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Kent W Dunstan

from Leavenworth, WA
Age ~68
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Also known as:
Kent W Dustan, Kent Dunstokn
Related to:
Kyoung Y Kim, 60Jeff Markley, 42Dale W Markley, 74Erik R Dunstan, 41Michael C Padron, 46Denise M Dunstan, 67Phillip E Dunstan, 97Duke DunstanCheryl A Dunstan, 36Mary E Dunstan, 97
Connected to:
Christina R Dunstan, 62Eleanor F Dunstan, 96Guy Dunstan, 79Hazel E Dunstan, 52Jan L Dunstan, 92Jennifer M Dunstan, 50Larry J Dunstan, 77Lauren R Dunstan, 27Lawrence W Dunstan, 77Leon Dunstan, 36

Kent Dunstan Phones & Addresses

  • Leavenworth, WA
  • 32409 51St St, Federal Way, WA 98023 (253) 874-8886
  • Kent, WA
  • Des Moines, WA
  • 32409 51St Ave SW, Federal Way, WA 98023 (253) 217-6750

Work

Position: Professional/Technical

Education

Degree: Associate degree or higher

Emails

k***[email protected]

Resumes

Resumes

Kent Dunstan Photo 1

Engineer

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Location:
Federal Way, WA
Industry:
Aviation & Aerospace
Work:
Boeing
Engineer
Kent Dunstan Photo 2

Kent Dunstan

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Publications

Us Patents

Superplastic Forming Of Titanium Assemblies

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US Patent:
7850058, Dec 14, 2010
Filed:
Nov 10, 2005
Appl. No.:
11/272244
Inventors:
Thomas J. Connelly - Rellevue WA, US
Kent W. Dunstan - Federal Way WA, US
Peter N. Comley - Sumner WA, US
Larry D. Hefti - Auburn WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B23K 31/00
US Classification:
228157, 228193, 148564
Abstract:
A method of superplastic forming of titanium packs and an associated assembly is provided. The titanium packs can include sheets having different granular structures so that the different sheets are adapted to superplastically form at different temperatures. One or more of the sheets can be formed at a temperature that is below the superplastic forming temperature of another sheet in the pack. In some cases, the occurrence of markoff can be reduced or eliminated.

Spring Loaded Pressure Relief Door

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US Patent:
8439308, May 14, 2013
Filed:
Nov 19, 2010
Appl. No.:
12/927659
Inventors:
Michael E. Armstrong - Kent WA, US
Michael D. Jones - Kirland WA, US
Kent W. Dunstan - Federal Way WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
F16P 7/00
B64D 33/00
F24F 11/02
US Classification:
2441294, 244 53 R, 454 70, 454340, 60 391, 49141
Abstract:
A pressure relief apparatus for an engine compartment having a wall and an opening in the wall is provided. The pressure relief apparatus includes a door panel arranged in blocking relationship to the opening in the wall of the engine compartment, a plurality of hinges coupling the door panel to an inner surface of the wall of the engine compartment, a spring assembly coupled between each hinge and the inner surface of the wall, wherein the spring assembly includes a canister having an open end and a spring element housed within the canister, and a support fitting mounted to the engine compartment wall and having a portion extending toward the open end of the canister for applying a compressive force on the spring element.

Three Link Failsafe Engine Mount

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US Patent:
58606238, Jan 19, 1999
Filed:
Apr 14, 1997
Appl. No.:
8/834329
Inventors:
Kent W. Dunstan - Federal Way WA
Kenneth E. Hey - Seattle WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
B64D 2726
US Classification:
244 54
Abstract:
A failsafe engine mount (19) that includes a first link (45), a second link (47), a third link (53), four upper connection locations (39a), (39b), (39c), (39d) on an upper fitting (31), and four lower connection locations (75a), (75b), (75c), (75d) on a clevis strip (73) of an engine casing (71), is disclosed. The first link (45) connects the first upper connection location (39a) with the first lower connection location (75a). The second link (47) has a first arm (49) that connects the second lower connection location (75b) with the second upper connection location (39b). The second link (47) further includes a second arm (51) that connects the second upper connection location (39b) with the third lower connection location (75c). The third link (53) has a first arm (55) that connects the third upper connection location (39c) with the fourth upper connection location (39d). The third link (53) further includes a second arm (57) arranged to connect the fourth upper connection location (39d) with the fourth lower connection location (75d).

Aircraft Engine Thrust Mount

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US Patent:
58735470, Feb 23, 1999
Filed:
May 20, 1997
Appl. No.:
8/859663
Inventors:
Kent W. Dunstan - Federal Way WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
B64D 2726
US Classification:
244 54
Abstract:
A thrust mount (24) for passing thrust loads between a forward engine frame (16) and an aft engine mount upper fitting (34). The thrust mount includes first and second thrust links (46), (48) interconnected between the engine frame and an evener bar. A central clevis (30) extends forwardly from a forward surface (32) of the upper fitting (34). The central clevis (30) accepts a center portion (36) of the evener bar (38) and secures the evener bar therein using a rotatable connection mechanism (40). A pair of thrust lugs (42) also extends forwardly from the upper fitting. The central clevis is located between the opposed thrust lugs. Each thrust lug (42) includes slots (44) for receiving an evener bar end. The evener bar (38) further includes an aft surface (48) positioned near, though not normally contacting, the upper fitting forward surface (32). The rotatable connection mechanism (40) at the central clevis transfers thrust loads during normal operations.
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Kent W Dunstan from Leavenworth, WA, age ~68 Get Report