A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aircraft component. The thermoplastic patch and the thermoplastic aircraft component each include a thermoplastic matrix and a plurality of fibers embedded within the thermoplastic matrix. A metal plate is arranged against a stack. The stack includes the thermoplastic patch and the thermoplastic aircraft component. The thermoplastic patch and the thermoplastic aircraft component are consolidated together. The consolidating includes concurrently induction heating the thermoplastic patch, the thermoplastic aircraft component and the metal plate using an induction heating coil.
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
B29C 73/32 - Apparatus or accessories not otherwise provided for for local pressing or local heating using an elastic element, e.g. inflatable bag
B29C 73/34 - Apparatus or accessories not otherwise provided for for local pressing or local heating for local heating
2.
INDUCTION WELDING THERMOPLASTIC MATERIAL WITH DIFFERENT ELECTRICAL CONDUCTIVITIES
A method is provided during which a first thermoplastic body is provided. The first thermoplastic body includes first fiber-reinforcement with a first electrical conductivity. A second thermoplastic body is provided. The second thermoplastic body includes second fiber-reinforcement with a second electrical conductivity that is greater than the first electrical conductivity. The second thermoplastic body is arranged with the first thermoplastic body. The second thermoplastic body is induction welded to the first thermoplastic body using an induction welding coil. The second thermoplastic body is arranged between the first thermoplastic body and the induction welding coil.
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
3.
LOCKING ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM THRUST REVERSER
A thrust reverser for an aircraft propulsion system includes a fixed thrust reverser structure including a wall, a sleeve configured to translate between a first stowed position and a second position, and a blocker door assembly including a plurality of blocker doors. An upstream end of the sleeve is disposed at the wall with the sleeve in the first stowed position. A locking assembly includes a locking body and a receiver. Each blocker door includes a body pivotably mounted to the sleeve by a hinge and the locking body. Translation of the sleeve from the first to the second position effects pivoting of the blocker door body from a first stowed position to a second position. In a locked position, the locking body is engaged with the wall and disposed at the receiver. In an unlocked position, the locking body is disengaged with the wall and the receiver.
According to an aspect of the present disclosure, an ultrasonic welding tool having a longitudinal axis is provided that includes an ultrasonic tool, a tapered step horn, an ultrasonic transducer, and a plurality of helical grooves. The ultrasonic tool (UT) has a diameter, a UT length extending between a UT first end and a distal tool tip, and a UT exterior surface that extends around a UT circumference of the ultrasonic tool. The tapered step horn (SH) has an SH length that extends between an SH first end and an SH second end, a major diameter disposed at the SH first end, a minor diameter disposed at the SH second end, a middle diameter between the SH first end and the SH second end, and an SH exterior surface that extends around an SH circumference of the step horn. The SH second end of the step horn is connected to the UT first end of the ultrasonic tool. The ultrasonic transducer is in communication with the step horn and the ultrasonic tool. The ultrasonic transducer is controllable to ultrasonically vibrate the step horn and the ultrasonic tool. The ultrasonic tool, the step horn, and the ultrasonic transducer are disposed along the longitudinal axis. The plurality of helical grooves may be disposed in the UT exterior surface spaced apart from one another around the UT circumference, or in the SH exterior surface spaced apart from one another around the SH circumference, or both. The ultrasonic vibration caused by the ultrasonic transducer produces a composite ultrasonic vibration of the ultrasonic tool that includes a longitudinal component and a torsional component.
B23K 20/10 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating making use of vibrations, e.g. ultrasonic welding
5.
THERMOPLASTIC COMPOSITE STRUCTURE AND METHODS FOR FORMING
A method is provided during which a thermoplastic rib is arranged with a thermoplastic spar. A first flange of the thermoplastic rib is abutted against the thermoplastic spar. The first flange of the thermoplastic rib is ultrasonic welded to the thermoplastic spar using a tilted ultrasonic horn. A centerline of the tilted ultrasonic horn is angularly offset from the first flange of the thermoplastic rib by an acute angle during the ultrasonic welding.
A shape forming tool for pre-carbonization compression of a fibrous preform is provided, comprising a female forming tool, a first plug, a second plug, and a wedge, each configured to be received by a die recess of the female forming tool. A first tapered surface of the wedge is configured to engage the first plug and the second tapered surface of the wedge is configured to engage the second plug. In response to the first tapered surface of the wedge engaging the first plug and the second tapered surface of the wedge engaging the second plug, the first plug and the second plug, respectively, are configured to move laterally towards opposing sides of the female forming tool and/or vertically toward a bottom side of the female forming tool to compress the fibrous preform into a shaped body.
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/56 - Tensioning reinforcements before or during shaping
B29K 105/06 - Condition, form or state of moulded material containing reinforcements, fillers or inserts
7.
HORIZONTAL ULTRASONIC WELDING THERMOPLASTIC MATERIAL
A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aerospace component. The thermoplastic patch contacts the thermoplastic aerospace component. The thermoplastic patch is horizontal ultrasonic welded to the thermoplastic aerospace component using an ultrasonic horn.
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
B29C 65/08 - Joining of preformed partsApparatus therefor by heating, with or without pressure using ultrasonic vibrations
B29C 65/72 - Joining of preformed partsApparatus therefor by combined operations, e.g. welding and stitching
8.
AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET ASSEMBLY
An assembly is provided for an aircraft propulsion system. This assembly includes a center body, a scarfed inlet structure and an inlet passage. The scarfed inlet structure extends circumferentially about the center body. The inlet passage is radially between and formed by at least the center body and the scarfed inlet structure. A first component of the assembly is configured to rotate about an axis relative to a second component of the assembly between: (A) a first position where a metering portion of the inlet passage has a first area; and (B) a second position where the metering portion has a second area. The first component is one of the center body or the scarfed inlet structure, and the second component is the other one of the center body or the scarfed inlet structure.
A method of blind welding thermoplastic composite components is provided that includes: providing a first thermoplastic composite having a FTPC bonding surface, a second thermoplastic composite having a STPC bonding surface, and an interface layer; disposing the interface layer between the FTPC STPC bonding surfaces; applying a normal force to the outer surface of the first thermoplastic composite component; applying an electromagnetic field to at least portions of the first and second thermoplastic composite components and the interface layer while the normal force is applied, and maintaining the application of the electromagnetic field until the first and second thermoplastic composite components and the interface layer create a weld pool; and removing the application of the electromagnetic field after the weld pool is created.
B29C 65/14 - Joining of preformed partsApparatus therefor by heating, with or without pressure using wave energy or particle radiation
B29C 65/34 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
10.
METHOD AND APPARATUS FOR JOINING THERMOPLASTIC COMPOSITE COMPONENTS
A method of blind welding thermoplastic composite components is provided. The method includes providing a first and second thermoplastic composite components each having a bonding surface. The first thermoplastic composite component has a first melting temperature and the second thermoplastic composite component has a second melting temperature; providing an interface layer having a third melting temperature; disposing the interface layer between the bonding surfaces; disposing an external susceptor adjacent to the outer surface of the first thermoplastic composite component, wherein the external susceptor includes a central segment and lateral segments that respond differently to an application of an EM field; applying a normal force to the first component external susceptor without an application of an opposing second normal force to the second thermoplastic component; and applying an electromagnetic field to the central and lateral segments using an inductor.
A porosity gradient fibrous preform includes at least one first fabric-resin layer and a second fabric-resin layer, each including a plurality of fibers and a resin. The second fabric-resin layer is positioned on top of the at least one first fabric-resin layer. A weight ratio percentage of the resin sequentially decreases from a center of the porosity gradient fibrous preform toward an outer surface of the porosity gradient fibrous preform to create a path through the porosity gradient fibrous preform for infiltration of a fluid.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 37/18 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of discrete sheets or panels only
A porosity gradient fibrous preform includes a plurality of fabric-resin layers and a plurality of pore formers. Each fabric-resin layer includes a plurality of fibers and a resin. A volume of the plurality of pore formers sequentially increases from a center of the porosity gradient fibrous preform toward an outer surface of the porosity gradient fibrous preform. The pore formers can be pyrolyzed from the preform to create paths through the porosity gradient fibrous preform for infiltration of a fluid.
