Abstract: An electronic flight bag computer (EFB) includes a housing defining first and second compartments that are fluidly isolated from and in thermal communication with one another. The first compartment contains electronic components connected to a user interface on an exterior portion of the housing for providing interactive flight related computation functions to a user. The second compartment contains a forced convection cooling component in thermal communication with the electronic components. The forced convection cooling component directs a flow of cooling fluid into the second compartment to convey heat produced by the electronic components out of the housing, such that the cooling fluid in the second compartment remains fluidly isolated from the electronic components in the first compartment of the housing.

Abstract: An enhanced multi-phased wind power generating system is disclosed that creates power from flow through an air inflow chamber and by second phase air flow that does not pass through the inflow chamber. In one embodiment, a turbine extends at least partially from the air inflow chamber whereby second phase air flow that may be directed, deflected or concentrated prevailing wind, may impinge the air blades to enhance the power generation of the system. In another embodiment, second phase air flow may be deflected by a configuration of air deflectors to create a low pressure over a flow tube to enhance power generation. Air deflectors and/or air scoops are described in any number of configurations to further increase and optimize power generation. In one embodiment an impingement chamber is attached to the inflow chamber and one or both chambers may comprise protective fencing material.

Abstract: An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a ratio of a number of stages in the low-pressure turbine to a number of stages in the high-pressure turbine is 2.

Abstract: A method for fabricating a gas turbine engine component including an inner ring, an outer ring and at least one strut connecting the inner ring with the outer ring includes the steps of connecting the inner ring to the outer ring via a load carrying edge of the strut, and attaching a side face component of the strut in abutment with the load carrying edge after the step of connecting the inner ring to the outer ring has been performed. A as turbine engine component fat by the method is also provided.

Abstract: A turbine rotor for a turbocharger, in particular for a motor vehicle, has a turbine wheel which is formed in one piece and which has a turbine blade arrangement and a solid turbine wheel shoulder with a first end surface without cavities or depressions. A rotor shaft is formed in one piece and has a second end surface with a depression arranged coaxially with respect to the rotational axis. The first end surface of the turbine wheel shoulder is connected to a second end surface of the rotor shaft in a cohesive fashion by way of a friction weld. There is also provided a turbocharger and a method for producing a corresponding turbine rotor.

Abstract: A service tube apparatus for a gas turbine engine includes a service tube assembly having: (a) an elongated, hollow service tube; and (b) a service tube baffle surrounding the service tube which is pierced with a plurality of impingement cooling holes.

Abstract: The invention proposes that the shaft-hub connection of a rotatable cell rotor (7) of a gas-dynamic pressure wave machine (6) for charging a combustion engine be composed of individual sheet metal parts having a hub outer body made of a tube, or of a mixture of hub outer bodies (71), and a disk (18) as a cast shaft holder. According to the invention, this is to replace a shaft-hub connection that is a solid casting.

Abstract: An example compressor shroud assembly includes a shroud body extending along an axis and having a hollow bore. An enlarged flange is located at one axial end of the shroud body. The enlarged flange provides a rotating surface for a retention plate on a first side and a rotating surface for a drive ring on an opposing, second side. The enlarged flange establishes a channel that receives the retention plate. The channel has a ratio of the channel depth to the channel width that is between 0.0216 and 0.0251.

Abstract: A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs.

Abstract: Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections (11A, 11B) formed of two-or-more-stage impeller vanes (14a to 14h) arranged between bearings (21a, 21b) on a rotor shaft (13) consisting of a single shaft are housed in a signal casing (10).

Abstract: A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors.

Abstract: Methods and apparatus are provided for a fan containment system for a gas turbine engine having a plurality of fan blades includes a cylindrical casing with an inner surface surrounding the plurality of fan blades and an opposing outer surface; a first layer of fabric material positioned on the exterior surface of the cylindrical casing; and a shear thickening fluid impregnated within the first layer of fabric material.

