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David B Jan

from Ontario, CA
Age ~65
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Also known as:
David Brian Jan, David B Dan, David B Jain, Dave Jan, Jian Zhen
Related to:
Vivian J Chen, 33Andrew D Jan, 30Stephanie L Jan, 61Christina M Rodriguez, 61Christina C Jan, 64Donael T Miller, 39Weilian Zhen, 54Xuemei LiangChien Y ChenRongzhen ZhenThomas JanDonna Y ZhenKolton R LongYuming Chen, 33Michael L Chen, 63John C Jan, 93Chien Ying Chen, 37Zhen Zhang, 53Zhen Ying, 63
Connected to:
Abdullah Jan, 50Afzal S Jan, 98Alvin F Jan, 35Antony K Jan, 36Ben Jan, 56David B Jan, 70Duresamin A Jan, 85Elizabeth A Jan, 67Jane A Jan, 38Jenny Jan, 80

David Jan Phones & Addresses

  • Ontario, CA
  • Surprise, AZ
  • Pahrump, NV
  • Eastvale, CA
  • Corona, CA
  • Walnut, CA
  • Diamond Bar, CA
  • Rowland Heights, CA

Publications

Us Patents

Method For Modifying Gas Turbine Nozzle Area

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US Patent:
7186070, Mar 6, 2007
Filed:
Oct 12, 2004
Appl. No.:
10/963185
Inventors:
Mark C. Morris - Phoenix AZ, US
Thomas E. Strangman - Prescott AZ, US
Craig A. Wilson - Mesa AZ, US
George W. Wolfmeyer - Tempe AZ, US
Steve H. Halfmann - Chandler AZ, US
David K. Jan - Fountain Hills AZ, US
Assignee:
Honeywell International, Inc. - Morristown NJ
International Classification:
F04D 29/40
US Classification:
415 1, 2988922
Abstract:
A method of modifying a turbine nozzle area comprises depositing a thermal barrier coating (TBC) on the nozzle endwalls to provide a minimum nozzle area, evaluating an airflow through the nozzle, and machining the TBC to increase the nozzle area. Adjacent segment area variation may be minimized, improving engine reliability by reducing the aerodynamic excitation to the down stream blade.

Flow Discouraging Systems And Gas Turbine Engines

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US Patent:
8312729, Nov 20, 2012
Filed:
Sep 21, 2009
Appl. No.:
12/563622
Inventors:
Mark Matwey - Phoenix AZ, US
David Jan - Fountain Hills AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
F02C 7/12
US Classification:
60806, 415115
Abstract:
A flow discouraging system includes a stator assembly, fins, and a rotor assembly. The stator assembly includes stationary components forming a side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface. One or more outer axial fins disposed in the annular groove extend along the outer axially-extending surface of the side wall. One or more inner axial fins disposed in the annular groove extend along the inner axially-extending surface of the side wall. One or more radial fins disposed in the annular groove extend axially from the radial surface of the side wall. The rotor assembly is disposed adjacent to and is spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove and disposed between the outer and inner axial fins.

Methods And Tooling Assemblies For The Manufacture Of Metallurgically-Consolidated Turbine Engine Components

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US Patent:
8408446, Apr 2, 2013
Filed:
Feb 13, 2012
Appl. No.:
13/371922
Inventors:
Jason Smoke - Phoenix AZ, US
David K. Jan - Fountain Hills AZ, US
Don Mittendorf - Mesa AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
B23K 20/00
B21K 25/00
US Classification:
228193, 228194, 2282341, 228245, 298892
Abstract:
Embodiments of a method for manufacturing a turbine engine component are provided, as are embodiments of a thermal growth constraint tool for the manufacture of turbine engine components. In one embodiment, the method includes the steps of obtaining a plurality of arched pieces, arranging the plurality of arched pieces in a ring formation, and bonding the plurality of arched pieces together to produce a monolithic ring by heating the ring formation to a predetermined bonding temperature while constraining the outward radial growth thereof.