B29C 44/02 - Shaping by internal pressure generated in the material, e.g. swelling or foaming for articles of definite length, i.e. discrete articles
B29C 44/34 - Component parts, details or accessoriesAuxiliary operations
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
13.
POROSITY GRADIENT PREFORM ARCHITECTURE FOR HIGH TEMPERATURE COMPOSITES
A porosity gradient fibrous preform includes a first fabric-resin layer having a first plurality of fibers and a first resin and a second fabric-resin layer having a second plurality of fibers and a second resin. The second fabric-resin layer is positioned further outward from the center of the porosity gradient fibrous preform than the first fabric-resin layer. In response to the porosity gradient fibrous preform being heated to a curing temperature, the first resin and/or the second resin is configured to separate into a fusible resin and a plurality of fugitive pore formers. Accordingly, a volume of the fugitive pore formers sequentially increases from a center of the porosity gradient fibrous preform toward an outer surface of the porosity gradient fibrous preform.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
B32B 37/20 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of continuous webs only
14.
POROSITY GRADIENT PREFORM ARCHITECTURE FOR HIGH TEMPERATURE COMPOSITES
A porosity gradient fibrous preform includes a first fabric-resin layer having a first plurality of fibers and a first resin and a second fabric-resin layer having a second plurality of fibers and a second resin, the second fabric-resin layer being positioned further outward from a center of the porosity gradient fibrous preform than the first fabric-resin layer. The first resin is different from the second resin so as to generate sequentially increasing porosity in the preform prior to a CVI densification step. The sequentially increasing porosity can be achieved, for example, by selecting resins for each layer with sequentially increasing moisture content, by selecting resins for each layer with sequentially decreasing char yield, and/or adding black carbon powder to interior located fabric-resin layers.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 37/18 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of discrete sheets or panels only
A hold open rod has a control sleeve, an outer cylinder, lock balls, a lock sleeve, a piston, a piston head, a release spring, and a lock spring. The control sleeve has first and second cavity sections, an inner radial surface, a CS channel, and a pin. The outer cylinder has an OC inner cavity, OC inner and outer radial surfaces, an OC axial end wall, lock ball apertures, and a pin guide slot. The lock balls are configured to pass through the lock ball apertures. The piston has first and second sections. The piston head has an outer radial surface, a channel, and a piston bore. The piston bore is configured to receive the first section of the piston. The release spring biases the control sleeve toward a first axial end. The lock spring biases the lock sleeve toward a second axial end.
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
E05C 17/02 - Devices for holding wings openDevices for limiting opening of wings or for holding wings open by a movable member extending between frame and wingBraking devices, stops or buffers, combined therewith by mechanical means
16.
BONDING FOR HIGH-TEMPERATURE COMPOSITE APPLICATIONS
A manufacturing method is provided. The manufacturing method applies a bonding adhesive to at least one of the first surface of the first composite preform component or the first surface of the second composite preform component, and joins the first surface of the first composite preform component to the first surface of the second composite preform component.
B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
B29C 65/72 - Joining of preformed partsApparatus therefor by combined operations, e.g. welding and stitching
C09J 5/00 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers
C09J 5/02 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers involving pretreatment of the surfaces to be joined
C09J 5/06 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers involving heating of the applied adhesive
C09J 9/00 - Adhesives characterised by their physical nature or the effects produced, e.g. glue sticks
An apparatus is provided for an aircraft. This apparatus includes a latch, and the latch includes a handle, a hook structure and a linkage system operatively coupling the handle to the hook structure. The linkage system includes a mounting link, a handle link, a handle pivot member and an inter-link pivot member. The hook structure includes a hook, a structure aperture and a structure slot located longitudinally between the hook and the structure aperture. The handle link is pivotally connected to the handle. The handle pivot member is received within the structure aperture. The handle pivot member is pivotally connected the handle to the hook structure. The inter-link pivot member is received within the structure slot. The inter-link pivot member pivotally connects the mounting link and the handle link to the hook structure.
A laser perforating system includes at least one laser source and a controller. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to control the at least one laser source to form a hole in a skin by: generating a short pulse width (SPW) beam with the at least one laser source and directing the SPW beam to the skin at a hole location for the hole and generating a long pulse width (LPW) beam with the at least one laser source and directing the LPW beam to the skin at the hole location.
A tooling element includes a flexible sleeve defining an interior cavity. The flexible sleeve includes a sealable access port extending through the flexible sleeve from the interior cavity to an exterior of the flexible sleeve. The tooling element further includes vacuum-packed tooling particulate disposed within and filling the interior cavity of the flexible sleeve.
B29C 33/38 - Moulds or coresDetails thereof or accessories therefor characterised by the material or the manufacturing process
B29C 33/50 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic
B29C 33/54 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles made of powdered or granular material
An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure extending axially along and circumferentially about an axis. The nacelle inlet structure includes an inlet lip skin, an inner barrel, an outer barrel, a foam core and an acoustic structure. The inlet lip skin forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft from the inlet lip skin. The inner barrel forms a perforated face skin of the acoustic structure. The outer barrel projects axially aft from the inlet lip skin. The outer barrel is radially outboard of the inner barrel. The foam core is radially between the inner barrel and the outer barrel. The foam core axially overlaps the perforated face skin and projects axially to the inlet lip skin.
A commingled fiber preform is provided. The commingled fiber preform includes a plurality of first fabric layers and a second fabric layer. The second fabric layer is positioned on top of the plurality of first fabric layers. The second fabric layer is joined to the plurality of first fabric layers via through thickness reinforcement (TTR) using a commingled thread. A transport depth of the TTR penetrates completely through a thickness of the second fabric layer and partially through a thickness of the plurality of first fabric layers. The commingled thread comprises carbon fibers commingled with fugitive fibers. The fugitive fibers are pyrolyzed from the commingled fiber preform to create a path through the thickness for infiltration of fluids.
B32B 7/09 - Interconnection of layers by mechanical means by stitching, needling or sewing
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/03 - Layered products characterised by the relation between layers Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties Layered products characterised by the interconnection of layers with respect to the orientation of features
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
A method is provided during which a first thermoplastic composite body is arranged on a rigid support structure. The first thermoplastic composite body contacts the rigid support structure. A second thermoplastic composite body is arranged on the first thermoplastic composite body. The second thermoplastic composite body contacts the first thermoplastic composite body. Energy transmission material is arranged on the second thermoplastic composite body. The first thermoplastic composite body and the second thermoplastic composite body are disposed between the rigid support structure and the energy transmission material. The second thermoplastic composite body is ultrasonic welded to the first thermoplastic composite body using an ultrasonic horn. The energy transmission material is arranged between the second thermoplastic composite body and the ultrasonic horn.
A commingled fiber preform is provided. The commingled fiber preform includes at least one first fabric layer and a second fabric layer. The second fabric layer is positioned on top of the at least one first fabric layer. The second fabric layer is joined to the at least one first fabric layer via through thickness reinforcement (TTR) using a commingled thread. A transport depth of the TTR penetrates completely through a thickness of the second fabric layer and an entirety of the at least one first fabric layer. The commingled thread comprises carbon fibers commingled with fugitive fibers. The fugitive fibers are pyrolyzed from the commingled fiber preform to create a path through the thickness for infiltration of fluids.