Abstract: A disclosed fan containment case includes a mount ring that supports a portion of the engine core. The mount ring includes openings and features that define a mounting location for the gas turbine engine. The example fan containment case includes a generally cylindrically shaped fan case that extends between an open front end and an open rear end. The mount ring is secured onto an outer surface of the fan case and includes a mounting lug and a plurality of openings for attachment of gas turbine engine components.

Abstract: A casing includes an inner shell and an outer shell that surrounds the inner shell and comprises a plurality of inflection points. An annular flange is between the inner shell and the outer shell, and a plurality of joints attach the inner shell to the annular flange. A connector is between the annular flange and the outer shell at each of the plurality of inflection points. A method for assembling a casing includes joining a plurality of curved sections to one another to generally define an arcuate inner shell and surrounding the arcuate inner shell with an outer shell. The method further includes attaching the arcuate inner shell to an annular flange at first attachment points and connecting the annular flange to the outer shell at second attachment points spaced approximately equidistantly from the first attachment points.

Abstract: The present invention relates to a multi-stage turbocharger arrangement (1), having a high-pressure turbocharger (20) which has a turbine housing (26A), a bearing housing (27A), a compressor housing (28A); and having a low-pressure turbocharger (21) which has a turbine housing (26B), a bearing housing (27B), a compressor housing (28B); wherein the turbine housings (26A, 26B) are provided with an integrated inner shell (23) for conducting exhaust gas.

Abstract: A wind power converting apparatus that includes a rotor unit. The rotor unit includes a rotary blade assembly and a cover. The rotary blade assembly has a rotary blade disposed in the longitudinal direction of the rotary shaft, and is rotated by the wind from the outside. The cover blocks a headwind, which blows opposite to the direction in which the rotary blade assembly is rotated, from being introduced to the rotary blade assembly. According to the wind power converting apparatus, the operating efficiency of the wind power converting apparatus is increased, power generation is possible even in light wind, and a plurality of generators can be connected together.

Abstract: An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks.

Abstract: A fan nacelle for a gas turbine engine includes a leading edge region with a flow path between an intake region in a nacelle outer surface and an exhaust region in a nacelle inner surface to locally modify a flow around the leading edge region during a predefined off-design condition.

Abstract: A disclosed fan containment case includes a fan case fabricated from a plurality of non-metallic composite layers with an attachment flange formed of both a composite portion and a metallic backing. The disclosed metallic backing is mounted on a rearward facing surface of a composite portion of the attachment flange.

Abstract: There is provided a fan unit including a shutter capable of closing the shutter despite a change in installation direction of the fan unit, an electronic apparatus including such fan unit, a method of opening/closing the fan unit, and the shutter. In the fan unit with the shutter, the shutter is opened and closed in different directions according to the installation direction of the fan unit.

Abstract: A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.

Abstract: The present disclosure provides methods, assemblies, and systems for power production that can allow for increased efficiency and lower cost components arising from the control, reduction, or elimination of turbine blade mechanical erosion by particulates or chemical erosion by gases in a combustion product flow. The methods, assemblies, and systems can include the use of turbine blades that operate with a blade velocity that is significantly reduced in relation to conventional turbines used in typical power production systems. The methods and systems also can make use of a recycled circulating fluid for transpiration protection of the turbine and/or other components. Further, recycled circulating fluid may be employed to provide cleaning materials to the turbine.

Abstract: Aspects of the manufacturing of Flow Deflection Devices (FDDs) for wind turbines are presented as a system that requires adjustments in order to improve power output and adjust for changes in different conditions yet provides stability of shape.

Abstract: A cooling structure for a working vehicle in which a shroud is attached to a radiator provided to a vehicle body, and an air-cooling fan is made face to an airflow opening of the shroud, wherein the shroud comprises a shroud body attached to the radiator, and an opening member having the airflow opening, and further comprises securing means capable of fixing the opening member to the shroud body, and of freely adjusting a fixing position of the opening member with respect to the shroud body, and a relative position between the air-cooling fan and the airflow opening of the shroud is made freely adjustable. With the configuration above, the sufficient amount of heat radiated by the radiator can be obtained without causing the disadvantages such as increased noise.

