The Boeing Company

Michael R Holle

Alex V Botvinnik

Deborah L Hartley

Leonard J Hebert

John George Kladouris

Russel L Thornock

Joel E Hansen

Jeffrey P Kane

Russell S Brinton

Michael B Scholey

Russel S Brinton

A method of forming an assembly from a plurality of components, the plurality of components each having a component volume and a respective locus point, is described. The method includes selecting a target volume by defining a target volume and respective locus point. The method further includes determining a solution group of components comprising a list of components having a component volume positioned at least one of within the target volume and a predetermined distance from the target volume. The method further includes displaying the solution group of components forming an assembly.

Method and apparatus for determining a solution group of parts in an assembly

A method for determining a solution group of parts among a plurality of parts in an assembly, the solution group being situated substantially proximate to at least one target part of the plurality of parts, each respective part of the plurality of parts being identified by a respective part volume and a respective locus, each respective part volume substantially containing a respective part and each respective locus being identified with respect to an origin, includes the steps of: (a) Identifying a target volume substantially containing the at least one target part. (b) Identifying each respective part volume for each relevant part. Each relevant part is identified by a respective part volume having a predetermined relationship with respect to the target volume. (c) Assigning each relevant part to the solution group.

In a turbofan jet engine installation including a low pressure area (48) located between a primary exhaust nozzle (20) and strut fairings (30), an improvement including a fencing assembly (66) for reducing interaction of fan air (52) with air in the low pressure area. The fencing assembly (66) includes two pairs (70), (72) of opposed flow control fences (68) connected to the primary exhaust nozzle (20) at locations laterally outboard of the strut fairings (30). A first pair (70) includes fences formed of a single piece connected directly to the primary nozzle (20). A second pair (72) includes fences formed of a number of longitudinally spaced-apart segments (82). The segments (82) are connected to one face of an elongated attachment strap (84) with the opposite strap face being connected to the nozzle. Each fence includes a foot portion (78) and an upright portion (80) extending outwardly from the foot portion.

Segmented engine flow control device

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Kent, WA, United States of America

Michael R Holle