John A Welch

US Patent:

6549820, Apr 15, 2003

Filed:

Jul 27, 1999

Appl. No.:

09/361666

Inventors:

Russell A. Barrett - Douglass KS
Jon J. Fischer - Bentley KS
Kenneth E. Garrett - Wichita KS
David M. Gayle - Douglass KS
Timothy L. Holdeman - Halstead KS
Darrell C. Jundt - Derby KS
Brian R. Kitt - Wichita KS
Donald D. Ruebke - Whitewater KS
Brett E. Russell - Seattle WA
Kenneth C. Stewart - Wichita KS
John M. Welch - Wichita KS
Sandra L. Jansen - Wichita KS

Assignee:

The Boeing Company - Seattle WA

International Classification:

G06F 1900

US Classification:

700110, 700169, 382141

Abstract:

A computer-implemented method for providing on-line ultrasonically scanned images of composite parts for immediate feedback in a manufacturing environment is discussed. The scanned images are edited to indicate each deficiency that has been repaired on a previously assembled composite part. Quality assurance personnel enter data associated with each composite part and verify the data content. Repair personnel enter data associated with correcting an identified deficiency of the composite part. Historical data suitable for developing statistics and trends are stored for each type of composite part. When queries are launched, the statistical and trend data is filtered to produce reports that are displayed. That is, reports are generated that identify particular statistics and trends. The scan image and data associated with a composite part are linked together for cross-referencing and stored in a database that is accessible by client and server computers on a network.

US Patent:

7571527, Aug 11, 2009

Filed:

Mar 29, 2005

Appl. No.:

10/907320

Inventors:

John L. Burnett - Derby KS, US
David W. Hackler - Wichita KS, US
Timothy C. Wilson - August KS, US
John M. Welch - Wichita KS, US
Thomas D. Popp - Wichita KS, US
Christopher S. Sawyer - Oxford KS, US
Leo B. Hoadley - Belle Plaine KS, US
Leroy J. Fulbright - Wichita KS, US
Mitchel B. Granger - Wichita KS, US
Barry B. Craig - Rose Hill KS, US
Phillip E. Kenney - Cottonwood Falls KS, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B25B 27/14
B23Q 3/00

US Classification:

292816, 292811, 29464, 29468, 29 2351, 60798, 244110 B

Abstract:

A mandrel is disclosed for fabricating a monolithic composite nacelle panel for use on an airplane. Also disclosed is the method of constructing the mandrel, the method of assembling the mandrel, and the method of disassembling the mandrel.

US Patent:

7963039, Jun 21, 2011

Filed:

Mar 9, 2009

Appl. No.:

12/400003

Inventors:

John L. Burnett - Derby KS, US
David W. Hackler - Wichita KS, US
Timothy C. Wilson - Augusta KS, US
John M. Welch - Wichita KS, US
Thomas D. Popp - Wichita KS, US
Christopher S. Sawyer - Oxford KS, US
Leo B. Hoadley - Belle Plaine KS, US
Leroy J. Fulbright - Wichita KS, US
Mitchel B. Granger - Wichita KS, US
Barry B. Craig - Rose Hill KS, US
Phillip E. Kenney - Cottonwood Falls KS, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B21K 23/00
B25B 27/14
B23Q 3/00

US Classification:

2989732, 29464, 29468, 60798, 244110 B

Abstract:

A method of constructing, assembling and disassembling a mandrel for fabricating a monolithic composite nacelle panel for use on an airplane comprises attaching a first fairing bar including an exposed ball roller assembly to a tilting plate; attaching a first outer section to said first fairing bar; attaching a second outer section to said first fairing bar; attaching a center section to said first outer section and said second outer section; attaching a nozzle section to said first fairing bar and positioned adjacent an inner wall of said first outer section, an inner wall of said center section, and an inner wall of said second outer section; attaching a second fairing bar to said first outer section, said center section, and said second outer section; and attaching a cavity section to said second fairing bar.

US Patent:

8172176, May 8, 2012

Filed:

Feb 4, 2009

Appl. No.:

12/365620

Inventors:

John M. Welch - Wichita KS, US
Thomas D. Popp - Wichita KS, US

Assignee:

Spirit AeroSystems, Inc. - Wichita KS

International Classification:

B64C 25/68

US Classification:

244110B, 244131, 244117 R, 2441291, 602262, 464 52, 464 88, 74 88, 74 8933

Abstract:

A slider apparatus integral with a slidable member and a method for integrating the slider apparatus with the slidable member. The slider apparatus integrated with the slidable member may be configured to slidably couple with and be structurally supported by a fixed structure. The slider apparatus may comprise a primary slider component made of composite material and at least one chamfered element bonded to the primary slider component. The slidable member may comprise the slider apparatus, a core assembly, a plurality of composite material plies wrapped around the slider apparatus and core assembly and cured therewith, and at least one low-friction slider shoe removably attached to the primary slider component outward of the plurality of composite material plies.