Abstract: An air current generating system and method, includes an air source, a passage (105), at least a motor-less air pump device (104) and at least a turbine generating set (102, 103); the passage has an air current inlet connected with the air source and an air current outlet; the motor-less air pump device is mounted at the air current outlet and in the natural wind; the turbine generating set at least includes a rotating blade provided in the passage; the motor-less air pump device is driven by the air current from the air source and/or the outside wind to form negative pressure in the passage, absorbs air from the air source continuously and forms an air current in the passage, wherein the air current rotates the rotating blade to drive the turbine generating set to generate electricity.

Abstract: A method and apparatus for controlling distortion in the casing of a gas turbine are disclosed. The method uses a split in the flange ID underneath “false” flanges to tune the hoop stiffness of the casing to match the stiffness and behavior of the bolted joint. By matching the hoop carrying capability and load path of the split-line flange, as well as the thermal mass effect, the distortion can be channeled to a higher order distortion mode that can evenly distribute the deflection and approach a pure circular form.

Abstract: A vacuum pump rotor suitable for use in a vacuum pump is described for a vacuum pump that comprises a regenerative pumping mechanism. The rotor has a generally disc-shaped configuration and is mounted on an axial shaft for rotation relative to a stator of a vacuum pump. The rotor has a first and second opposing surface on which a rotor formations are disposed, each rotor formation defining a portion of a pump stage formed between the pump rotor and a stator for pumping gas from an inlet to an outlet in the same radial direction along the first and second opposing surface. A conduit is provided to interconnect the portions of the pump stage and assist with pressure imbalance that might occur on opposing sides of the rotor.

Abstract: A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust ring is coaxially disposed within the turbine case. The splash plate extends axially along the turbine exhaust ring, radially spaced between the turbine exhaust ring and the turbine case. There are cooling fluid apertures in the turbine case to provide cooling fluid flow from the bypass duct onto the splash plate, and impingement holes in the splash plate to provide impingement flow onto the turbine exhaust ring.

Abstract: The present invention relates to a nacelle for a wind turbine, the nacelle having a first height in its installed position and a second height in its transported position, the first height being higher than the second height, comprising a bottom part having a bottom face and two opposite side faces defining a space and a width of the bottom part and a top part. In the transported position, the top part extends inside the width or outside the width in order to cover at least part of the space. The invention also relates to a transportation kit and a transport method.

Abstract: A vane profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Y-coordinates.

Abstract: A gas turbine transition duct is provided comprising a generally tubular main body having first and second ends, the first end being adapted to be positioned adjacent to a combustor unit and the second end being adapted to be positioned adjacent to a turbine and a collar coupled to the main body second end. The collar may have upper, lower and side portions. At least one of the side portions may be provided with a notched section.

Abstract: A compressor has a housing defining a gas inlet flow path and a gas outlet and a rotatable impeller wheel between the gas inlet flow path and the gas outlet. The housing has an inner wall defining a surface located in close proximity to radially outer edges of impeller wheel vanes that sweep across said surface as the impeller wheel rotates. At least one opening is provided in the inner wall at the surface. A port is provided in the compressor housing in gas communication with the at least one opening and for diverting gas in a direction away from the gas inlet flow path during relatively low gas flow rate conditions. A gas displacement device such as a pump is disposed outside of the gas inlet flow path and connected to said port, the pump being operable to remove gas selectively through the at least opening and the port in a direction away from said gas inlet flow path.

Abstract: A composite material and method for manufacturing the material, the material including: a plurality of plies layered one on top of the other; and one or more through-thickness fibres which join one or more of the plurality of plies to one another; wherein the one or more through-thickness fibres form a boundary which delineates one or more discrete regions of the material.

