8255results about "Blade accessories" patented technology

A wind energy plant with a nacelle, a rotor, which features at least one rotor blade adjustable in its blade pitch angle, a central control device for controlling the wind energy plant and a control unit disposed in the rotor for controlling the blade pitch angle of the at least one rotor blade, wherein the central control device and the control unit in the rotor can exchange data with each other via a data link, which comprises at least one first sending and receiving device at the nacelle side and at least one second sending and receiving device at the rotor side, wherein a wireless network connection with a safety-oriented communication protocol is provided between the at least one first sending and receiving device and the at least one second sending and receiving device, and that one monitoring- and communication device at a time is associated to the first and / or the second sending and receiving device, which can monitor the function of the sending and receiving device and initiate a predetermined action in the case of an error.

A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.

A method of forming a rotor for an ACM, having steps of forming a base having: a first section adjacent to an ACM diffuser shroud when installed; a second section forming a seal disposed against an ACM aft frame member when installed; a third section connected to an ACM compressor rotor shaft when installed; a fourth section connected to an ACM tie rod when installed; a fifth section between the second and fourth sections, forming the base includes: printing thermoplastic polymer surfaces from thermoplastic polymers disposed against each other, the thermoplastic polymer surfaces having different CTEs; forming a lower support section on the base by printing along the discrete sections a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the rotor by depositing on the lower support section along the discrete sections, via electrolysis deposition, a metallic coating.

Unfaired fan for aeronautical propulsion. Unfaired propulsive fan (100) comprising at least a first row of blades (110) capable of rotating about a central axis (X). Each of the blades (110) of the first row comprises a streamlined body extending radially from an inner radius Ri to an outer radius Re with respect to the central axis (X) and comprising an intrados (111) and an extrados (112) connecting a leading edge (BA) to a trailing edge (BF). The trailing edge (BF) of the profiled body of each blade (110) of the first row of blades (110) has teeth with spacings (λk) between adjacent tooth apexes that decrease monotonically in a radial direction towards the outer radius Re and the profiled body of each blade (110) of the first row of blades (110) has an activity factor FA between 100 and 225. Figure for the abstract: Fig. 2.

An airfoil, having: a body defining a leading edge and a trailing edge, wherein the body comprises: a base having an outer boundary extending longitudinally from a first end to a second end and transversely from a first side to a second side; and beads within the outer boundary, wherein each of the beads has a bead void, and wherein one or more of the beads includes: damping element within the bead void; or stiffening element extending across the bead.

A component includes a body having a coupon opening defined therein, and an additively manufactured (AM) metal coupon including a dense region, a porous region adjacent the dense region, and a coupon outer surface. The porous region has a first cross-sectional area at a first location at or near the coupon outer surface and a second cross-sectional area less than the first cross-sectional area at a second location distal from the coupon outer surface. A braze material couples the metal coupon in the coupon opening and infiltrates into the porous region, e.g., based at least on a characteristic of the porosity thereof. The dense region may have a third cross-sectional area at the first location and a fourth cross-sectional area greater than the third cross-sectional area at the second location so it can direct the braze material in the porous region toward an inner surface of the coupon opening.

A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

A sheath is provided. The sheath includes a leading edge portion having pressure and suction sides for respective association with pressure and suction sides of an airfoil and first and second wings respectively extending from the pressure and suction sides of the leading edge portion. The first wing includes a first elongate portion and a first trailing edge disposed at an end of and thinned relative to the first elongate portion. The second wing includes a second elongate portion and a second trailing edge disposed at an end of and thinned relative to the second elongate portion.

Method for manufacturing a hollow stator blade with internal stiffeners. A method for manufacturing a turbomachine stator blade, the method comprising: - the production of a fibrous blank (100) of an aerodynamically profiled structure by three-dimensional weaving of yarns, said blank comprising two skins (110, 111), an internal housing (104a) located between the skins, one or more first fibrous stiffeners (140) extending into the internal housing and one or more second fibrous stiffeners (150, 160) extending into the internal housing, the first and second fibrous stiffeners delimiting between them cavities (112, 113, 114, 115, 116, 117) in the internal housing (104a), - the insertion of soluble cores (171, 172, 173, 174, 175, 176) in the cavities of the internal housing,- the injection of a resin into the fibrous preform and the transformation of the resin into a matrix so as to obtain an intermediate stator blade part made of composite material having an internal volume between two skins and comprising stiffeners each in contact with the inner face of the skins, at least some stiffeners having one or more circulation channels, - the dissolution of the cores present in the cavities. Figure for the abbreviation: Fig. 4.