B32B 7/08 - Interconnection of layers by mechanical means
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/03 - Layered products characterised by the relation between layers Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties Layered products characterised by the interconnection of layers with respect to the orientation of features
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
A preform is provided. The preform includes first fabric layers that include a first set of commingled fibers and a second set of commingled fibers. The preform includes a second fabric layer positioned between the first fabric layers. The second fabric layer includes a third set of commingled fibers and a fourth set of commingled fibers. The first set of commingled fibers includes a lower percentage of the at least one of first carbon fibers or first fusible fibers than the third set of commingled fibers, The first set of commingled fibers include a higher percentage of first fugitive fibers than the third set of commingled fibers. The first fugitive fibers and the third fugitive fibers are pyrolyzed from the first fabric layers and the second fabric layer.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 37/16 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating
B32B 38/00 - Ancillary operations in connection with laminating processes
25.
PERMEABLE CLOSED-MOLD OUT-OF-AUTOCLAVE COMPOSITE PART MANUFACTURING
A system for manufacturing a composite component is disclosed herein. The system includes a mold defining an interior space and having a conduit through the mold and into the interior space, a prepreg part configured to fit in the interior space, and a permeable media configured to fit in the interior space and around the prepreg part, wherein a vacuum is applied to the interior space through the conduit to extract volatiles from the prepreg part, through the permeable media, and out the conduit.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 33/10 - Moulds or coresDetails thereof or accessories therefor with incorporated venting means
26.
SYSTEMS AND METHODS FOR THROUGH THICKNESS REINFORCEMENT USING ROLL-TO-ROLL VEIL CLOTH
An apparatus for through thickness reinforcement of a fibrous preform includes an actuating textile needle, a feeder spool configured to supply a veil cloth, and a take up spool. The feeder spool and take up spool can rotate to cause a portion of the veil cloth to translate such that a needled portion of the veil cloth is received by the take up spool and an unneedled portion of the veil cloth is provided for subsequent needling by the textile needle. In this manner, the veil cloth is only momentarily supplied to the fibrous preform for providing the through thickness fibers and removed from the fibrous preform before subsequent processing of the fibrous preform. The textile needle, feeder spool, and take up spool can be mounted to a common apparatus (e.g., a housing) such that the entire assembly is moveable together as a single unit.
Systems and methods for through thickness reinforcement of a fibrous preform include a needle configured to move a through thickness fiber along a curved path. The needle can be moved along the curved path and can penetrate one or more plies of the fibrous preform. The needle can move one or more through thickness fibers along the curved path (e.g., from a first ply of the fibrous preform at least partially into a second ply of the fibrous preform). The needle can be moved about one or more axes during through thickness reinforcement. In various embodiments, the needle is translated along an axis, and rotated about the same axis to move the through thickness fiber(s) along the curved path.
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 5/24 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer
An assembly is provided for an aircraft. This aircraft assembly includes a keeper and a latch. The keeper includes a keeper bearing surface with a semi-spherical geometry. The latch includes a handle and a hook structure operatively coupled to the handle. The handle is configured to move between a closed position and an open position. The hook structure includes a hook bearing surface with a semi-spherical geometry. The hook bearing surface is engaged with the keeper bearing surface when the handle is in the closed position. The hook structure is disengaged from the keeper when the handle is in the open position.
An assembly for an aircraft propulsion system includes a first lip segment and a second lip segment. The first lip segment includes a first lip skin, a first mount and a first electric heater. The first mount is disposed at a first side of the first lip segment and connected to the first lip skin. The first electric heater is disposed at the first side of the first lip segment and integrated with the first lip skin. The second lip segment includes a second lip skin, a second mount and a second electric heater. The second mount is disposed at a second side of the second lip segment and connected to the second lip skin. The second mount is removably attached to the first mount. The second electric heater is disposed at the second side of the second lip segment and integrated with the second lip skin.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F01D 25/02 - De-icing means for engines having icing phenomena
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
H05B 3/18 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor the conductor being embedded in an insulating material
A pressure relief latch includes a housing, a bolt, a cam, and a spring assembly. The housing includes a door panel, a first lateral panel, and a second lateral panel. The first lateral panel and the second lateral panel extend outward from the door panel. The bolt includes a bolt body and a roller bearing. The bolt body is pivotably mounted to the first lateral panel and the second lateral panel at a bolt pivot axis. The bolt body is pivotable about the bolt pivot axis between a latched position and an unlatched position. The roller bearing is rotatably mounted to the bolt body. The cam is pivotably mounted to the first lateral panel and the second lateral panel. The spring assembly is pivotably mounted to the cam. The spring assembly is configured to bias the cam toward the bolt.
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
E05C 3/12 - Fastening devices with bolts moving pivotally or rotatively with latching action
E05C 3/30 - Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch the bolt being spring-controlled in the form of a hook
31.
HEAT TREATMENT OF FIBROUS PREFORMS VIA FLUID FLOW SYSTEMS AND METHODS
Systems and methods for performing an in-tool carbonization process including exotherm control on a fibrous preform includes one or more temperature control channels disposed in a heat treatment tooling fixture. A fluid may be moved through the temperature control channel(s) for controlling a temperature of the fibrous preform as the fibrous preform is heated during carbonization. A fluid source, a valve arrangement, and one or more heaters can be controlled for regulating a temperature and/or flow rate of fluid through the temperature control channel(s). In this manner, the fibrous preform may be uniformly brought to an exotherm temperature range such that shrinking of the fibrous preform occurs simultaneously and uniformly throughout the fibrous preform. The temperature control channels can be grouped by geographic location for zoned temperature control. The carbonization process can be performed using a single composite fixture or using both metallic and composite fixtures.
Systems and methods for controlling exotherms in a fibrous preform during carbonization include one or more temperature control channels disposed in a heat treatment tooling fixture. A fluid may be moved through the temperature control channel(s) for controlling a temperature of the fibrous preform as the fibrous preform is heated during carbonization. A fluid source and a valve arrangement may be controlled for regulating a flow of fluid through the temperature control channel(s). In this manner, the fibrous preform may be uniformly brought to a temperature range such that shrinking of the fibrous preform occurs simultaneously and uniformly throughout the fibrous preform.
A method for forming a fiber reinforced thermoplastic part may comprise the steps of locating a thermoplastic material over a mold tool, heating the thermoplastic material to a pliable forming temperature, conforming the thermoplastic material to a mold surface of the mold tool, and depositing a plurality of fiber strips over the thermoplastic material.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/10 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns oriented
An apparatus is provided for an aircraft. This apparatus includes a latch. The latch includes a handle, a hook structure and a linkage system operatively coupling the handle to the hook structure. The linkage system includes a back link, a center link, a back link pivot member and a center link pivot member. The hook structure includes a hook, a structure aperture and a structure slot located longitudinally between the hook and the structure aperture. The back link is pivotally coupled to the center link. The back link pivot member is received within the structure aperture and pivotally couples the back link to the hook structure. The center link pivot member is received within the structure slot and pivotally couples the handle and the center link together and to the hook structure.
A thrust reverser includes a fixed thrust reverser structure, a translating sleeve, and a blocker door assembly. The fixed thrust reverser structure includes a wall. The translating sleeve is configured to translate between a first stowed translating sleeve position and a second translating sleeve position. The blocker door assembly includes a plurality of blocker doors. Each blocker door of the plurality of blocker doors includes a blocker door body, at least one hinge, and a blocker door retention assembly. The blocker door body is pivotable about a hinge line of the at least one hinge between a first stowed blocker door position and a second blocker door position. The blocker door retention assembly includes a first retention body fixedly mounted to the wall or to the translating sleeve. The first retention body is configured to support the blocker door body in the first stowed blocker door position.
F02K 1/76 - Control or regulation of thrust reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
36.