Flow Discouraging Systems And Gas Turbine Engines

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US Patent:
20120003084, Jan 5, 2012
Filed:
Jun 30, 2010
Appl. No.:
12/827296
Inventors:
Mark Matwey - Phoenix AZ, US
David K. Jan - Fountain Hills AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
F01D 1/02
US Classification:
4151981
Abstract:
A flow discouraging system includes a stator assembly, a rotor assembly, and a plurality of fingers. The stator assembly includes one or more stationary components forming a side wall, the side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface extending between the outer and inner axially-extending surfaces. The rotor assembly is disposed adjacent to and spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove. The plurality of fingers is disposed in the annular groove and extends from the one or more stationary components the annular rim.

Multi-Piece Centrifugal Impellers And Methods For The Manufacture Thereof

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US Patent:
20130004316, Jan 3, 2013
Filed:
Jun 28, 2011
Appl. No.:
13/171158
Inventors:
Mark Matwey - Phoenix AZ, US
Srinivas Chunduru - Chandler AZ, US
David K. Jan - Fountain Hills AZ, US
David Hanley - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
F01D 5/14
B23P 15/04
US Classification:
416198 A, 298897
Abstract:
Embodiments of a multi-piece centrifugal impeller are provided, as are embodiments of a method for manufacturing a multi-piece centrifugal impeller. In one embodiment, the centrifugal impeller includes an inducer piece and an exducer piece. The inducer piece includes, in turn, an inducer hub and a plurality of forward blade segments, which extend radially outward from the inducer hub. The exducer piece includes an exducer hub, which is positioned axially adjacent the inducer hub, and a plurality of aft blade segments, which extending outward from the exducer hub. The plurality of aft blade segments interlock with the plurality of forward blade segments to form a plurality of contiguous blade structures, which extend from a forward portion of the inducer hub to an aft portion of the exducer hub.

Gas Turbine Engine Cooling Systems Having Hub-Bleed Impellers And Methods For The Production Thereof

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US Patent:
20130098061, Apr 25, 2013
Filed:
Oct 19, 2011
Appl. No.:
13/277034
Inventors:
Mark Matwey - Phoenix AZ, US
David K. Jan - Fountain Hills AZ, US
Srinivas Jaya Chunduru - Chandler AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
F02C 6/04
B23P 15/04
US Classification:
60785, 298892
Abstract:
Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller having a hub, a plurality of hub bleed air passages, and a central bleed air conduit. The plurality of hub bleed air passages each have an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub. The central bleed air conduit is fluidly coupled to the outlets of the plurality of hub bleed air passages and is configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto.

Dual Alloy Gas Turbine Engine Rotors And Methods For The Manufacture Thereof

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US Patent:
20170044912, Feb 16, 2017
Filed:
Aug 11, 2015
Appl. No.:
14/823787
Inventors:
Jason Smoke - Phoenix AZ, US
Eric Blumer - Scottsdale AZ, US
David K. Jan - Fountain Hills AZ, US
Robbie Joseph Adams - Phoenix AZ, US
Harry Lester Kington - Scottsdale AZ, US
Assignee:
HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:
F01D 5/30
F01D 5/14
F01D 5/22
F01D 5/02
Abstract:
Dual alloy Gas Turbine Engine (GTE) rotors and method for producing GTE rotors are provided. In one embodiment, the method include includes arranging bladed pieces in an annular grouping or ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces. A first or bonding alloy is deposited along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints, which join the bladed pieces in a bonded blade ring. The bonding alloy is preferably selected to have a ductility higher than and a melt point lower than the alloy from which the bladed pieces are produced. After deposition of the first alloy and formation of the alloy-filled joints, a hub disk is inserted into the central opening of the bonded blade ring. The hub disk and blade ring are then bonded utilizing, for example, a Hot Isostatic Pressing process.
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David B Jan from Ontario, CA, age ~65 Get Report