Aeronautical part (10) comprising a body (11) made of composite material having a portion that is at least partially impregnated with a thermoplastic impregnation material (30) and a protective element (34, 44) comprising a thermoplastic construction material that is overmolded onto the portion. Method for manufacturing such a part. Figure for the abstract: Figure 10

A metal coupon (200) for repairing a component (202) includes an additively manufactured (AM) metal member (210) having at least two porous regions (300) and a braze material infiltration barrier (304) positioned between the at least two porous regions (300). The braze material infiltration barrier (304) has a lower porosity than the at least two porous regions (300). A component (202) using the metal coupon (200) may also include a braze material (310) coupling the metal coupon (200) in a coupon opening (204) in the body (206). The braze material (310) infiltrates at least one of the two porous regions (300), and the braze material infiltration barrier (304) separates the braze material (310) in the at least one of the two porous regions (300) from at least one other of the at least two porous regions (300). Different braze materials may be used in each porous region.

An additive manufactured (AM) metal coupon for a turbomachine component is provided. The component includes an airfoil body having a pressure side, a suction side, a trailing edge, and a coupon opening. The AM metal coupon has an AM metal member with at least one slanted coupon side wall at an angle of less than 90° with an exterior surface of the AM metal member. The AM metal member also has a first porous region having a first porosity and a second porous region having a second porosity different than the first porosity. A braze material couples the AM metal coupon in the coupon opening in the airfoil body and infiltrates into at least one of the first porous region based at least on a characteristic of the first porosity and the second porous region based at least on a characteristic of the second porosity.

A metal coupon includes an additively manufactured (AM) metal member having a porous region having between 2% to 50% open space volume to total volume. The metal coupon includes a first section of an anchor configured to interact with a second section of the anchor in a coupon opening of a body of a component. A component including the metal coupon may include the body including the coupon opening, and an anchor including a first section in or on one of the AM metal coupon and the body and a second section in or on the other of the AM metal coupon and the body. At least the first and second sections cooperatively hold the AM metal coupon in the coupon opening in the body. Braze material couples the coupon in the coupon opening in the body. The braze material infiltrates into the porous region.

A metal coupon for repairing a component includes an additively manufactured (AM) metal member having a conduit in an interior of the AM metal member, and a first porous region around the conduit. The conduit is hollow. The porous metal coupon with conduit allows a braze material to be directed based on characteristics of the first porous region. A second porous region may be provided inside the conduit to increase heat rejection of the conduit.

A component includes a dense base region, a dense replacement region and an additively manufactured (AM) porous region between the dense base region and the dense replacement region. The porous region has a porosity between 2% to 50% open space volume to total volume of the AM porous region. The porous region can be printed onto the base region or the replacement region. A braze material couples the base region, the porous region and the replacement region together, and infiltrates into the porous region based at least on a characteristic of the porosity. The porous region reduces stress at a joint between the dense regions and can be customized to create different physical characteristic(s) than just those of the base and replacement regions.

A component (202) is disclosed that includes a body (206) and an additive manufactured (AM) metal mass (200) that includes a first section (292) and a stress relief section (294). The stress relief section (294) includes a porous region (300) having a porosity in which an open spatial volume accounts for 2% to 50% of the total volume of the stress relief section (294). The stress relief section (294) has a smaller at least one of thermal conductivity, tensile strength, ductility, and fatigue strength than the first section (292). A braze material (310) couples the AM metal specimen block (200) to a specimen block opening (204) in the body (206). The stress relief section (294) creates a low stress zone in the metal specimen block (200), which can be located near or adjacent to a high stress zone. The stress relief section (294) reduces residual stress in the metal sample block (200), which reduces related challenges to couple the metal sample block (200) to the body (206) of the component (202), particularly in the case of the use of superalloy materials.

A component includes a body and an additively manufactured (AM) metal coupon that includes at least one first porous region having a first porosity and may include any number of second porous regions having a second porosity different than the first porosity. A braze material couples the metal coupon in a coupon opening in the body. The braze material infiltrates into at least one of the first porous region based at least on a characteristic of the first porosity or any second porous region based at least on a characteristic of the second porosity. The different porosities can be customized to provide the first porous region and the second porous region with the braze material therein with different physical characteristic(s).

This mixed flow turbine is provided with a turbine wheel comprising a hub and blades provided at intervals in a circumferential direction of the hub on an outer peripheral surface of the hub. The tip ends of the leading edges of the blades are positioned on an outer side in the radial direction of the turbine wheel than the hub ends of the leading edges. When a distance between the downstream end of the outer peripheral surface of the hub and a rotational axis line of the turbine wheel is Dh and the average of distances between respective positions from the hub ends to the tip ends at the leading edges and the rotational axis line is Eave, Dh / Eave>0.4 is satisfied.

A metal coupon for repairing a component includes an additively manufactured (AM) metal member having a low porosity region in an interior of the AM metal member, and a porous region around the low porosity region. The low porosity region may have a porosity in a range of 0% to 5%, so is solid or nearly solid. The porous metal coupon with low porosity region allows braze material to be directed based on characteristics of the porous region.