WEIGHT BALANCED ROTOR BLADE WITH THERMOPLASTIC COMPOSITE WEIGHT
A rotor blade is provided that includes an airfoil extending spanwise from a base to a tip. The airfoil extends longitudinally (e.g., chordwise) from a leading edge to a trailing edge. The airfoil extends laterally between a first side and a second side. The airfoil includes a body and a weight. The body includes a plurality of body layers. Each of the body layers includes fiber reinforcement within a body thermoplastic matrix. The weight includes a weight layer embedded within the body. The weight layer includes metal powder within a weight thermoplastic matrix.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
An assembly is for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, a linkage mount and an actuation linkage. The blocker door is pivotally coupled to the translating structure. The linkage mount includes a mount link, a mount spring and a mount stop. The mount link is pivotally coupled to the fixed structure about a pivot axis. The mount spring is configured to bias the mount link about the pivot axis against the mount stop. The actuation linkage operatively couples the blocker door to the mount link.
An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, an actuation linkage and a door lock. The blocker door is pivotally coupled to the translating structure. The actuation linkage operatively couples the blocker door to the fixed structure such that translation of the translating structure to the deployed position actuates pivoting of the blocker door into a flowpath. The door lock is configured to lock the actuation linkage to the translating structure such that the pivoting of the blocker door into the flowpath is delayed as the translating structure translates from the stowed position towards the deployed position.
An assembly for an aircraft propulsion system includes a fixed structure, a translating structure and a thrust reverser. The thrust reverser includes a blocker door, a door link and a structure link. The blocker door is pivotally coupled to the translating structure. The door link includes a first door link arm, a second door link arm and a door link mount connected to the first door link arm and the second door link arm. The first door link arm and the second door link arm are each pivotally coupled to the blocker door. The first door link arm and the second door link arm laterally converge towards one another as the first door link arm and the second door link arm extend longitudinally towards the door link mount. The structure link extends longitudinally between and is pivotally coupled to the door link mount and the fixed structure.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
40.
FIRE RETARDANT THERMOPLASTIC COMPOSITE AND METHOD FOR FORMING SAME
A method for forming a fire-retardant thermoplastic composite panel includes mixing a thermoplastic polymer with a fire-retardant additive to form a fire-retardant polymer composition and assembling a composite layup of a plurality of first layers and a plurality of second layers by alternatingly positioning the plurality of first layers and the plurality of second layers with each first layer including a fire-retardant polymer composition film of the fire-retardant polymer composition and each second layer including a carbon-fiber fabric. The method further includes compression molding the composite layup to form the fire-retardant thermoplastic composite panel.
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B29C 43/00 - Compression moulding, i.e. applying external pressure to flow the moulding materialApparatus therefor
B29C 43/20 - Making multilayered or multicoloured articles
B29C 48/00 - Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired formApparatus therefor
B29C 48/08 - Flat, e.g. panels flexible, e.g. films
B29K 71/00 - Use of polyethers as moulding material
B29K 105/00 - Condition, form or state of moulded material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 27/18 - Layered products essentially comprising synthetic resin characterised by the use of special additives
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
41.
COMPOSITE PROPULSION SYSTEM CASE AND METHOD FOR FORMING SAME
A method for forming a composite propulsion system case includes providing a liner, bonding a thermoplastic film layer to the liner using an adhesive, and, subsequent to bonding the thermoplastic film layer to the liner, depositing a thermoplastic composite material onto the thermoplastic film layer to form an outer shell of the composite propulsion system case. The outer shell extends circumferentially about an axial centerline of the composite propulsion system case. The outer shell forms an outer radial surface of the composite propulsion system case.
B64D 27/02 - Aircraft characterised by the type or position of power plants
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 25/08 - Layered products essentially comprising natural or synthetic rubber comprising rubber as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B32B 25/10 - Layered products essentially comprising natural or synthetic rubber next to a fibrous or filamentary layer
B32B 25/16 - Layered products essentially comprising natural or synthetic rubber comprising polydienes or poly-halodienes
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
42.
Spring guided hand actuator for aircraft component
An assembly is provided for an aircraft. This aircraft assembly includes an actuator and a cable assembly. The actuator includes a support structure, a handle structure and a guide system configured to guide movement of the handle structure longitudinally along the support structure between a first position and a second position. The guide system includes a first guide element and a second guide element. The first guide element includes a first spring element and is pivotally coupled to the handle structure at a handle structure pivot axis. The second guide element includes a second spring element and is pivotally coupled to the handle structure at the handle structure pivot axis. The cable assembly includes a sleeve and a cable projecting longitudinally out of the sleeve. The sleeve is attached to the support structure. The cable is coupled to the handle structure.
G05G 1/02 - Controlling members for hand-actuation by linear movement, e.g. push buttons
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
G05G 5/05 - Means for returning or tending to return controlling members to an inoperative or neutral position, e.g. by providing return springs or resilient end-stops
43.
MANUFACTURING THERMOPLASTIC CONTAINER WITH INTERNAL BAFFLE(S)
A method is provided for manufacturing a container. During this method, a baffle is provided. The baffle is configured from or otherwise includes baffle thermoplastic material. A sidewall is formed using an additive manufacturing device. The sidewall is bonded to the baffle during the forming of the sidewall. The sidewall circumscribes the baffle. The sidewall is configured from or otherwise includes sidewall thermoplastic material. The container includes an internal chamber, the baffle and the sidewall. The sidewall forms an outer peripheral boundary of the internal chamber. The baffle is arranged within the internal chamber.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 33/52 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
B29C 64/188 - Processes of additive manufacturing involving additional operations performed on the added layers, e.g. smoothing, grinding or thickness control
B29C 64/268 - Arrangements for irradiation using laser beamsArrangements for irradiation using electron beams [EB]
B29C 64/40 - Structures for supporting 3D objects during manufacture and intended to be sacrificed after completion thereof
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
A method may comprise: laying up a first plurality of plies of material comprising thermoplastic resin and fiber to form an inner skin preform, the inner skin preform being a continuous sheet including alternating peaks and valleys; laying up a second plurality of plies of material comprising thermoplastic resin and fiber to form an outer skin preform; and joining the inner skin preform to the outer skin preform.
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
An acoustic panel is provided that includes a perforated first skin, a second skin and a core. The core is between and connected to the perforated first skin and the second skin. The core includes a plurality of chambers, a first corrugated structure and a second corrugated structure. The chambers includes a first chamber. The first chamber extends from the perforated first skin, through the first corrugated structure and the second corrugated structure, to the second skin.
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 3/28 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer comprising a deformed thin sheet, e.g. corrugated, crumpled
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
A propulsion system of an aircraft includes a hybrid electric gas turbine engine, and a nacelle at least partially enclosing the hybrid electric gas turbine engine. The nacelle includes a first nacelle half and a second nacelle half. Each of the first nacelle half and the second nacelle half include an outer nacelle sleeve, an inner nacelle sleeve radially offset from the outer nacelle sleeve such that a flowpath is defined between the outer nacelle sleeve and the inner nacelle sleeve, and an upper bifurcation connecting the outer nacelle sleeve to the inner nacelle sleeve at an upper end of the nacelle. The flowpath is circumferentially continuous between the upper bifurcation of the first nacelle half and the upper bifurcation of the second nacelle half.
An apparatus for non-destructive testing of a component is disclosed herein. The apparatus comprises a robotic arm, a probe holder, a probe connected to the robotic arm via the probe holder, and a controller configured to move the robotic arm to move the probe over a surface of a component to be tested. The probe holder comprises a spring assembly for biasing the probe towards the surface of the component to be tested to keep the probe in contact therewith. The spring assembly comprises at least one pair of spring portions that are spaced apart along a first axis.
G01N 29/265 - Arrangements for orientation or scanning by moving the sensor relative to a stationary material
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details
A system is provided for an aircraft. This aircraft system includes an aircraft wing extending spanwise from a wing base to a wing tip. The aircraft wing extends chordwise from a leading edge to a trailing edge. The aircraft wing extends laterally between a first surface and a second surface. The aircraft wing includes a first section, a second section and a third section. The second section extends spanwise between and connects the third section and the first section. The second section is pivotally connected to first section at a first hinge line. The third section is pivotally connected to the second section at a second hinge line that is angularly offset from the first hinge line by a first acute angle.