US Patent:

8251174, Aug 28, 2012

Filed:

Mar 26, 2010

Appl. No.:

12/732415

Inventors:

John M. Welch - Wichita KS, US
John Thomas Strunk - Derby KS, US
Brian R. Kitt - Wichita KS, US

Assignee:

Spirit AeroSystems, Inc. - Wichita KS

International Classification:

E04B 1/82

US Classification:

181292, 181210

Abstract:

A method for splicing honeycomb core together to form a core structure, such as an acoustic panel for an aircraft. The core structure may comprise a first honeycomb core, a second honeycomb core, and an intermediate bonding part disposed between the first and second honeycomb cores. The intermediate bonding part may comprise a syntactic core wrapped with or sandwiched between a non-foaming film adhesive. The syntactic core sandwiched between a first and second layer of film adhesive and a first and second honeycomb core is then compressed by vacuum and cured to bond the honeycomb cores together, forming the core structure.

US Patent:

8302907, Nov 6, 2012

Filed:

Mar 4, 2010

Appl. No.:

12/717501

Inventors:

John M. Welch - Wichita KS, US
Henry Arnold Schaefer - Wichita KS, US
Matthew Scott Tymes - Wichita KS, US
Michael Patrick Urban - Wichita KS, US

Assignee:

Spirit AeroSystems, Inc. - Wichita KS

International Classification:

F02K 1/54

US Classification:

244110B

Abstract:

A hybrid torque box comprising a plurality of composite tubes and metal fittings attached together in alternating succession and configured to attach a thrust reverser to an engine fan case of an aircraft. The hybrid torque box may be substantially hollow and may comprise two V-blades for attaching the torque box to the engine fan case. The hybrid torque box may also be attached to or integral with a bull nose fairing configured for attachment with a cascade of the thrust reverser. Furthermore, the hybrid torque box may comprise and/or attach to a cowl interface flange configured for interfacing with an outer cowl of the thrust reverser.

US Patent:

8322653, Dec 4, 2012

Filed:

Sep 11, 2009

Appl. No.:

12/558042

Inventors:

John M. Welch - Wichita KS, US
Henry A. Schaefer - Wichita KS, US
Matthew Scott Tymes - Wichita KS, US
Michael Urban - Wichita KS, US

Assignee:

Spirit AeroSystems, Inc. - Wichita KS

International Classification:

F02K 1/54

US Classification:

244110B, 244 54, 602262, 23926525

Abstract:

Latch beams and hinge beams of an aircraft thrust reverser and a method for manufacturing the beams. The latch and hinge beams may comprise a plurality of hollow composite tubes joined with a plurality of machined metal fittings in alternating succession. The metal fittings may comprise at least one of hinge fittings and latching fittings. The latch and hinge beams may further comprise slider tracks configured to slidably attach to a translating sleeve of the thrust reverser. The hinge beams may each be rotatably attached to an engine strut or pylon of the aircraft, and the latch beams may each be mechanically latched with each other. Each of the latch and hinge beams may also be fixedly attached to an inner engine cowling of the thrust reverser.

US Patent:

8398017, Mar 19, 2013

Filed:

Feb 4, 2009

Appl. No.:

12/365376

Inventors:

John M. Welch - Wichita KS, US

Assignee:

Spirit AeroSystems, Inc. - Wichita KS

International Classification:

B64D 27/00

US Classification:

244 54, 244 53 B, 60796, 60797, 60798, 384 29

Abstract:

A duct having a continuous C-shaped cross section slidably attached to a strut supporting an aircraft engine. The duct may comprise an inner wall, an outer wall, a first end wall, a second end wall, at least one slider, a thrust reverser, and an outer cowl panel of a thrust reverser. The inner wall may comprise a forward section and an aft section. The aft section may be integral with the first end wall, the second end wall, the outer wall, and the at least one slider. The forward section may comprise a right half and a left half which may be pivotally attached to the strut and may pivot to an open position when the rest of the fan duct is slid aftward away from the engine. The duct, excluding the forward section of the inner wall, may slide aftward on its at least one slider, providing engine access.