3530results about "Engine manufacture" patented technology

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.

A systematic framework for optimizing multi-stage axial compressor disk designs in gas turbine engines. By combining finite element analysis (FEA), Design of Experiments (DOE), and optimization algorithms of multi-objective genetic algorithm (MOGA), the method balances stress, deformation, and mass to enhance structural performance. The six-step process includes blade modeling, parameterizing disk geometry, structural analysis using FEA, developing functional relationships, applying optimization algorithms, and generating manufacturable 3D disk models. This approach reduces weight, improves fuel efficiency, and adapts to various compressor designs and materials, enhancing the overall performance of gas turbine engines.

A pump side part for use with a centrifugal slurry pump for pumping a fluid mixture containing particulate matter, the pump side part comprising a main body having a main axis, the main body including a side wall section which extends laterally with respect to the main axis and has opposite facing first and second sides, a plurality of formations on a surface of the second side including an inner formation and an outer formation in spaced relation to the inner formation, the formations being configured so that in use the formations generate a flow of the fluid mixture across the surface which detaches from the surface the particulate matter adjacent thereto.

A power turbine blade for a gas turbine engine includes at least one of a third-stage blade, a fourth-stage blade, or a fifth-stage blade. The power turbine blade includes a platform and an airfoil that extends in a spanwise direction from the platform to a tip shroud. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.

A gas turbine engine includes: a turbomachine comprising a drive turbine and defining a working gas flowpath and an inlet to the working gas flowpath; a fan having a fan blade formed of a composite material, the fan blade defining a leading edge fan radius RFan_LE and a trailing edge fan radius RFan_TE, and the fan defining a leading edge hub radius RHub_LE and a trailing edge hub radius RHub_TE, the gas turbine engine defining a bypass ratio during operation of the gas turbine engine in a cruise operating mode; and a reduction gearbox mechanically coupling the drive turbine of the turbomachine to the fan; wherein the gas turbine engine defines a Fan Leading Edge to Trailing Edge Compression Factor (FLTCF) greater than or equal to 1.05 and less than or equal to 1.8.

A fluid connection for a hydromotive machine or fluid-control valve having a first duct and a second duct. The first duct includes a mid-portion between a first end of the first duct and a second end of the first duct that has a non-circular cross-section. A second end of the first duct is wholly within the second end of the second duct. A first end of the second duct is wholly outside of the first duct.

A micro gas turbine engine may include a single-piece rotor having a compressor, a turbine, and a shaft manufactured from an additive manufacturing process. The compressor, turbine, and shaft are a single uniform piece and not separately joined together. The micro gas turbine engine may further include a ceramic cover having built in fuel injectors and stator blades for the compressor. The micro gas turbine engine may further include a inner combustor lining having built in stator blades for the turbine.

A fluid film bearing for a rotor hub of a wind turbine includes a first part and a second part rotatably coupled to each other about a longitudinal axis. The first part includes an annular first sliding surface extending in the circumferential direction of the fluid film bearing along the first part. In addition, the second part includes a support structure and a first group of bearing pads coupled to the support structure and having a bearing pad sliding surface configured to slide on the first sliding surface. In addition, the fluid film bearing further includes a seal arranged between the first part and the second part.

A method for constructing a wind turbine concrete floater including a central connector from which radial arms extend, the central connector carrying a central stability tower, and each arm carrying an outer stability tower. The method includes prefabricating the arms, central connector and at least parts of the stability towers, pre-assembling the central connector with one arm to form a primary pre-assembly, mounting temporary flotation devices onto the arms to provide additional buoyancy to them, floating the primary preassembly and floating the other arms of the floater, and assembling offshore said primary preassembly with said other arms.

The invention relates to a blade decommissioning tool for decommissioning an installed wind turbine blade. The blade decommissioning tool comprises cutting means for cutting through the wind turbine blade in a transversal direction perpendicular to a longitudinal direction L of the wind turbine blade to form a proximal and distal part of the wind turbine blade; lowering means for lowering the distal part of the wind turbine blade relative to the proximal part; support means for supporting the cutting means and the lowering means; and clamping means for clamping the support means to wind turbine blade.