A modular tooling arrangement includes a base member comprising a planar working surface, a frame circumscribing a first cavity at least partially defined by the planar working surface, and a plurality of plates configured to be received in the first cavity for forming a second cavity of a desired shape and size. The plurality of plates at least partially define the second cavity configured to receive a work piece. The plurality of plates may be replaced with plates of various sizes to vary at least one of the size and shape of the second cavity.
B29C 33/38 - Moulds or coresDetails thereof or accessories therefor characterised by the material or the manufacturing process
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
An anti-icing system for an aircraft nacelle structure is provided that includes a controllable PRSOV, a circumferentially extending duct, a bleed air duct segment, at least one PRV, and a controller. The PRSOV may be disposed in a closed or an open configuration. The PRV is disposed downstream of the PRSOV and in fluid communication with the bleed air duct segment. The PRV may be disposed in a closed or in an open configuration. The controller is in communication with a memory storing instructions. The instructions when executed cause the system controller to control the PRSOV to maintain bleed air within the anti-icing system within a predetermined range of operating pressures by selectively controlling the PRSOV into at least one of the one or more PRV open configurations, and control the PRV to open to maintain the bleed air below the maximum pressure.
An air inlet for an aircraft propulsion system nacelle includes an outer skin, an inner skin, a lip skin, and a forward bulkhead. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The forward bulkhead includes a first bulkhead portion and a second bulkhead portion. The first bulkhead portion and the second bulkhead portion are mounted to the outer skin. The first bulkhead portion and the second bulkhead portion are mounted to the inner skin. The first bulkhead portion includes a rigid body material and the second bulkhead portion includes a flexible body material.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
An air inlet section for an aircraft propulsion system nacelle includes an outer skin, an inner skin, and a lip skin. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The lip skin forms an exterior lip skin surface extending from the inner end to the outer end. The exterior lip skin surface forms a leading edge of the lip skin. The exterior lip skin surface includes an outer surface portion and an inner surface portion. The outer surface portion extends from the outer end to the inner surface portion. The outer surface portion forms a hydrophobic surface. The inner surface portion extends from the inner end to the outer surface portion. The inner surface portion forms a hydrophilic surface.
A door assembly for an aircraft includes a door, a door hinge, and a support assembly rotatably mounting the door hinge to the door. The support assembly includes a forearm and at least one link. The forearm is rotatably mounted to the door hinge along a first rotational axis. The forearm extends along the first rotational axis between and to an upper end and a lower end. The at least one link extends between and to an inner end and an outer end. The at least one link is rotatably mounted to the forearm at the inner end. The at least one link is rotatable relative to the forearm about a second rotational axis. The at least one link is rotatably mounted to the door at the outer end. The at least one link is rotatable about the second rotational axis between and to a lowered position of the door and a raised position of the door.
An interlock assembly for an aircraft door includes a shaft, an interlock first portion, and an auto-disarm second portion. The shaft is rotatable about the second rotational axis between an armed position and a disarmed position. The shaft includes an interlock cam and an auto-disarming cam. In a first interlock position, the interlock first portion permits rotation of the shaft between the armed position and the disarmed position. In a second interlock position, the interlock first portion prevents rotation of the shaft from the disarmed position to the armed position. In a first auto-disarm position, the auto-disarm second portion permits rotation of the shaft between the armed position and the disarmed position. In a second auto-disarm position, the auto-disarm second portion prevents rotation of the shaft from the disarmed position to the armed position.
A door assembly for an aircraft includes a door, a door handle, a door hinge, a support assembly, and a lifting assembly. The door handle is rotatable between an unlatched position and a latched position. The support assembly rotatably mounts the door hinge to the door. The lifting assembly includes a latch cam, a lift track, and a latch idler. The latch cam is mounted to the door handle. The latch cam is rotatable with the door handle about the door handle rotational axis. The latch cam forms an eccentric roller path extending about the door handle rotational axis. The latch idler includes a first roller and a second roller. The first roller is disposed on a lift track of the support assembly and configured to roll along the lift track. The second roller is disposed within the eccentric roller path. The latch idler is mounted to the door. The latch idler is configured to lift the door as the door handle rotates from the latched position to the unlatched position.
E05F 7/02 - Accessories for wings not provided for in other groups of this subclass for raising wings before being turned
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
E05F 11/16 - Mechanisms by which the bar shifts the wing shifting the wing by pivotally-connected members moving in a plane perpendicular to the pivot axis of the wing
A door assembly for an aircraft includes a door, an interior door handle and an exterior door handle, and a clutch assembly. The interior door handle and the exterior door handle are rotatable about a door handle rotational axis. The clutch assembly includes a shaft, an exterior coupling body, an exterior handle body, and a clutch lever. The shaft includes an interface portion. The interface portion includes a handle tooth. The exterior coupling body includes a fixed body portion disposed adjacent the interface portion. The exterior handle body is rotatably mounted to the exterior coupling body. The exterior handle body is rotatable between and to an engaged position and a disengaged position. The clutch lever is rotatably mounted to the exterior coupling body. The clutch lever is pivotable between and to an engaged pivot position and a disengaged pivot position. In the engaged pivot position, the handle tooth is positioned circumferentially between the clutch lever and the fixed body portion.
A preform tooling arrangement includes a base plate comprising a male die surface and a stripper plate comprising a female die surface. A plurality of perforations are disposed in the base plate and/or the stripper plate. The stripper plate is moveable with respect to the base plate. The preform tooling arrangement is configured to receive a fibrous preform between the male die surface and the female die surface. The preform tooling arrangement is a dual-purpose fixture configured to accommodate z-needling and densification, all while the fibrous preform remains in the same fixture (i.e., the preform tooling arrangement). The perforations are configured to receive one or more textile needles for through thickness reinforcement of the fibrous preform.
B28B 23/22 - Arrangements specially adapted for the production of shaped articles with elements wholly or partly embedded in the moulding material wherein the elements are reinforcing members assembled from preformed parts
B28B 7/16 - Moulds for making shaped articles with cavities or holes open to the surface
B28B 7/34 - Moulds, cores, or mandrels of special material, e.g. destructible materials
A method is provided for manufacturing during which a first duct section is formed with a tubular first sidewall. A first opening extends through the tubular first sidewall. The forming of the first duct section includes disposing a first woven fiber sleeve over a first mandrel and disposing a polymer material with the first woven fiber sleeve. A second duct section is disposed with a tubular second sidewall. The forming of the second duct section includes disposing a second woven fiber sleeve over a second mandrel and disposing the polymer material with the second woven fiber sleeve. The second duct section is arranged with the first duct section. The second duct section engages the tubular first sidewall. The tubular second sidewall is located at and extends circumferentially around the first opening. A duct structure is formed by attaching the second duct section to the first duct section.
An assembly is provided for an aircraft propulsion system. This assembly includes a variable area inlet, and the variable area inlet includes an inlet structure, an inlet lip, an inlet orifice and an inlet passage extending within the variable area inlet from the inlet orifice. The inlet lip is configured to pivot about a pivot axis between a first position and a second position. The inlet orifice is formed by and between the inlet structure and the inlet lip. The inlet orifice has a first area when the inlet lip is in the first position. The inlet orifice has a second area when the inlet lip is in the second position. The second area is different than the first area.
