11134results about "Engine manufacture" patented technology

An impeller according to an example of the present invention comprises a hub, and at least one blade supported by the hub. The impeller has a deployed configuration in which the blade extends away from the hub, and a stored configuration in which the impeller is radially compressed, for example by folding the blade towards the hub. The impeller may comprise a plurality of blades, arranged in blade rows, to facilitate radial compression of the blades. The outer edge of a blade may have a winglet, and the base of the blade may have an associated indentation to facilitate folding of the blade.

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.

A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.

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.

An impeller according to an example of the present invention comprises a hub, and at least one blade supported by the hub. The impeller has a deployed configuration in which the blade extends away from the hub, and a stored configuration in which the impeller is radially compressed, for example by folding the blade towards the hub. The impeller may comprise a plurality of blades, arranged in blade rows, to facilitate radial compression of the blades. The outer edge of a blade may have a winglet, and the base of the blade may have an associated indentation to facilitate folding of the blade.

An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

A fatigue resistant gravity based spread footing under heavy multi-axial cyclical loading of a wind tower having a central vertical pedestal, a substantially horizontal continuous bottom support slab with a stiffened perimeter, a plurality of radial reinforcing ribs extending radially outwardly from the pedestal and a three-dimensional network 500 of post-tensioning elements that keep the structural elements under heavy multi-axial post compression with a specific eccentricity that is intended to reduces stress amplitudes and deflections and allows the foundation to have a desirable combination of high stiffness and superior fatigue resistance. The foundation design reduces the weight and volume of materials used, reduces cost, and improves heat dissipation conditions during construction by having a small ratio of concrete mass to surface area thus eliminating the risk of thermal cracking due to heat of hydration.

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.

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 has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.

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 tower comprises a base tower member fixed on a base in the ground, a lower tower member hingedly connected at a lower end thereof with an upper end of the base tower member through a hinge and swinging between a lying position and a standing position, a first stage connecting tower member connected at a lower end thereof with an upper end of the lower tower member, a second stage connecting tower member connected at a lower end thereof with an upper end of the first stage connecting tower member, and a third stage connecting tower member connected at a lower end thereof with an upper end of the second stage connecting tower member. Thus formed tower is raised swingingly around the hinge from the lying position to the standing position. A nacelle includes a tower penetrating hole through which the tower vertically penetrates and is formed by a plurality of nacelle sections divisible around the tower penetrating hole. After the tower is built, a plurality of nacelle sections are collected around the tower and are connected with each other while the nacelle is penetrated by the tower. Then, the nacelle is lifted up along the tower in that state and fixed to the top end of the tower.

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.

Methods, systems, and apparatuses for exhaust silencers for engines, such as microturbines, are described. An exhaust silencer reduces noise produced by an engine. While passing through an exhaust silencer, an exhaust stream from the engine makes one or more turns, thereby reducing turbine noise. An exhaust silencer includes a body, a cavity in the body, a baffle plate that partially divides the central cavity, an inlet port formed in a first surface of the body, and an outlet port formed in a second surface of the body. The inlet port is configured to receive an exhaust stream that flows through the cavity, around the baffle plate. The outlet port is configured to discharge the exhaust stream from the body.

The invention discloses a turbine fracturing semitrailer. The turbine fracturing semitrailer comprises a semitrailer body, a turbine engine, a reduction gearbox, a transmission mechanism and a plungerpump; the turbine engine, the reduction gearbox, the transmission mechanism and the plunger pump are arranged on the semitrailer body, the output end of the turbine engine is connected with the reduction gearbox, and the reduction gearbox is connected with the plunger pump through the transmission mechanism in a transmission mode. The turbine fracturing semitrailer has the beneficial effects thatthrough linear connection of the turbine engine, the reduction gearbox, the transmission mechanism and the plunger pump in the power-transmission direction, excessive transmission loss can be avoided, and efficient transmission performance is guaranteed; and the whole semitrailer is small in size, light in weight, low in the use cost, and low in failure risks.

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.

Articles having substantially cylindrical bodies including a plurality of circumferential layers, each layer having at least one ply of material, the material comprising a weave fabric, a non-crimp fabric, or a combination thereof.

An apparatus for handling a turbomachine part, particularly during disassembling and reassembling operations. More specifically, an apparatus for handling the stator cone of a gas turbine suitable to completely manipulate the stator cone during disassembling and reassembling operations. The apparatus allows to disassemble and reassemble the stator cone of a gas turbine without the need to dismount the turbomachine enclosure and without the necessity to have personnel inside the turbomachine package during the operations.

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.

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.

In a turbine bucket having an airfoil portion and a root portion with a platform at an interface between the airfoil portion and the root portion, a platform cooling arrangement including: a cooling passage defined in the platform to extend along at least a portion of a concave, pressure side of the airfoil portion, at least one cooling medium inlet to said cooling passage extending from an airfoil cooling medium cavity in a vicinity of an axial center of the airfoil portion, and at least one outlet opening for expelling cooling medium from said cooling passage.

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.

An acoustic structure that includes a honeycomb having cells in which septum caps are located. The septum caps are formed from sheets of acoustic material and include a resonator portion and a flange portion. The flange portion has an anchoring surface that provides frictional engagement of the septum caps to the honeycomb cells when the caps are inserted into the honeycomb during fabrication of the acoustic structure. An adhesive is applied to the anchoring surface of the septum caps after the caps have been inserted into the honeycomb cells to provide a permanent bond.

An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, and a mixer downstream of the low pressure turbine section and in fluid communication with the fan bypass duct, and an aft FLADE turbine downstream of the mixer. At least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine and radially extending across a FLADE duct circumscribing the fan bypass duct. The aft FLADE turbine may be a free turbine or connected to and rotatable with the low pressure turbine section. A power extraction apparatus may be disposed within the engine and drivenly connected to the aft FLADE turbine.