A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

A dual pump unit having a pair of pumps that provide parallel hydraulic paths, and are configured to operate concurrently in opposite rotational directions. The dual pump unit has a sealed casing which includes a suction flange, two volutes in hydraulically parallel configuration, and a discharge flange. The pair of pumps are located within a respective volute of the casing and, in an example, are radially inline and horizontally inline. The casing may include a flattened bottom. Each pump may include a touchscreen for configuration of the respective pump. The pumps are controllable to circulate a circulating medium to collectively provide output to source a load.

An acoustic panel for an aircraft includes a skin, a plurality of first cells and a plurality of second cells interspersed with the first cells. Each first cell includes a first tube, a first endwall and a first cavity. The first tube projects vertically out from the skin to a distal end of the first tube. The first endwall closes off the first cavity at its distal end. The first cavity extends vertically through the first tube from the skin to the first endwall. Each second cell includes a second tube, a second endwall and a second cavity. The second tube projects vertically out from the skin to a distal end of the second tube. The second endwall closes off the second cavity at its distal end and is offset from the first endwall. The second cavity extends vertically through the second tube from the skin to the second endwall.

A ceramic matrix composite (CMC) blade outer air seal (BOAS) assembly includes a CMC BOAS including a base and a pair of rails having a substantially π-shaped cross-section. The pair of rails include a first pair of aligned holes at a first end and second pair of aligned holes at a second end. A first pair of parallel metallic pins have a first end connected to a first central support pin and a second end connected to a second central support pin, respectively, wherein the first pair of parallel metallic pins are configured to engage the first pair of aligned holes. A second pair of parallel metallic pins also have a first end connected to a first central support pin and a second end connected to a second central support pin, respectively, wherein the second pair of parallel metallic pins are configured to engage the second pair of aligned holes.

A cooled brush seal for use with a CMC component of a gas turbine engine having a hot side exposed to a hot gas path and an opposing side having a cavity for feeding a cooling flow to at least one film cooling hole. The cooled brush seal includes: an OD backing plate; an ID backing plate; a plurality of brush seal bristles sandwiched between the OD backing plate and the ID backing plate; a first hole extending through the OD backing plate, the brush seal bristles, and the ID backing plate; and a cover plate attached to an inner surface of the ID backing plate and including a second hole circumferentially offset from the first hole and forming a second passage into the cavity, wherein the ID backing plate and the cover plate form a circumferential cooling passage extending between the first hole and the second hole.

A wind turbine arrangement, that includes: a wind turbine blade; an inflatable platform positioned in the wind turbine blade; and an inflatable outer pressure ring surrounding the platform, wherein the outer pressure ring, when inflated with a gaseous fluid, fixes the platform in the wind turbine blade by generating a normal friction force between the platform and the wind turbine blade. In a first wind turbine arrangement, after the platform has been inflated with a gaseous fluid, the inflated platform includes a material that contains the gaseous fluid and is continuously distributed throughout the area defined by a circular or oval shape of the platform. In a second wind turbine arrangement, the platform comprises a fibrous material disposed in the platform. In a third wind turbine arrangement, a tarpaulin edge is positioned above the platform and positioned interior to the outer pressure ring.

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine comprising: a turbomachine comprising, in serial flow order, a compressor section, a combustion section, and a turbine section, the turbomachine defining a working gas flow path and a fan duct flow path; a primary fan driven by the turbomachine, the primary fan defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan downstream of the primary fan and driven by the turbomachine, at least a portion of airflow from the primary fan being configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide, during operation, a fan duct airflow through the fan duct flow path to generate a fan duct thrust, wherein the fan duct thrust is equal to a %Fn of a total engine thrust during operation of the gas turbine engine at rated speed during standard day operating conditions 3S ; wherein a ratio of R1 to R3 is equal to wherein EFP is between 1.5 and 11, wherein RqR Prim.‑Fan is a ratio of R2 to R1, and wherein RqR Sec.‑Fan is a ratio of R4 to R3.

