974results about "Turbines" patented technology

A combustor for a gas turbine (GT) system includes a combustor body including a non-additively manufactured (non-AM) part having corrosion at a first level and a replacement additively manufactured (AM) part coupled to the non-AM part. The replacement AM part has corrosion at a second level less than the first level. The replacement AM part includes at least an aft section of a tapered transition portion and an aft frame of the combustor body, and a plurality of shared parallel, sintered metal layers extending into the aft section of the tapered transition portion and the aft frame. The replacement AM part may also include a receiving element in a forwardmost end thereof configured to receive a rearwardmost remaining end of the non-AM part. The replacement AM part may also optionally include an AFS injector mount and part of a cylindrical portion of a combustion liner.

Systems and methods for generating a shape-based graded lattice structure that can be used in additive manufacturing. A slicer computer system generates the lattice structure by simulating the packing of a planar region with variable-sized packing shapes, where packing shape sizes correspond to intensity values of a non-uniform physical field expected to be experienced by the article. An intermediate lattice structure is then generated using a first set of polygonal cells, followed by a second set of polygonal cells that refine the final lattice structure. Tailored sectioning and field-based smoothing can modify polygon packing algorithms to adapt lattice generation. The resultant multi-stage graded lattice structures, which may include multiple lattice patches and transition zones, from shape-based packing, tailored sectioning, field-based smoothing, and slicer-based additive manufacturing processing improve connectivity and manufacturability over traditional lattice structures.

A tooling support system is provided. The tooling support system includes tooling support elements. Each tooling support elements includes an anchor mountable to an external component of a body being drilled into, a tool guide supportable by the anchor and defining a tooling pathway and a guide sleeve disposed at an end of the tooling pathway. Each of the guide sleeves of the tooling support elements have varying dimensions.

An oxyide dispersion-strengthened (ODS) alloy is disclosed that is compatible with melt-based additive manufacturing processes, such as laser powder bed fusion (L-PBF) while achieving material properties, such as resistance to frictional ignition, comparable to or better than wrought ODS alloys. This is accomplished, in part, by adjusting the composition of the ODS alloy and / or adjusting the operating parameters of the additive manufacturing process to reduce or, in some instances, mitigate dispersoid coarsening and slag formation. For example, a nickel (Ni)-based ODS alloy may include less than 0.3 wt % aluminum (Al) to reduce the formation of low melting point oxides that are prone to coarsening and slag formation. In another example, various processing parameters associated with a selective laser melting process, such as beam power, beam spot size, and scan speed, may be chosen to reduce a melt time associated with the additive manufacturing process.

The invention discloses application of a double-channel powder feeding process in preparation of an aero-engine turbine disc blank, belongs to the technical field of aero-turbine disc manufacturing, and is characterized in that high-temperature alloy powder is subjected to gradient proportioning deposition through a double-channel system by an electric arc powder feeding additive process, and material gradient distribution is formed in disc center, transition and disc edge areas; meanwhile, dynamic mechanical deformation is applied to a new deposition layer in a high-temperature plastic state by adopting a synchronous micro-forging process, hot isostatic pressing treatment is carried out on a prepared turbine disc blank to eliminate internal defects, high-temperature homogenizing annealing is carried out in a vacuum furnace to improve the structure uniformity, and finally, the required mechanical property is obtained through solution treatment and aging treatment. The gradient accurate control of material components in different areas of the turbine disc is realized, the microstructure of a deposition material can be effectively improved, regulated and controlled in the manufacturing process, and metallurgical defects are reduced.

Disclosed herein is an integrated in-line emergency lube pump assembly for a planetary gearbox, including a main lube pump, a coaxial lube pump coaxially aligned with and coupled to the planetary gearbox, and an oil tank having a main section and an auxiliary section. There is no physical boundary between the main section and the auxiliary section of the oil tank. When the detected pressure in the oil supply line is equal to or exceeds a predetermined pressure threshold, the main lube pump operates to causes the main pump to pump oil from the main section of the oil tank to the planetary gearbox. Alternatively, when the detected pressure in the oil supply line is less than the predetermined pressure threshold the main lube pump ceases operation to cause the coaxial lube pump to draw oil from the auxiliary section of the oil tank to the planetary gearbox.

