The Boeing Company

Theboeing Company

Adrian Stanescu

Michael Ronald Butcher

Mohammad Ali Heidari

John E Yestrau

Constantine Kostakis

Kyle C Advent

Dan Davis

Larry Schneider, Jr

Joseph B LaBelle

Donald T Powell

Daniel F Gelzer

Jennifer Bender Zielinski

Richard D Stokes, Jr

Saba Mahanian

Michael Patrick Foy

Richard D Stokes Jr

John Yestrau

Larry Schneider

Richard D Stokes

Joseph B Labelle

Nacelle inlet structures comprise an inlet inner barrel, an inlet outer barrel at least substantially enclosing the inlet inner barrel, an aft bulkhead extending between and operatively coupled to each of the inlet inner barrel and the inlet outer barrel, and an annular load absorber that is operatively coupled to each of the aft bulkhead and the inlet inner barrel. The aft bulkhead is operatively coupled to the inlet inner barrel via the annular load absorber, and the annular load absorber has a U-shaped cross-section that is open toward the inlet outer barrel.

Nacelle inlet structures, engine assemblies and vehicles including the same, and related methods

Nacelle inlet structures, engine assemblies and vehicles including the same, and related methods. A nacelle inlet structure of an engine assembly includes an inlet outer barrel and an inlet inner barrel with a tubular portion and an inlet attachment flange. The tubular portion of the inlet inner barrel extends at least partially along a direction parallel to the engine axis, while the inlet attachment flange extends from the tubular portion. The inlet attachment flange is integrally formed with at least a portion of the tubular portion of the inlet inner barrel. The inlet attachment flange is configured to be operatively coupled to an engine case of the engine assembly to operatively couple the nacelle inlet structure to the engine case. In examples, a method of manufacturing an inlet inner barrel includes forming a composite laminate with a composite manufacturing process.

A movement- and/or load transfer-limiting device for a turbine engine, comprises a first fitting including a retention member, with the first fitting being engaged with a fancase surrounding a turbine engine fan blade system. A second fitting is engaged with a fancowl disposed radially outward of the fancase. The second fitting includes a constraint member arranged to be received by the retention member. The retention member is arranged to limit radially outward movement of the fancowl via engagement with the constraint member. The constraint member comprises at least one of (i) a hook member arranged to limit radially inward movement of the first fitting in relation to the fancowl or (ii) a laterally-extending shaft having opposed ends and a flange engaged with at least one of the ends, arranged to limit lateral movement of the retention member in relation to the first fitting. Associated devices and methods are also provided.

Movement-limiting device for a turbine engine and associated method

Deformable spacers and spacer assemblies absorb energy when flange bolts are subjected to compressive axial loads by plastically deforming, failing in shear, rupturing or in a combination of failure modes so the flange bolts and the flanges connected thereby are not damaged. One deformable spacer may have a hollow cylindrical body with a plurality of elongated slots there through. Another deformable spacer may have an annular stiffener extending inwardly from an inner surface of a hollow cylindrical body. A spacer assembly may include an inner cylindrical body, and outer cylindrical body, and an annular shoulder extending from one of the bodies and engaged by the other body shears when a shear failure load is applied to the flange bolt. Another spacer assembly may include an annular belt around a cylindrical body so that the belt will rupture before the cylindrical body plastically deforms.

Load controlling bolted flange deformable spacers

A barrel nut with features for reducing tensile stresses under heavy load within the barrel nut has a partial-cylindrical body having a first planar end surface and a second planar end surface. A threaded bore extends through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface. At least one groove is formed in each of the first planar end surface and the second planar end surface, the groove having a rounded surface extending at least a part of a distance between a curved upper surface of the partial-cylindrical body to a bottom surface thereof in a direction substantially parallel to the central axis of the threaded bore.

Barrel nut with stress reduction features

A method and apparatus for suspending a load is provided. A load is connected to a yoke by one or more mounting links. The mounting links are connected to the yoke by a yoke pins and to the load by load mounting pins. The mounting links are connected to the pins by spherical bearings that enable the mounting links to move relative to yoke and to the load to accommodate movement of the load, such as movement caused by thermal expansion of the load. A stop collar is arranged around the load mounting pins to limit free movement of the mounting links about a longitudinal axis so that the mounting links cannot contact the load.

AFT engine mounting link rotational stop collar

Methods and apparatus to retain a rotor blade are disclosed herein. An example apparatus includes a rotor blade coupled to a rotatable hub of an engine system. The rotor blade includes a root, a flange and a blade. The root and the flange are disposed inside a cowling, and the blade is disposed outside of the cowling. The example apparatus also includes a retainer disposed inside the cowling adjacent the flange. The flange is to engage the retainer to retain the rotor blade with the engine system.

Methods and apparatus to retain a rotor blade

A method for manufacturing a bearing housing comprising: selecting a configuration for housing and manufacturing the housing the configuration. The selected housing configuration comprises a bearing section and a base having a cylindrical shape. The bearing section and base are substantially aligned centrally along an axis. A plurality of members extends between the bearing section and the base. The plurality of members has a length and a width, and, in the configuration, each of the plurality of members has a side that is substantially non-perpendicular with respect to the bearing section and the base. At least one of the plurality of members extends at an angle from the bearing section to the base; the plurality of members having a curve relative to the axis; and the width of the plurality of members decreasing or increasing along the length of the plurality of members.

Method of manufacturing a bearing housing for an engine with stress and stiffness control

An apparatus has a tubular body with a channel and a number of stiffeners. The number of stiffeners allows the tubular body to absorb additional mechanical energy through axial compression. Additionally, the number of stiffeners is located on a number of locations for the tubular body. The apparatus also has a plurality of hinges located in part between the number of locations of the number of stiffeners for the tubular body, and also located between end flanges at the end of the tubular body and a stiffener. The number of hinges further define deformable regions. At least one deformable region of the plurality of deformable regions is configured to expand away from the channel in response to the tubular body being compressed in the axial direction.

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Maple Valley, WA, United States of America

Adrian Stanescu