3588results about "Engine manufacture" patented technology

A turbine airfoil with a film cooling hole having a bell mouth shaped opening that has expansion in both the side walls and the downstream wall of from 15 to 25 degrees. The film cooling hole includes an expansion section formed with two long ribs and one short rib to form three inlets of equal cross sectional areas so that the flows into the three passages are the same. The short rib forms two middle passages to combine with two outer passages to form four exit passages for the film hole. The two side walls are curved outward in the stream-wise oriented film hole and have an expansion of from 0 to 5 degrees in the compound angled film hole.

The present invention relates to wind generators installed off-shore, in particular at sea, to support structures forming a part of such wind generators, and to methods of making and installing such wind generators. The technical field of the invention is that of making, transporting, and installing wind generators for producing electricity, more particularly off-shore, and in large numbers, so as to form wind "farms". The wind generator of the invention comprises a wind turbine and a deployable telescopic pylon or support supporting the turbine, and a gravity base supporting the pylon or support.

First stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.055 inches in directions normal to the surface of the airfoil.

A material system (60) contains close packed hollow shapes (50, 70) having a dense wall structure (52, 66), which are bonded together and which may contain a matrix binder material (56) between the shapes, where the system has a stable porosity, and is abradable and thermally stable at temperatures up to possibly 1700° C., where such systems are useful in turbine apparatus.

An inlet air treatment system. The inlet air treatment system includes a housing with more than two symmetric sides. Each of the sides includes a number of air filters and a number of spray arrays. A central air deflector is positioned within the housing.

There has been invented a turbine engine with a single rotor which cools the engine, functions as a radial compressor, pushes air through the engine to the ignition point, and acts as an axial turbine for powering the compressor. The invention engine is designed to use a simple scheme of conventional passage shapes to provide both a radial and axial flow pattern through the single rotor, thereby allowing the radial intake air flow to cool the turbine blades and turbine exhaust gases in an axial flow to be used for energy transfer. In an alternative embodiment, an electric generator is incorporated in the engine to specifically adapt the invention for power generation. Magnets are embedded in the exhaust face of the single rotor proximate to a ring of stationary magnetic cores with windings to provide for the generation of electricity. In this alternative embodiment, the turbine is a radial inflow turbine rather than an axial turbine as used in the first embodiment. Radial inflow passages of conventional design are interleaved with radial compressor passages to allow the intake air to cool the turbine blades.

The invention relates to a wind turbine blade (5) comprising at least two wind turbine blade sections (12, 13) that include one or more strengthening structures (6, 6a, 6b), the ends (14, 15) of said strengthening structures being connected in a connection joint. The ends include corresponding connection surfaces, the one or more relevant dimensions of said surfaces being larger than the dimensions of the transverse surfaces of the strengthening structures at said ends. The one or more relevant dimensions of said connection joint are larger than that of the adjacent strengthening structure. The invention also relates to a wind turbine blade in which the at least two wind turbine blade sections include a number of substantially oblong carbon fiber strips and strips of one or further materials such as wood or glass fiber. The invention further relates to a wind turbine blade section, an assembly plant for assembling wind turbine blade sections (12, 13) and to a method and use of such wind turbine blades.

A hub-side leading edge part of a fan first-stage rotating blade 10 for taking an air thereinto more extends in a forward direction of an engine than a tip-side leading edge part and a mid-span leading edge part. The hub side of the fan first-stage rotating blade 10 is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span. A radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.

An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.

A method and system for assembling large wind turbine blades that includes providing a plurality of wind turbine blade segments. An adhesive distribution arrangement is disposed on a surface of at least one of the plurality of the wind turbine blade segments. The adhesive distribution arrangement includes a bonding grid having a plurality of adhesive distribution openings. The wind turbine blade segments are directed together and sufficient adhesive is provided to the bonding grid to substantially fill an area between the wind turbine segments. The adhesive is then cured to form a bonded joint, the bonding grid being incorporated into the bonded joint. A bonding grid for use with the method and system and a segmented wind turbine blade are also disclosed.

A process for mass production of three-dimensional articles made of intermetallic compounds based on titanium and aluminium by an electron beam melting technology. The articles are produced in successive sections from powders of the intermetallic compound with which the articles are to be produced. For each section, melting of the powders preceded by a preheating step is performed.

PCT No. PCT/JP95/01817 Sec. 371 Date Jun. 2, 1998 Sec. 102(e) Date Jun. 2, 1998 PCT Filed Sep. 13, 1995 PCT Pub. No. WO97/10066 PCT Pub. Date Mar. 20, 1997A method for producing titanium alloy turbine blades comprising the steps of (a) forming turbine blades of titanium alloy through hot forging or machining, (b) cooling leading edges on tip portions of the turbine blades including covers thereof formed through hot forging or machining faster than blade main body after final hot forging or solid solution treatment, and (c) heat treating the cooled turbine blades. With this method, it is possible to manufacture titanium turbine blades in an economical fashion and obtain titanium alloy turbine blades superior in reliability by preventing erosion.

An exhaust mixer assembly having a twisted mixer and an open centerbody is provided. The open centerbody is centrally disposed within the twisted mixer and helps to provide efficient cooling of exhaust air from gas turbine engines. A method for cooling exhaust air from a gas turbine engine using the exhaust mixer assembly of the invention is also provided.

The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame. The filtration unit may include a positioning slot therein such that the positioning element extends through the positioning slot when the filtration unit is mounted within the holding frame.

Apparatus and methods related to wind turbine blades and manufacturing of the blades.