A method is provided for manufacturing. During this method, a first woven fiber sleeve is disposed over a first mandrel to provide a first overbraided mandrel. The first woven fiber sleeve is wrapped circumferentially around the first mandrel. An opening is formed through a side of the first woven fiber sleeve. A second woven fiber sleeve is disposed over a second mandrel to provide a second overbraided mandrel. The second woven fiber sleeve is wrapped circumferentially around the second mandrel. The second overbraided mandrel is arranged with the first overbraided mandrel. The second woven fiber sleeve engages the side of the first woven fiber sleeve. A second overbraid first end is disposed at and extends circumferentially around the opening. A polymer material is disposed with the first woven fiber sleeve and the second woven fiber sleeve to provide a duct structure.
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
61.
ENGINE EXHAUST CENTER BODY WITH ACOUSTIC ATTENUATION
An exhaust center body includes an inner skin, a perforated outer skin, a first bulkhead, a second bulkhead, a baffle and an acoustic chamber. The first bulkhead extends radially between the inner skin and the perforated outer skin. The second bulkhead extends radially between the inner skin and the perforated outer skin. The baffle includes a panel and a flange formed integral with the panel. The panel extends radially between the inner skin and the perforated outer skin. The panel extends axially along the axial centerline between the first bulkhead and the second bulkhead. The panel is attached to one of the inner skin, the first bulkhead or the second bulkhead by the flange. The acoustic chamber is formed radially between the inner skin and the perforated outer skin, axially between the first bulkhead and the second bulkhead, and circumferentially adjacent the baffle.
F02K 1/34 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
During a manufacturing method, a first thermoplastic body is arranged with a second thermoplastic body. The first thermoplastic body and/or the second thermoplastic body includes a plurality of fibers embedded within a thermoplastic matrix. The fibers include a plurality of parallel first fibers and a plurality of parallel second fibers that are angularly offset from the parallel first fibers. A conductive element is arranged vertically next to a surface of the first thermoplastic body. The first thermoplastic body is induction welded to the second thermoplastic body using the conductive element. The conductive element includes a first segment and a second segment. The first segment is at least substantially parallel with the plurality of parallel first fibers. The second segment is at least substantially parallel with the plurality of parallel second fibers. A first portion of the conductive element is vertically above and overlaps a second portion of the conductive element.
B29C 65/36 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
B29C 65/00 - Joining of preformed partsApparatus therefor
63.
METHOD OF REPAIRING THERMOPLASTIC COMPOSITE COMPONENTS WITH MANUAL ULTRASONIC WELD
A method for repairing a thermoplastic composite component is provided that includes: preparing at least one repair patch configured to conform with a defect region of the thermoplastic composite component, the defect region having a periphery that defines the defect region, the at least one repair patch comprising a thermoplastic composite material; providing a thermoplastic interface film configured to conform with at least a part of the at least one repair patch, the thermoplastic interface film having a melt temperature; disposing the thermoplastic interface film between a surface of the thermoplastic composite component disposed at the periphery of the defect region and the at least one repair patch; and heating the thermoplastic interface film to its melt temperature using an ultrasonic welder, and subsequently allowing the thermoplastic interface film to cool, thereby welding the at least one repair patch to the thermoplastic composite component.
B29C 73/34 - Apparatus or accessories not otherwise provided for for local pressing or local heating for local heating
B29C 65/08 - Joining of preformed partsApparatus therefor by heating, with or without pressure using ultrasonic vibrations
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
64.
METHOD OF ULTRASONIC WELDING THERMOPLASTIC COMPOSITE COMPONENTS
A method for welding thermoplastic composite components is provided that includes: providing a first thermoplastic composite component having a first weld region surface; providing a second thermoplastic composite component having a second weld region surface; disposing the first and second weld region surfaces in stationary contact with one another; ultrasonically welding the first and second thermoplastic composite components using a ultrasonic welding device having a sonotrode that linearly reciprocates, the welding including contacting an engagement surface of the first or second thermoplastic composite component with the sonotrode and reciprocating the sonotrode along a travel axis that is parallel to the first and second weld region surfaces until at least one of the first or second thermoplastic material reaches a melt temperature; and then maintaining the first and second weld region surfaces stationary until cooled.
B29C 65/08 - Joining of preformed partsApparatus therefor by heating, with or without pressure using ultrasonic vibrations
B29C 65/34 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
65.
LATCH ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM COWL
A cowl assembly for an aircraft propulsion system includes a first cowl door, a second cowl door, and a latch system. The first cowl door is pivotable. The second cowl door is pivotable. The latch system includes at least one latch assembly and a latch indicator light assembly. The at least one latch assembly includes a first latch assembly portion and a second latch assembly portion. The first latch assembly portion is disposed on the first cowl door. The second latch assembly portion is disposed on the second cowl door. The latch system is configured to energize the latch indicator light assembly to direct a latch indicator light with one or more of the at least one latch assembly in the unlatched condition and deenergize the latch indicator light assembly with each of the at least one latch assembly in the latched condition.
A method is provided for manufacturing. This method includes: providing a first skin; providing a second skin; overmolding a cellular core onto the first skin; and joining the second skin to the cellular core to form a blocker door panel for an aircraft thrust reverser system. The blocker door panel includes a plurality of acoustic chambers and a face skin. Each of the acoustic chambers extends through the cellular core from the first skin to the second skin. Each of the acoustic chambers is fluidly coupled with one or more perforations through the face skin. The face skin includes one of the first skin or the second skin.
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
67.
THERMOPLASTIC COMPOSITE COMPONENT WITH VIBRATION WELDED NON-PARALLEL SURFACES AND METHOD FOR PRODUCING THE SAME
A method for joining thermoplastic composite includes: providing a first part having a first joining surface disposed in a first plane and a second joining surface disposed in a second plane that is non-parallel to the first plane; providing a second part having a third joining surface disposed in the first plane and a fourth joining surface disposed in the second plane; disposing the parts so that the first and third joining surfaces are in contact with one another, and the second and fourth joining surfaces are in contact with one another; forcing the second and fourth joining surfaces against one another; and welding the first and third joining surfaces together using a vibration welding process, wherein the welding process and the forcing of the second and fourth joining surfaces against one another causes the second and fourth joining surfaces to be welded.
A method is provided for manufacturing. During this method, a woven fiber sleeve is disposed over a mandrel to provide an overbraided mandrel. The woven fiber sleeve includes a base section and a mount section. The base section is wrapped circumferentially around the mandrel and extends longitudinally along the mandrel between a first end and a second end. The mount section is disposed longitudinally at an intermediate location between the first end and the second end. The mount section projects out from the base section. The overbraided mandrel is arranged with tooling. A polymer material is disposed with the woven fiber sleeve to provide a duct structure. The duct structure includes a tubular duct and an annular flange. The tubular duct is formed by the base section. The annular flange is formed by the mount section.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
F16L 9/133 - Rigid pipes of plastics with or without reinforcement the walls consisting of two layers
F16L 9/19 - Multi-channel pipes or pipe assemblies
An apparatus is provided for an aircraft propulsion system. This apparatus includes a duct structure, and the duct structure includes a transition duct, an inlet duct and a bypass duct. The duct structure is configured as a monolithic body. The transition duct includes an inlet, a first outlet and a second outlet. The transition duct extends longitudinally along a longitudinal centerline from the inlet to the second outlet. The first outlet is arranged longitudinally along the longitudinal centerline between the inlet and the second outlet. A centerline axis of the first outlet is angularly offset from the longitudinal centerline. The inlet duct extends longitudinally along the longitudinal centerline to the inlet. The bypass duct extends longitudinally along the longitudinal centerline from the second outlet.
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
70.
Systems and methods for rotary tensioning of fibrous preforms
A shape forming tool for pre-carbonization compression of a fibrous preform is provided, comprising a female forming tool, a first plug, a second plug, and a wedge, each configured to be received by a die recess of the female forming tool. A first tapered surface of the wedge is configured to engage the first plug and the second tapered surface of the wedge is configured to engage the second plug. In response to the first tapered surface of the wedge engaging the first plug and the second tapered surface of the wedge engaging the second plug, the first plug and the second plug, respectively, are configured to move laterally towards opposing sides of the female forming tool and/or vertically toward a bottom side of the female forming tool to compress the fibrous preform into a shaped body.