A fan assembly has a substantially centrifugal outlet, an axial intake, an airflow channel extending substantially perpendicular to the axial intake, and a guide element for redirecting airflow adjacent the axial intake. The axial intake is spaced apart from a back wall of the airflow channel by a first distance, and the guide element is positioned between the axial intake and the back wall of the airflow channel, or the guide element comprises a back surface of the fan assembly. The airflow from the airflow channel then passes through the guide element to enter the axial intake.

Systems and methods are provided for assembling and installing multiple wind turbines from a single vessel. In general, different embodiments use wind turbine components on the vessel including blades, a nacelle assembly with a rotating hub, and a tower. A Turbine Installation Gantry System (TIGS) embodiment uses a gantry system with a truss substructure and at least one bridge crane on an elevated vessel for assembling the wind turbine blades on the vessel to a nacelle hub supported on the seabed. A Skidding Turbine Installation Crane (STIC) embodiment has a rotatable crane mounted on a skidding pedestal or cantilever structure, providing full access to the vessel deck and blades, and for bringing the assembled nacelle assembly outboard to assemble each blade. A Turbine Assembly Positioning System (TAPS) embodiment includes both a handling system and a crane mounted on a skidding cantilever structure for securing the blades to the assembled tower section and nacelle hub that are cantilevered outboard of the vessel by the handling system. The combination embodiment uses selected components and systems from the TIGS, STIC and TAPS embodiments to provide component and system redundancy and concurrent operation.

The invention relates to a system (2, 102) for assembling a generator (3, 103), preferably a permanently excited generator (3, 103) of a wind turbine, comprising a rotor (16, 116) and a stator (10, 110). According to the invention a vertical assembly device (4, 104) being connectable to the rotor (16, 116) and the stator (10, 110) is proposed, for guiding the rotor (16, 116) in parallel and coaxially aligned to the stator (10, 110) during assembly, the vertical assembly device (4, 104) comprising a first assembly element (26, 126) being connectable to the rotor (16, 116), a second assembly element (6, 106) being connectable to the stator (10, 110), and guiding means (28, 128) for guiding the first assembly element (26, 126) coaxially aligned to the second assembly element (6, 106).

The present disclosure relates to methods (40) and assemblies for installing a bushing (50) in a root (16) of a wind turbine blade (10). The present disclosure further relates to methods (40) and assemblies for replacing a bushing of a wind turbine blade (10). A method (40) comprises providing (41) a bushing hole (51); inserting (42) a bushing (50) wrapped in a reinforcement fabric (52) in the hole (51), the bushing (50) being closed at a tip end portion. The method (40) further comprises creating (43) vacuum in the hole (51), infusing (44) the reinforcement fabric (52) with resin, and curing the resin.

An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing; a turbine support case secured to the bearing housing, the scroll case disposed axially between the turbine support case and the bearing housing, the turbine support case having spokes extending through the scroll case and radially supported by the bearing housing; and heat shields distributed around the central axis in circumferential alignment with the spokes and extending axially through the scroll case for thermally shielding the spokes, a heat shield of the heat shields disposed around a spoke of the spokes, the heat shield defining an air gap surrounding the spoke inside the scroll case.

A cooling flow arrangement for a ceramic matrix composite (CMC) component of a turbine engine, wherein the CMC component includes a hot side configured for exposure to a hot gas path of the turbine engine and an opposing cold side. At least one cavity is provided in the CMC component, the at least one cavity having an entrance disposed on the cold side that is configured for receiving a cooling flow. A seal is disposed adjacent the at least one cavity and the cold side of the CMC component and is configured to provide a seal between the CMC component and an upstream turbine component. At least one hole extends through the seal and is positioned to provide the cooling flow to the at least one cavity of the CMC component.