A device for releasing gas into molten metal includes a base having a discharge. The discharge has a first section including a first cross-sectional area and a second section including a second cross-sectional area, wherein the first section is upstream of the second section and the first cross-sectional area is smaller than the second cross-sectional area. A gas-release opening is positioned so that it can release gas into one or more of the first section or the second section. As the molten metal moves from the first cross-sectional area to the second cross-sectional area gas is released into the molten metal and the molten metal flow helps to draw the gas into the flow, thereby lowering the pressure required to release gas into the molten metal. Metal-transfer conduits other than a discharge incorporated in a pump base are also disclosed, as are pumps including either a discharge or other metal-transfer conduit according to the invention.

At least one shroud segment, floating axially independently of adjacent turbine engine shroud assembly members, includes a segment body comprising a radially outer surface and a radially outwardly projecting segment support that includes an axial support wall surface therein. The assembly includes a shroud hanger in axial juxtaposition with the segment support, and at least one axial support projection from the shroud hanger into the segment support at the support wall surface. The support projection supports the shroud segment releasably at the support wall surface sufficiently to enable relative axial movement of the shroud segment on the support projection independently of the shroud hanger and adjacent engine members.

An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.

Ionomeric polymer sensors, actuators, and transducers and methods for fabricating them are disclosed. One embodiment of the sensors, actuators, and transducers possess a high surface area electrode layer that is applied by hot pressing and a highly conductive surface layer. Another embodiment of these sensors, actuators, and transducers possess a high surface area electrode layer that is penetrated by electronically conductive nanowires. Methods for fabricating these sensors, actuators, and transducers are disclosed. These methods involve the formation of the high surface area layer from a liquid mixture that contains ionomeric polymer, electronically conductive particles, and possibly diluent. This mixture is formed into layers either directly on an ionomeric polymer, on a separate transfer decal, or on an electronically conductive layer. This electronically conductive layer may also include an array of nanowires. These electrode layers are then attached to an ionomeric polymer membrane by hot pressing. The ionomeric polymer membrane may be swollen with a diluent either prior to the hot pressing or after the hot pressing step. Also, the ionomeric polymer membrane may be formed by casting from a liquid mixture containing ionomeric polymer and diluent.

A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering.

An optical inspection system is for visually inspecting the blades of a turbine at turning gear operation. The inspection system includes an imager for capturing images of the blades, an optical passage coupled to the imager and structured to provide maximum viewing area of the blades through an inspection port in the turbine and an illuminating assembly adapted to illuminate the blades while the imager captures images thereof. A method wherein the captured blade images are inspected for blade defects, is also disclosed.

An engine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Extending from a surface of the platforms is a trailing edge ridge structure which adjoins the pressure sides, suction sides, and trailing edges of the airfoils with their respective platforms.

The invention relates to a wind turbine including a foundation and a tower positioned on the foundation where the tower includes more than one modules, where the modules each include a separate strengthening structure defining the outer edges of the module and wind turbine equipment, and where the more than one module are positioned substantially vertically on top of each other in an upright position within the tower. The modules are connected directly and/or indirectly through the strengthening structure, to the foundation (18). The invention further relates to a method for assembling a wind turbine at a wind turbine site and a method for handling more than one wind turbine modules.

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.

An exhaust gas diffuser includes a center body having an inlet adapted for coupling to a gas turbine, an outer wall, an inner wall and an end downstream from the inlet. The inner wall forms a continuous curve from an entry location to the end. The diffuser also includes a second portion coupled to the end of the of center body.

An airfoil used in a gas turbine engine, especially a large rotor blade in an industrial gas turbine engine, the airfoil having at least one cooling air supply cavity formed by an inner wall of the airfoil to supply cooling air to the airfoil, and a plurality of mini-serpentine cooling modules formed between the inner wall and the outer wall surface of the airfoil providing near-wall cooling for the airfoil. The modules includes three-pass or five-pass serpentine cooling channels with an inlet in fluid communication with the cooling air supply cavity and an outlet opening onto the airfoil surface to provide film cooling to the airfoil. The length of a straight section of the passage is about 5 to 10 mm and about 1 mm in diameter. A plurality of supply cavities are formed within the inner wall and separated by ribs. A plurality of mini-serpentine cooling modules is arranged along a chordwise length of the airfoil and each is in fluid communication with the nearest supply cavity.

The present invention provides a nonlinearly stacked low noise turbofan stator vane. The stator is in an axial fan or compressor turbomachinery stage that is comprised of a collection of vanes whose highly three-dimensional shape is selected to reduce rotor-stator and rotor-strut interaction noise while maintaining the aerodynamic and mechanical performance of the vane. The nonlinearly stacked low noise turbofan stator vane reduces noise associated with the fan stage of turbomachinery to improve environmental compatibility. The stator vane has a characteristic curve that is characterized by a nonlinear sweep and a nonlinear lean.

A method for forming a bond between a first and a second shell of a blade is provided. The method comprises the steps of forming a cavity between said first and second blade shells and filling an adhesive into said cavity to form a bond line between said first and second blade shells.

An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only to four decimal places, wherein Y represents a distance from a platform on which the airfoil is mounted, and X and Z are coordinates defining the profile at each distance Y from the platform.

A method for mounting a wind turbine blade to a wind turbine hub by use of a crane boom is provided. The orientation of the blade is kept substantially horizontal when the blade is lifted off the ground and mounted to the rotor hub. Control wires which connect the blade via the crane boom to a winch arrangement are used for keeping the blade orientation substantially horizontal in addition to at least one bearing wire for bearing the blade weight.