A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

A metal coupon (200) for repairing a component (202) includes an additively manufactured (AM) metal member (330) having a sealed cavity (296) in an interior of the AM metal member (330), and a porous region (300) around the sealed cavity (296). A metal coupon system (210) may include at least two AM metal parts (292) with each AM metal part (292) including at least a section (294) of a sealed cavity (296) therein and a porous region (300) around the at least a section (294) of the sealed cavity (296). The AM metal parts (292) combine to form the metal coupon (200), i.e., AM metal member (330), with the sealed cavity (296) in an interior thereof and the porous region (300) around the sealed cavity (296). In any event, the sealed cavity (296) is hollow. The porous metal coupon (300) with sealed cavity (296) provides reduced mass and allows braze material (310) to be directed based on characteristics of the porous region (300).

The invention relates to a metal sample block with a porous area for a component and the component with the metal sample block. A component (202) includes a body (206) and an additive manufactured (AM) metal sample block (200) that includes at least one first porous region (300A) having a first porosity and can include any number of second porous regions (300B) having a second porosity different from the first porosity. A braze material (310) couples the metallic sample block (200) in a sample block opening (204) in the body (206). The braze material (310) is infiltrated into at least one of the first porous region (300A) and any second porous region (300B) based at least on a characteristic of the first porosity and at least on a characteristic of the second porosity. Different porosities can be tailored to provide different physical characteristics for the first porous region (300A) and the second porous region (300B) having the braze material (310) therein.

An additive manufactured (AM) metal coupon (200) for a turbomachine component (202) is provided. The component (202) includes an airfoil body (206) having a pressure side (152, 178), a suction side (154, 180), a trailing edge (158, 184), and a coupon opening (204). The AM metal coupon (200) has an AM metal member (290) with at least one slanted coupon side wall (292, 294) at an angle of less than 90° with an exterior surface (296) of the AM metal member (290). The AM metal member (290) also has a first porous region (300A) having a first porosity and a second porous region (300B) having a second porosity different than the first porosity. A braze material (310) couples the AM metal coupon (200) in the coupon opening (204) in the airfoil body (206) and infiltrates into at least one of the first porous region (300A) based at least on a characteristic of the first porosity and the second porous region (300B) based at least on a characteristic of the second porosity.

An airfoil is provided that includes a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil. The exterior airfoil surface are formed in conformance with a plurality of cross-section profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.

The invention relates to a porous metal sample block with a pipeline for repairing a component, the component with the porous metal sample block and a related method. A metal sample block (200) for repairing a component (202) includes an additive manufactured (AM) metal component (330) having a conduit (296) inside the AM metal component (330) and a first porous region (300) surrounding the conduit (296). The duct (296) is hollow. A porous metal sample block (200) with conduits (296) allows the brazing material (310) to be directed based on characteristics of the first porous region (300). The second porous region (350) can be disposed within the conduit (296) to increase heat dissipation of the conduit (296).

A component including a body, and an additively manufactured (AM) metal coupon including a first section and a stress-relief section, is disclosed. The stress-relief section includes a porous region having a porosity between 2% to 50% open space volume to total volume of the stress-relief section. The stress-relief section has at least one of thermal conductivity, tensile strength, ductility, or fatigue strength less than first section. A braze material couples the AM metal coupon to a coupon opening in the body. The stress-relief section creates a low-stress zone in the metal coupon that can be located near or adjacent to a high-stress zone. The stress-relief section reduces residual stress in the metal coupon, which reduces the related challenges of coupling the metal coupon to the body of the component, especially where superalloy materials are used.

A metal coupon for repairing a component includes an additively manufactured (AM) metal member having at least two porous regions and a braze material infiltration barrier positioned between the at least two porous regions. The braze material infiltration barrier has a lower porosity than the at least two porous regions. A component using the metal coupon may also include a braze material coupling the metal coupon in a coupon opening in the body. The braze material infiltrates at least one of the two porous regions, and the braze material infiltration barrier separates the braze material in the at least one of the two porous regions from at least one other of the at least two porous regions. Different braze materials may be used in each porous region.

An assembly for an aircraft propulsion system includes a propulsor rotor and a guide vane structure. The propulsor rotor is configured to rotate about an axis. The guide vane structure includes a plurality of guide vanes arranged circumferentially about the axis. The guide vane structure is axially next to and downstream of the propulsor rotor. The guide vanes include a first guide vane. The first guide vane includes a camber line, a leading edge, a trailing edge, a leading edge section and a trailing edge section. The first guide vane extends longitudinally along the camber line from the leading edge to the trailing edge. The leading edge section forms the leading edge. The trailing edge section forms the trailing edge. The leading edge section is configured to move longitudinally along the camber line relative to the trailing edge section to change a camber of the first guide vane.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.