A method is disclosed for providing a component. During this method, braze powder is additively deposited with a substrate. The braze powder is sintered together during the depositing of the braze powder to provide the substrate with sintered braze material. The sintered braze material is heated to melt the sintered braze material and to diffusion bond the sintered braze material to the substrate to provide braze filler material. A first object is scanned using structured light to provide first object scan data. The first object includes the substrate and the braze filler material diffusion bonded to the substrate. The first object scan data is compared to first object reference data to provide machining data. The first object is machined using the machining data to provide a second object.

Inventive techniques for forming unique compositions of matter are disclosed, as well as various advantageous physical characteristics, and associated properties of the resultant materials. In particular, particles comprising polymer matrices are characterized by having carbon disposed within the polymer matrix structure thereof. The carbon is primarily, or entirely, present at interstitial sites of the polymer matrix, and may be present in amounts ranging from about 15 wt % to about 90 wt %. The carbon, moreover, forms covalent bonds with both atoms of the polymer matrix and other carbon atoms present in, but not part of, the matrix. This facilitates substantially homogeneous dispersal of the carbon throughout the resultant material, conveying unique and advantageous properties such as strength-to-weight ratio, density, mechanical toughness, sheer strength, flex strength, hardness, anti-corrosiveness, electrical and / or thermal conductivity, etc. as described herein. In some approaches, the resultant materials may be powderized or pelletized.

The invention relates to the technical field of high-temperature alloy additive manufacturing, and discloses a method for preparing a low-crack-sensitivity nickel-based high-temperature alloy through selective laser melting and application of the low-crack-sensitivity nickel-based high-temperature alloy. And selective laser melting forming treatment is conducted on the core-shell structure powder, specifically, regional laser scanning, interlayer pulse pressurization and in-situ heat treatment are conducted, and the low-crack-sensitivity nickel-based high-temperature alloy is obtained. According to the invention, synchronous regulation and control of microcrack closing and nanophase precipitation are realized through design of core-shell structure powder, laser regional dynamic energy control scanning of hot lines and interlayer in-situ densification. By means of the method, the SLM forming crack density can be reduced to be smaller than or equal to 0.1 mm / mm, the anisotropy index is smaller than or equal to 1.05, the post-treatment hot isostatic pressing link is omitted, and the method can be applied to thin-wall high-cycle fatigue parts such as aero-engine flame tubes and aerospace turbine pump rotors.

The invention discloses a laser additive repairing method for 17-4PH steam turbine blades, and relates to a laser repairing method for steam turbine blades. The method aims at solving the technical problem that in existing laser additive 17-4PH turbine blade repairing, the difference between the thermal expansion coefficient of Co-based corrosion-resistant alloy and the thermal expansion coefficient of 17-4PH alloy is large, and consequently the interface performance is reduced after repairing is conducted. According to the laser additive repairing method for the 17-4PH steam turbine blade, due to the fact that 17-4PH is poor in water erosion resistance, Co-based alloy powder is used for preparing a water erosion resistance structure, on the basis, in consideration of the problem that the performance difference of the Co-based alloy powder and the 17-4PH material is large, a powder component gradient transition mode is adopted, and the water erosion resistance of the 17-4PH steam turbine blade is greatly improved. The problem of low interfacial strength during direct transition is solved, the binding capacity of the Co-based water erosion resistant layer and the 17-4PH matrix is improved, and finally the service time of the 17-4PH blade is prolonged.

The invention relates to an oil collecting device, a lubricating system, a wind generating set and a control method, and the oil collecting device comprises a base which is configured to be connected with a part to be subjected to oil collection; the collecting container is arranged on the base, and the collecting container is provided with a containing cavity and an opening communicated with the containing cavity; the locking component is arranged on the base and comprises more than two locking units, the collecting container is provided with locking interfaces corresponding to the locking units respectively, and the locking component and the collecting container are switched between a first matching state and a second matching state; in the first matching state, each locking unit partially extends into the corresponding locking interface so as to fix the relative position of the collecting container and the base; and in the second matching state, each locking unit is separately arranged from the locking interface, and the collecting container has a motion freedom degree relative to the base. The oil collecting device provided by the invention can meet the oil collecting requirement, and is good in stability and high in safety.