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/56 - Tensioning reinforcements before or during shaping
B29K 105/06 - Condition, form or state of moulded material containing reinforcements, fillers or inserts
71.
Welding assembly and method using separately actuatable rams
A welding assembly is disclosed. The welding assembly includes a plurality of separately controllable actuators (e.g., pneumatic, having an axially movable ram) to press a corresponding portion of a first workpiece (e.g., a discrete flange of a first stiffener) against a second workpiece (e.g., an outer skin) for welding operations (e.g., via induction welding).
A hybrid mandrel for forming a composite part may comprise a core and a sleeve located around the core. The core may include a rigid material. The sleeve may comprise an elastomeric material. The part may be formed by locating the hybrid mandrel in an injection mold, depositing a molten resin around the hybrid mandrel, curing the molten resin; and removing the hybrid mandrel.
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 33/50 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic
B29C 33/52 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B64D 29/00 - Power-plant nacelles, fairings or cowlings
A center plug for attenuating noise in a gas turbine engine includes an inner skin, a forward bulkhead, and aft bulkhead, and a noise attenuation panel. The inner skin has a substantially cylindrical shape and extending along an axial centerline. The forward bulkhead is disposed proximate a forward end of the inner skin. The forward bulkhead is connected to and extends radially outward from the inner skin. The aft bulkhead is disposed proximate an aft end of the inner skin. The aft bulkhead is connected to and extending radially outward from the inner skin. The noise attenuation panel is positioned intermediate the inner skin and partially divides a region bounded by the inner skin, the forward bulkhead and the aft bulkhead into.
A center plug includes an inner skin, the inner skin extending along an axial centerline; an outer skin positioned radially outside the inner skin; a forward bulkhead connected to and extending radially outward from the inner skin; an aft bulkhead connected to and extending radially outward from the inner skin; and an acoustic panel, the acoustic panel including a first sheet having a first plurality of perforated walls and a first plurality of non-perforated walls, a second sheet having a second plurality of perforated walls and a second plurality of non-perforated walls, the first sheet being sandwiched together with the second sheet to form an N-shaped structure having a combined plurality of perforated walls and a combined plurality of non-perforated walls.
A method is provided for forming a thermoplastic structure. During this method, a substrate is provided. The substrate includes a substrate thermoplastic and a plurality of substrate fibers disposed within the substrate thermoplastic. The substrate fibers are arranged in a substrate pattern. A first layer is deposited on the substrate using an automated fiber placement device. The first layer includes a first layer thermoplastic and a plurality of first layer fibers disposed within the first layer thermoplastic. The first layer fibers are arranged in a first layer pattern that is different than the substrate pattern. A blank is stamped into the thermoplastic structure. The blank includes the substrate and the first layer where the first layer thermoplastic is consolidated with the substrate thermoplastic.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
76.
SYSTEMS AND METHODS FOR SELECTIVE NEEDLING OF FIBROUS PREFORMS FOR SHAPE-FORMING
A method for selective needling on a fibrous preform includes performing a through thickness reinforcement process on the fibrous preform and varying a needle density, a needle angle, and/or a needle penetrating depth during the through thickness reinforcement process such that a first needle density, a first needle angle, and/or a first needle penetrating depth of a first zone of the fibrous preform is greater than a second needle density, a second needle angle, and/or a second needle penetrating depth of a second zone of the fibrous preform. The method can further include identifying expected interlaminar stress throughout the fibrous preform and varying the needle density, needle angle, and/or needle penetrating depth in accordance with a magnitude of the expected interlaminar stress.
An anti-icing system includes a nozzle assembly, a bleed air supply, a bleed control valve assembly, and a controller. The bleed air supply is configured to direct pressurized bleed air to the nozzle assembly. The bleed air supply includes a first pressure sensor configured to measure a first pressure of the pressurized bleed air. The bleed control valve assembly includes a control valve and a valve actuator. The control valve is positionable to control a flow rate of the pressurized bleed air. The valve actuator is configured to control a position of the control valve. The controller is configured to identify a power condition of the bleed air supply as a first power condition or a second power condition and control the valve actuator to position the control valve in a fully opened position for the first power condition and in a predetermined position based on the first pressure for the second power condition.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
78.
EXPANDABLE MALE DIE BLADDER FOR MATCH DIE SHAPE-FORMING SYSTEMS AND METHODS
A shape forming tool for pre-carbonization compression of a fibrous preform includes a female forming tool comprising a die recess, a support structure moveable with respect to the female forming tool, and at least one bladder coupled to the support structure and configured to be received into the die recess. The support structure is configured to move the bladder(s) with respect to the female forming tool. The bladder(s) is/are configured to be inflated to apply a compressive force to compress and form a fibrous preform between the bladder(s) and the female forming tool.
A shape forming tool for pre-carbonization compression of a fibrous preform includes a female forming tool comprising a die recess, a first die half configured to be received by the die recess, a second die half configured to be received by the die recess, an expander tool coupled between the first die half and the second die half. The expander tool is configured to move the first die half laterally toward a first side of the female forming tool away from the second die half to compress the fibrous preform between the first die half and the female forming tool. The expander tool is further configured to move the second die half laterally toward a second side of the female forming tool away from the first die half to compress the fibrous preform between the second die half and the female forming tool.
A manufacturing method is provided. A preform is arranged over a surface of an inner mold line. The preform is folded over sides of the inner mold line. An end of the preform is clamped to a floating plate using a bladder-activated clamp. The floating plate is translated in a first direction to tension the preform into a shaped body. A plurality of compressing bladders are activated to apply compressive forces to the preform.
A manufacturing method is provided. The manufacturing method arranges a first surface of a first composite preform component to align with a first surface of a second composite preform component; attaches the first surface of the first composite preform component to the first surface of the second composite preform component to form a complex composite structure; and densifies the complex composite structure as one, complete complex composite structure.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
An end effector for the through thickness reinforcement of a fibrous preform includes a plurality of spray nozzles configured to direct a needle cleaning fluid to a needle to clean resin from the needle between through thickness reinforcement operations. The plurality of spray nozzles may extend from a presser foot toward the needle. The needle cleaning fluid may contact the needle while the needle or the presser foot move (e.g., translate and/or rotate) with respect to the other of the needle or the presser foot. The plurality of spray nozzles can be incorporated into the end effector. The plurality of spray nozzles can be incorporated into a needle cleaning station into which a portion of the robotic end effector can be moved for cleaning the needles.
An end effector for needling a fibrous preform includes a body (or head), a plurality of articulating presser feet mounted to the body and moveable with respect to the body, and a plurality of articulating needles mounted to the body and moveable with respect to the body. The needles may be configured to move between an extended position and a retracted position. The presser feet may be configured to move between an extended position and a retracted position. The end effector presser feet may conform to complex geometries of a fibrous preform. The end effector may control needling depth, needling density, applied tension and/or pressure on the fibrous preform, and needle angle.
An end effector for the through thickness reinforcement of a fibrous preform includes a needle cleaning material configured to contact a needle to clean resin from the needle during or between through thickness reinforcement operations. The needle cleaning material may extend from a presser foot toward the needle. The needle cleaning material may slidingly engage the needle in response to movement of one of the needle or the presser foot moving (e.g., translating and/or rotating) with respect to the other of the needle or the presser foot.