A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan, the fan comprising a plurality of fan blades; a turbomachine drivingly coupled to the fan, the turbomachine comprising a compressor section with a low pressure compressor, a turbine section with a low pressure turbine, a reduction gearbox, and an outer casing, the low pressure turbine drivingly coupled to the low pressure compressor across the reduction gearbox; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle at a location downstream of the plurality of fan blades, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip.

A tower structure of a wind turbine includes a plurality of tower sections stacked atop each other in an end-to-end configuration along a vertical axis to form the tower structure of the wind turbine at a wind turbine site. Each of the tower sections is formed of at least one first tubular portion and at least one second tubular portion. Further, the first and second tubular portions of each of the plurality of tower sections are concentric with each other. Moreover, the first tubular portion is formed at least in part, of a cementitious material and the second tubular portion is formed of a perforated material having a plurality of holes.

A helicopter has an air inlet barrier filter (IBF) system including a guide rail extending axially along one side of a nacelle housing a helicopter engine. A filter panel is slidable along the guide rail for movement between a filtered position in which the filter panel covers an air inlet of the nacelle and an unfiltered position in which the filter panel uncovers a total surface area of the air inlet to provide for a fully unobstructed air flow to the engine.

The invention provides a method for repairing a wind power blade, which comprises the following steps: carrying out polishing treatment on a region, with a damaged site, of a wind power blade to be repaired to form one or more regions to be filled, and covering the damaged site corresponding to each region to be filled; filling bodies are placed in the to-be-filled areas for filling treatment, and each filling body is of a grid structure; and under the negative pressure condition, an adhesive is injected into the to-be-filled area where the filling body is placed, curing and polishing treatment are conducted, and therefore the to-be-repaired wind power blade is repaired. According to the repairing method, the repairing mode that the filling body with the grating structure is combined with the adhesive is adopted, the advantages of the grating structure in the aspects of mechanical property improvement, light weight, energy absorption and the like are fully played, meanwhile, the bonding and curing effects of the adhesive are utilized, repairing of the damaged site of the wind power blade is achieved, and the repairing efficiency is improved. And the mechanical property and reliability of the repaired wind power blade are remarkably improved, the repairing cost is reduced, and good application prospects and economic benefits are achieved.

A reusable upper stage rocket or other atmospheric re-entry vehicle includes a nose, a base opposite the nose, and a propulsion engine toward the base. The propulsion engine includes a high pressure chamber and a nozzle configured to exhaust gas generated by the high pressure chamber. The nozzle includes an initial nozzle portion, a secondary nozzle portion downstream of the initial nozzle portion, and a nozzle exit at a downstream end of the secondary nozzle portion. The secondary nozzle portion includes an inner expansion surface, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.

A solid airfoil assembly (60) comprises: - a solid airfoil body (62) including a leading edge (70) and a trailing edge (72), a suction side (74) opposite a pressure side (72), a first trunnion (78) proximate the leading edge opposite a second trunnion (80) proximate the leading edge; - a faceplate cavity (88) formed within the solid airfoil body; - an inlet port (82) formed through the first trunnion; - a major airflow passage (90) formed within the faceplate cavity, the major airflow passage being in fluid communication with the inlet port; - a minor airflow passage (92) formed within the solid airfoil body within the faceplate cavity, the minor airflow passage being in fluid communication with the major airflow passage; - an exit port (94) in fluid communication with the minor airflow passage, the exit port being in fluid communication with the inlet port; and - a cover (64) attached to the faceplate cavity enclosing each of the major airflow passage and the minor airflow passage.

Systems and methods for measuring an axial position of a phonic wheel or other rotating component are provided. The system includes a phonic wheel rotatable about a rotation axis and translatable along the rotation axis, a first sensor, a second sensor and a computer. The phonic wheel includes an inclined tooth having an axially non-uniform radial height and a reference tooth having an axially uniform radial height. The first sensor generates a positioning signal indicative of a gap between the inclined tooth and the first sensor. The second sensor generates a reference signal indicative of a gap between the reference tooth and the reference sensor. The first and second sensors have different orientations. The computer generates an output indicative of the axial position of the phonic wheel based on the positioning signal and the reference signal.