A product includes a material having aluminum and at least one rare earth element (REE). The material includes the following microstructure features: at least 1 volume % particles of a phase of an aluminum-rare earth element alloy, the particles comprise at least 5 weight % of the at least one rare earth element, the particles have an average aspect ratio less than or equal to 5, and an average interparticle spacing between the particles is less than or equal to 1 μm. A method includes forming a base material, the base material having aluminum and at least one rare earth element (REE), and working the base material to form a product.

The invention relates to the field of industrial manufacturing, and provides a defect correction method and system for aerospace engine turbine blade additive manufacturing. The method includes; a quantum dot marking agent is adsorbed to the surface of metal powder, signal data in the additive manufacturing process are collected, and a multi-dimensional monitoring characteristic parameter set is obtained; constructing a graph neural network model, taking the multi-dimensional monitoring characteristic parameter set as node characteristic input, and performing spatio-temporal evolution prediction on a molten pool area to obtain a defect probability distribution field; performing multi-target optimization on the process parameter vector through a Bayesian optimization algorithm to obtain a self-adaptive regulation and control parameter combination, and performing partition regulation and control on the manufacturing process; and for the residual defects of the partition regulation and control result, a reinforcement learning strategy network is adopted to select a repair action sequence, the repair action sequence is input into an execution unit to perform cross-level cooperative processing on the residual defects, and a repaired blade structure is obtained. According to the method, intelligent prediction and active correction of the turbine blade additive manufacturing defects are achieved.

The invention belongs to the technical field of aero-engine materials, and particularly relates to a high-temperature-resistant aero-engine blade and a preparation method thereof.According to the blade, titanium-aluminum alloy is adopted as a base body, and two novel materials including a core-shell structure self-healing reinforcement phase and a rare earth niobate ferroelastic protection compound are introduced, so that the high-temperature-resistant aero-engine blade is obtained; and the comprehensive performance of the blade in a high-temperature environment is remarkably improved. The core-shell reinforcement phase takes titanium diboride as a core and boron nitride as a shell, and can realize a self-healing function at a high temperature; the rare earth niobate compound has ferroelastic behavior and ultralow thermal conductivity through doping modification of tantalum and rhenium. The preparation process comprises the following steps: mixing the titanium-aluminum alloy powder, the reinforcing phase, the silicon carbide short fibers and the binder, carrying out spark plasma sintering molding, carrying out machining, applying the protective coating through plasma spraying, and finally carrying out heat treatment. According to the method, the process is simplified, and the prepared blade has excellent high-temperature resistance, oxidation resistance and mechanical property and is suitable for aero-engine hot end components.

A vacuum induction melting (VIM) furnace and method of using. A VIM is configured for use with metal-containing carbon powders. In operation, the metal-containing carbon powders are formed into a pellet so as to minimize or eliminate ejection of material during introduction of the pellet into the VIM processor. The VIM processor may be substituted or used in combination with a vacuum arc melt processing apparatus, an electron beam melt furnace, an ion plating furnace, a plasma flame source, a smelter, a traditional metal-metal melt furnace, or any equivalent. Pelletizing can be accomplished through use of a press or through application of any pelletizing technique and / or use of any apparatus that is able to generate pellets that have sufficient mass to avoid ejection from a VIM processor.

The invention discloses a micro-crack electric shock regulation and control method for a laser remanufactured nickel-based superalloy aircraft engine blade, which comprises the following steps of: carrying out composite heat treatment on the laser remanufactured aircraft engine blade, adjusting the structure property and exposing the defects of the aircraft engine blade; scanning the laser remanufactured aircraft engine blade after heat treatment, performing three-dimensional reconstruction on scanning data, calibrating three-dimensional coordinates of the defect based on the reconstructed scanning data, and acquiring geometric characteristic parameters of the defect; electric shock process parameters are calculated according to the geometrical characteristic parameters of the defects, and an electrode loading path is planned on the laser remanufactured aircraft engine blade; performing electric shock treatment on the laser remanufactured aircraft engine blade point by point on the basis of the planned path and the electric shock process parameters to obtain a repaired aircraft engine blade; the laser additive remanufacturing nickel-based high-temperature alloy blade is subjected to high-energy short-time electric shock treatment, targeted precise repair of internal micro-nano defects is achieved, and the service life of the blade is prolonged.

