B64C 11/16
F01D 5/14
B32B 27/32
B32B 9/00
B32B 15/04
B32B 19/00
US Classification:
428702, 428220, 428469, 428472, 428697, 428701, 416241 B, 416241 R
Abstract:
A thermal barrier coating is formed over the substrate. A majority of the thermal barrier coating comprises a multi-phase material comprising a polycrystalline material including two or more phases. Each phase forms an individual grain, adjacent individual grains are separated by grain boundaries, each phase comprises an oxide compound, the multi-phase material is formed from three or more constituents, the three or more constituents consist of different materials that are not completely soluble in each other, and the two or more phases are not completely soluble in each other and do not form only one compound.

Methods And Systems For Inspecting Structures For Crystallographic Imperfections

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US Patent:
8605858, Dec 10, 2013
Filed:
Jun 27, 2011
Appl. No.:
13/169902
Inventors:
Surendra Singh - Chandler AZ, US
Andy Szuromi - Phoenix AZ, US
Vladimir K. Tolpygo - Scottsdale AZ, US
Andy Kinney - Chandler AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
G01N 23/207
US Classification:
378 73, 378 71
Abstract:
Embodiments of methods and systems for inspecting a structure for a crystallographic imperfection are provided. In the method, an X-ray wavelength that is particularly susceptible to diffraction by the crystallographic imperfection is identified. Then an X-ray source is provided to emit X-rays in the identified X-ray wavelength. While placing the structure at a sequence of positions relative to the X-ray source, X-rays are directed at the structure in multiple, non-parallel arrays to create sequential patterns of diffracted X-rays. The patterns of diffracted X-rays are digitally captured and communicated to a computer that compares them to locate the crystallographic imperfection. For a surface imperfection, the imperfection may be marked with a target to allow for physical removal.

Turbine Components And Methods Of Manufacturing Turbine Components

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US Patent:
8206117, Jun 26, 2012
Filed:
Dec 19, 2007
Appl. No.:
11/960099
Inventors:
Thomas E. Strangman - Prescott AZ, US
Vladimir K. Tolpygo - Scottsdale AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
F01D 5/34
US Classification:
416219R, 416244 A, 2988921
Abstract:
Turbine components are provided. In an embodiment, by way of example, a hub and a ring are included. The hub comprises a first material. The ring is bonded to the hub. The ring comprises a plurality of arc segments forming a ring, each arc segment comprising a second material comprising a single crystal superalloy material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each arc segment being substantially equal, and each predetermined secondary orientation of each arc segment being substantially equal, each arc segment adjacent another arc segment, and the adjacent arc segments having a predetermined crystallographic mismatch therebetween. Methods of manufacturing are also provided.

Coated Components And Methods Of Fabricating Coated Components And Coated Turbine Disks

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US Patent:
20100124670, May 20, 2010
Filed:
Nov 19, 2008
Appl. No.:
12/273843
Inventors:
Vladimir K. Tolpygo - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
H01B 12/00
C23C 10/28
C23C 28/00
US Classification:
428678, 428615, 427295, 205183, 505110
Abstract:
Coated components and methods of fabricating coated components and coated turbine disks are provided. In an embodiment, by way of example only, a coated component includes a substrate comprising a superalloy in an unmodified form and a coating disposed over the substrate, where the coating comprises the superalloy in a modified form. The modified form of the superalloy includes at least 10% more chromium and at least 10% more of one or more noble metals than the unmodified form of the superalloy, and the modified form of the superalloy is substantially free of aluminum.

Coated Components And Methods Of Fabricating Coated Components And Coated Turbine Disks

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US Patent:
20120090736, Apr 19, 2012
Filed:
Dec 30, 2011
Appl. No.:
13/341259
Inventors:
Vladimir K. Tolpygo - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
C23C 10/00
C23C 10/60
C23C 28/02
US Classification:
148518, 148527
Abstract:
Coated components and methods of fabricating coated components and coated turbine disks are provided. In an embodiment, by way of example only, a coated component includes a substrate comprising a superalloy in an unmodified form and a coating disposed over the substrate, where the coating comprises the superalloy in a modified form. The modified form of the superalloy includes, by weight, at least 10% more chromium and at least 10% more of one or more noble metals than the unmodified form of the superalloy, and the modified form of the superalloy is substantially free of aluminum

System And Method For Cleaning Cooling Passages Of A Combustion Chamber

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US Patent:
20200095940, Mar 26, 2020
Filed:
Nov 8, 2019
Appl. No.:
16/678476
Inventors:
- Morris Plains NJ, US
Nagaraja S. Rudrapatna - Chandler AZ, US
Vladimir K. Tolpygo - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:
F02C 7/30
F01D 25/00
F02C 7/18
F04D 29/54
Abstract:
Systems and methods are provided for cleaning one or more cooling passages associated with a combustion chamber of a gas turbine engine. The gas turbine engine has a compressor section upstream from the combustion section. The method includes receiving a pressurized fluid from a source and directing the pressurized fluid through an inlet of a chamber such that a portion of a plurality of particles within the chamber is entrained within the pressurized fluid. The method includes injecting the pressurized fluid with the entrained portion of the plurality of particles downstream from the compressor section through an end wall of a diffuser and deswirl system upstream from a combustor plenum of the combustion section to clean the one or more cooling passages associated with the combustion chamber.

Method Of Forming An Abrasive Nickel-Based Alloy On A Turbine Blade Tip

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US Patent:
20200078867, Mar 12, 2020
Filed:
Sep 10, 2018
Appl. No.:
16/126222
Inventors:
- Morris Plains NJ, US
Vladimir K Tolpygo - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:
B22F 5/04
B22F 9/08
B23K 26/21
Abstract:
A method of forming an abrasive nickel-based alloy on a turbine blade tip includes producing or obtaining a metal powder that is mixed with a carbon powder to form a carbon-enriched metal powder. The metal powder includes a refractory element. The method further includes bonding the carbon-enriched metal powder to the turbine blade tip. The step of bonding includes raising the temperature of the carbon-enriched metal powder past its melting point, thereby causing the carbon to combine with the refractory elements to form abrasive carbide particles.

Quinary, Low-Conductivity Thermal Barrier Coatings For Turbine Engine Components

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US Patent:
20190203603, Jul 4, 2019
Filed:
Jan 3, 2018
Appl. No.:
15/860861
Inventors:
- Morris Plains NJ, US
Wil Baker - Phoenix AZ, US
Vladimir K. Tolpygo - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:
F01D 5/28
F01D 9/04
Abstract:
Thermal barrier coatings, which may be used in gas turbine engines, comprise or consist of a tantala-niobia-zirconia mixture that is stabilized with two or more stabilizers. An exemplary thermal barrier coating comprises or consists of, by mole percent: about 2% to about 30% YO; about 8% to about 30% YbOor GdOor combination thereof; about 6% to about 30% TaO; about 0.1% to about 10% NbO; about 0% to about 10% HfO; and a balance of ZrO.
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Vladimir K Tolpygo from Scottsdale, AZ, age ~67 Get Report