A method is provided for manufacturing a container. During this method, a baffle is provided. The baffle is configured from or otherwise includes baffle thermoplastic material. A sidewall is formed using an additive manufacturing device. The sidewall is bonded to the baffle during the forming of the sidewall. The sidewall circumscribes the baffle. The sidewall is configured from or otherwise includes sidewall thermoplastic material. The container includes an internal chamber, the baffle and the sidewall. The sidewall forms an outer peripheral boundary of the internal chamber. The baffle is arranged within the internal chamber.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 33/52 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
B29C 64/188 - Processes of additive manufacturing involving additional operations performed on the added layers, e.g. smoothing, grinding or thickness control
B29C 64/268 - Arrangements for irradiation using laser beamsArrangements for irradiation using electron beams [EB]
B29C 64/40 - Structures for supporting 3D objects during manufacture and intended to be sacrificed after completion thereof
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
An apparatus is provided for an aircraft propulsion system. This apparatus includes a pivoting door thrust reverser system, and the pivoting door thrust reverser system includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot about a respective pivot axis between a stowed position and a deployed position. The thrust reverser doors include a first thrust reverser door and a second thrust reverser door. The second thrust reverser door is arranged to an opposing side of the pivoting door thrust reverser system from the first thrust reverser door. The pivot axis of the first thrust reverser door is angularly offset from a reference line by an acute angle. The reference line is coincident with and perpendicular to a centerline of the pivoting door thrust reverser system.
An Internet-based application allows a customer service trainee to record a performance of a scene containing roles A and B with performers for the scene's roles alternately speaking their respective lines. The lines are displayed in a teleprompter style, and based on the experience level of the trainee, the system may blank out increasing portions of the lines. The system will present each role A line to be spoken by the trainee with a time progress bar indicating the speed/timing or time remaining for that line. A “Next” button may be provided thereby allowing the trainee to depart from the progress bar timing. The teleprompter timer ensures that the trainee's recorded performance is coordinated with a take of role B, even though the trainee's take and the role B take are recorded at different times. The takes are played in tandem for evaluating effectiveness of the training.
A manufacturing method is provided. A first end of a set of spars is coupled to a first skin of a flight control surface. A set of ribs is interlocked with the set of spars and a first end of the set of ribs is coupled to the first skin. A second skin is coupled to a second end of the set of spars and a second end of the set of ribs.
An assembly is provided for an aircraft. This assembly includes a variable area inlet for an aircraft propulsion system. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage and an outer inlet passage. The inlet door is configured to move outward from a closed position to an open position. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends into the inlet structure to the inner inlet passage.
An assembly is provided for an aircraft. This assembly includes a variable area inlet for an aircraft propulsion system. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage and an outer inlet passage. The inlet door is configured to move outward from a closed position to an open position. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends into the inlet structure to the inner inlet passage.
F02K 3/04 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type
B64D 29/00 - Power-plant nacelles, fairings or cowlings
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
F02C 7/042 - Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
91.
AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET
An assembly is provided for an aircraft propulsion system. This assembly includes a variable area inlet, and the variable area inlet includes an inlet structure, an inlet lip, an inlet orifice and an inlet passage extending within the variable area inlet from the inlet orifice. The inlet lip is configured to pivot about a pivot axis between a first position and a second position. The inlet orifice is formed by and between the inlet structure and the inlet lip. The inlet orifice has a first area when the inlet lip is in the first position. The inlet orifice has a second area when the inlet lip is in the second position. The second area is different than the first area.
F02K 3/04 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type
B64D 29/00 - Power-plant nacelles, fairings or cowlings
B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
F02C 7/042 - Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
An assembly is provided for a gas turbine engine. This engine assembly includes an exhaust nozzle extending circumferentially about an axial centerline. The exhaust nozzle extends axially along the axial centerline to a trailing edge. The exhaust nozzle extends radially between an exterior inner surface and an exterior outer surface. The exhaust nozzle includes an inner skin, an outer skin and an internal cavity. The inner skin forms the exterior inner surface and includes a plurality of perforations. The internal cavity is disposed radially between the inner skin and the outer skin. The internal cavity is fluidly coupled with the perforations.
A centerbody assembly includes a center tube, a forward bulkhead, an aft bulkhead, at least one baffle, and an outer skin. The center tube extends circumferentially about an axial centerline. The center tube extends between and to a first axial tube end and a second axial tube end. The forward bulkhead is mounted to the center tube at the first axial tube end. The aft bulkhead is mounted to the center tube at the second axial tube end. The at least one baffle extends axially from the forward bulkhead to the aft bulkhead. At least the forward bulkhead, the aft bulkhead, or the at least one baffle include one or more thermal beads. The outer skin circumscribes the center tube, the forward bulkhead, the aft bulkhead, and the at least one baffle to form an acoustic cavity radially inside the outer skin.
F02K 1/34 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
A latch includes a handle, a hook, a first link, and a second link. The hook is rotatably mounted to the handle at a first rotational axis. The hook includes a hook body. The hook body includes a first lateral portion and a second lateral portion. The first lateral portion is laterally spaced from the second lateral portion. The first link is laterally between the first lateral portion and the second lateral portion. The first link is rotatably mounted to the first lateral portion and the second lateral portion at the first rotational axis. The second link is laterally between the first lateral portion and the second lateral portion. The second link is rotatably mounted to the first link at a second rotational axis. The second link is configured for translation relative to the first lateral portion and the second lateral portion.
An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure and a nozzle. The nacelle inlet structure extends circumferentially about an axial centerline. The nacelle inlet structure includes an inlet lip, a bulkhead and an internal cavity formed by and axially between the inlet lip and the bulkhead. The nozzle is configured to direct gas into the internal cavity axially towards the bulkhead.
A nacelle for a gas turbine engine includes a fixed nacelle portion, a cowl panel, and a latch assembly. The fixed nacelle portion extends circumferentially about an axial centerline. The cowl panel is axially adjacent the fixed nacelle portion. The cowl panel is moveable relative to the fixed nacelle portion between an open position and a closed position. The latch assembly includes a first latch portion and a second latch portion. The first latch portion is mounted to the cowl panel. The first latch portion includes a pin configured for translation along a pin axis between an extended pin position and a retracted pin position. The second latch portion is mounted to the fixed nacelle portion. The second latch portion includes a pin guide. The pin guide is configured to receive and engage the pin with the pin in the extended position and the cowl panel in the closed position.
A latch mechanism for joining two portions of a gas turbine engine. The latch mechanism is moveable between an open and a closed position and includes a first member configured to be attachable to a first portion of a gas turbine engine and a second member pivotally attached to the first member. The first member is attached to the second member at a first position. The latch mechanism also includes a handle pivotally attached to the second member that is attached to the second member at a second position, and third member pivotally attached to the second member. The third member is attached to the second member at a third position, the third position being between the first position and the second position, and wherein the third member comprises securing means for securing the third member to a second portion of a gas turbine engine.
E05C 3/08 - Fastening devices with bolts moving pivotally or rotatively without latching action with operating handle or equivalent member moving otherwise than rigidly with the bolt the handle or member moving essentially towards, or away from, the plane of the wing or frame
E05C 3/04 - Fastening devices with bolts moving pivotally or rotatively without latching action with operating handle or equivalent member rigid with the bolt
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
A manufacturing method is disclosed herein. The method includes arranging a preform with a plurality of clamping assemblies, the plurality of clamping assemblies disposed along ends of the preform; and forming the preform into a shaped body, the forming including incrementally tensioning the preform around a surface of an inner mold line using the plurality of clamping assemblies; and drawing the preform into a set of forming beads of the inner mold line.
A manufacturing method is provided. A preform is arranged over a surface of an inner mold line. The preform is folded over sides of the inner mold line. An end of the preform is pressed into a grip strip coupled to a side of the inner mold line. The grip strip is translated in a first direction to tension the preform into a shaped body.
A manufacturing method is disclosed herein. The method includes arranging a preform over a surface of an inner mold line; folding the preform over sides of the inner mold line; pressing an end of the preform into a grip strip coupled to a side of the inner mold line; and applying pressure to the preform to force excess material of the preform into a forming bead of the inner mold line.