An oil supply system, has: an oil tank; a closed-loop oil circuit including a component, a pump having a pump inlet and a pump outlet, and a de-aerator; a make-up flow conduit connecting the oil tank to the closed-loop oil circuit; a make-up pump connected to the closed-loop oil circuit; a recirculation conduit in parallel to the make-up pump and bypassing the make-up pump; a fixed orifice fluidly connected to the make-up flow conduit upstream of the closed-loop oil circuit and downstream of the recirculation conduit, the fixed orifice having an area selected to increase a pressure at an outlet of the make-up pump above a pressure at the de-aerator inlet; and a metering orifice connected on the recirculation conduit and having a flow circulating area selected to reduce a flow rate inputted into the closed-loop oil circuit below a flow rate generated by the make-up pump.

Oil and gas operations according to which a wellhead is operably associated with a wellbore, a valve is operably coupled to the wellhead, opposite the wellbore, a frac line is operably coupled to the wellhead, and a zipper module is operably coupled to the frac line, opposite the wellhead.

Inventive techniques for forming unique compositions of matter are disclosed, as well as associated physical characteristics and properties of the materials. In particular, particles comprising a metal lattice are characterized by having carbon (preferably graphene) disposed within the crystalline lattice structure thereof. The carbon is at least partially disposed in interstitial sites of the metal lattice, and may be present in amounts ranging from about 15 wt % to about 90 wt % of the total particle mass, with about 15 wt % to about 60 wt % being disposed in the interstitial sites, e.g., between basal planes, of the metal lattice. The carbon, moreover, is substantially homogeneously dispersed throughout the resultant material, conveying unique and advantageous properties such as strength-to-weight ratio, density, mechanical toughness, sheer strength, flex strength, hardness, anti-corrosiveness, electrical and / or thermal conductivity, etc. as described herein. In some approaches, the graphene is pristine, and has corresponding physical characteristics as described herein.

A gas turbine airfoil (126) includes a trailing edge cooling hole (144) that has an elliptical cross-sectional baseline shape. In addition, the exit passage wall leading to the trailing edge cooling hole (144) has a surface that varies according to an exit passage profile (150). Applying an iterative method of embodiments can produce a final exit passage profile (150) with significantly reduced thermal strain during operation as compared to the prior art, resulting in improved component life.

An oil distributor is provided for a bearing chamber. The oil distributor includes an outer annular manifold, which is integrally formed with an interior surface of the bearing chamber and which defines a first interior cavity receptive of pressurized oil which defines a first interior cavity receptive of pressurized oil, an inner annular manifold, which defines a second interior cavity and comprises an interior facing surface defining holes respectively communicative with the second interior cavity and one or more support struts by which the inner annular manifold is supported within the outer annular manifold. Each of the one or more support struts defines interior lines by which the pressurized oil flows from the first interior cavity to the second interior cavity and to the holes.

A processing method is a processing method for processing a processing target object held by a holding tool, and acquires holding tool information related to a position of a reference part of the holding tool placed in the processing apparatus, in a processing coordinate system; sets the holding tool in a measurement apparatus; acquires, by using the measurement apparatus, measurement information including information related to a three-dimensional shape of the processing target object in a measurement coordinate system and information related to a position of the reference part in the measurement coordinate system; generates processing path information based on the measurement information and the holding tool information; places the holding tool, which has been taken out of the measurement apparatus, in the processing apparatus; and processes the processing target object on the holding tool placed in the processing apparatus based on the processing path information.

An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, a spatter monitoring system, and a computing device configured to receive image data from the spatter monitoring system. The spatter monitoring system is configured to capture image data indicative of spatter, wherein spatter is material ejected from the melt pool. The computing device is configured to identify a spatter event based on the received image data and control at least one of the energy delivery device or the powder delivery device based on the determined spatter event.

An aerospace part, which is made from a base material, is inspected to identify a worn or defective repair region that requires repair. A repair procedure is performed on the repair region using a directed energy deposition (DED) energy / powder head. The repair procedure includes depositing, using the DED energy / powder head, a first layer of DED powder material in the repair region; melting and consolidating, using energy from the DED energy / powder head, the first layer of DED powder material to form a first repair layer having a first pre-determined microstructure; and repeating the depositing and melting and consolidating steps to create a desired plurality of repair layers. Each of the plurality of repair layers has a pre-determined microstructure. The microstructure of each of the plurality of repair layers is imparted using selected levels of DED powder material feed to the repair region, intensity of energy directed from the DED energy / powder head to the repair region, rate at which the DED energy / powder head traverses the repair region, and auxiliary heating and / or cooling provided to the repair region. The aerospace part is returned to service after completion of the desired repair.

The invention belongs to the technical field of powder metallurgy, and particularly discloses a powder filling device of a sheath for hot isostatic pressing and a powder filling method and application thereof.The powder filling device comprises a fixed carrying table, a powder supply mechanism, a first vibration mechanism and a second vibration mechanism, the fixed carrying table is provided with a plurality of containing barrels in an annular array mode, and the powder supply mechanism can rotate and has a powder monitoring function; the first vibration mechanism and the second vibration mechanism provide vibration in the vertical direction and the horizontal direction respectively. According to the powder filling method, powder filling is guaranteed to reach the standard through the steps of sheath placing and weighing, primary powder filling and preheating, secondary powder supplementing through vibration in the vertical direction, tertiary powder supplementing through vibration in the horizontal direction, weight verification iterative vibration and the like. When the device is applied to TiAl alloy blade preparation, multi-bag powder filling can be achieved at a time, a multi-dimensional vibration mode is formed, powder is fully compacted through vibration, the filling condition is monitored and controlled in real time, manual intervention is reduced, the powder filling efficiency and quality stability are remarkably improved, cost is reduced, the preparation period is shortened, and large-scale production of TiAl alloy blades is powerfully promoted.

A braze tape includes a first portion, a second portion, and a central portion located between and adjacent to the first portion and the second portion. The first portion includes a low melting temperature alloy material, the second portion includes a high melting temperature alloy material, and the central portion includes a mixture of the low melting temperature alloy material and the high melting temperature alloy material. The central portion may gradually change between the low melting temperature alloy material and the high melting temperature alloy material. A related method is also disclosed.

An aerospace part, which is made from a base material, repairing using directed energy deposition (DED) techniques. The aerospace part is inspected to identify a worn or defective repair region on a repair feature that requires repair. An intervening feature that blocks line-of-sight from a DED laser / powder head to the repair region on the repair feature is removed such that after removal of the intervening feature there is line-of-sight from the DED laser / powder head to the repair region on the repair feature. a repair procedure is performed on the repair region of the repair feature using the DED laser / powder head. A replacement intervening feature is obtained and attached to the aerospace part to complete a desired repair. The aerospace part is returned to service after completion of the desired repair.

The invention provides a nickel-based superalloy with high cobalt and gamma'content and a preparation method and application thereof, and belongs to the technical field of superalloy additive manufacturing. The invention provides spherical nickel-based high-temperature alloy powder which comprises the following components in percentage by mass: 20 to 30 percent of Co, 8 to 10 percent of Cr, 4 to 7 percent of Al + Ti, 14 to 16 percent of W + Mo + Ta, 0 to 3.5 percent of Nb, 0.001 to 0.015 percent of B, 0.05 to 0.1 percent of C and the balance of Ni. And the spherical nickel-based superalloy powder serves as a printing raw material, laser additive manufacturing is conducted, then heat treatment is conducted, and the nickel-based superalloy with the high cobalt content and the high gamma'content is obtained. The nickel-based superalloy with high cobalt and gamma'content prepared by the method has excellent high-temperature mechanical properties and excellent printability, and is suitable for direct forming of turbine blades or additive manufacturing repair of damaged turbine blades.

The invention relates to a method for the additive manufacturing of a combustion chamber (5). A cross-sectional shape (2) is defined as a closed, parameterized curve, and an extrusion curve (3) is defined as an open, three-dimensional curve. The material is applied along the extrusion curve (3) to form a strand (1), the cross-section of which is defined by the cross-sectional shape. A first end of the strand (1) forms one of the inlet openings (1a), and a second end of the strand (1) forms one of the outlet openings (1b). The application step is repeated at least once to produce further strands (1). The strands (1) are arranged such that they form a wall of the combustion chamber (5), with the outlet opening (1b) of each strand facing an interior region of the combustion chamber (5).

A fan exit guide vane with acoustic treatment includes a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; and an acoustic zone integrally formed within the fan exit guide vane. A gas turbine engine includes the fan exit guide vane with acoustic treatment. A process forms the fan exit guide vane with acoustic treatment.