Abstract: A fan includes a casing that is composed of a front cover and a rear cover, a base mounted under the casing, and blades rotatably mounted in the casing. The base includes support frames symmetrically mounted thereto. The front and rear covers are each composed of a plurality of circular frames of different diameters. The rear cover has a lower portion that forms slots corresponding to the support frames so that the support frames are movably received through the slots respectively. A connection bar is connected to the rear cover so that the casing may undergo vertical and horizontal rotations through the arrangement of the slots for adjusting direction of airstream generated by the fan, thereby realizing an effect of indoor air circulation. Further, due to the arrangement of the rotation structure inside the casing, the outside appearance of the fan shows a sense of completeness of aesthetics.

Abstract: A hydraulic pump has a rotor and a hollow housing with a main interior chamber. The rotor is rotatably mounted in the main interior chamber. A smaller interior chamber is separated from the main interior chamber such that the smaller interior chamber retains gas therein when the main interior chamber is filled with a liquid.

Abstract: A fan section of a gas turbine engine includes nacelle inlet and a fan containment case that are integrally formed together as a single-piece component.

Abstract: A side channel pump for conveying fuel having a flow divider disposed in an impeller. The flow divider divides blade chambers of the impeller into individual partial chambers. Flow dividers are also disposed in housing parts opposing the impeller having partial ring-shaped channels radially encompassing each other. The flow dividers in the impeller and in the housing parts are at a distance from each other in order to allow cross flow between the conveyance chambers formed by the partial chambers and the partial ring-shaped channels. The side channel pump thereby has a high efficiency and particularly low radial dimensions.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Abstract: A compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly thereform to define a gap therebetween; a plurality of grooves disposed in the inner surface of the casing and extending in a generally circumferential direction, the plurality of grooves including a first groove and a second groove; and a channel system comprising at least a first channel positioned within the casing and configured to provide fluid communication between the first groove and the second groove.

Abstract: An impeller for use in a containment structure has a hub, a blade attaching to the hub for compressing air as the blade rotates with the hub, and an annulus disposed about the hub whereby the annulus reduces an effect of the hub breaking apart such that a weight of the containment structure is reduced.

Abstract: This invention employs the isentropic acceleration of a basic air flow, supplied by the wind, through a converging/diverging De Laval Nozzle, to thereby enormously increase the air flow speed and power at the nozzle throat section and to simultaneously lower the pressure there to approximately one-half of ambient pressure. This low throat pressure is then used as a ‘vacuum’ source to activate a high speed isentropic flow of air through a power take-off means consisting of a flow rotor which converts the energy of the accelerating linear air flow through it into rotational energy suitable for take-off to do useful external work at very low cost. The invention can also be mounted on a moving vehicle so that the relative air flow past the vehicle supplies the air flow to produce the high power output at very low cost.

Abstract: The invention relates to a light floating flue consisting of a wall of fibre-reinforced film which rotates about its axis to balance the reduced pressure in the flue with the centrifugal force on the gases in the flue and with the flue wall. The flue floats due to the friction with the rising air, the upward force of the lighter gases, optionally a zeppelin and balloon-like bodies filled with helium or hydrogen. In order to prevent bending moments on the flue, the flue is attached to the base of the tower by means of a tillable bearing.

Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

Abstract: A method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method.

Abstract: A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have an internal passage extending between an inlet to an outlet. An axis of the transition duct body may be generally linear such that gases expelled from the transition duct body flow in a proper direction into the downstream turbine blades. The linear transition duct may include an outlet with exhaust mouths that are configured such that sides of the transition duct are coplanar with adjacent transition ducts, thereby eliminating destructive turbulence between adjacent, linear transition ducts.

Abstract: An apparatus and associated method for directing windage involves a body defining an aperture. A fastener is operably disposed in the aperture and is selectively engageable with a fixed support member between a first mode permitting rotation of the body around the fastener longitudinal axis, and a second mode affixing the body in place to the support member at a desired rotational orientation. A shroud depends from the body and is sized at a distal end for an operable mating relationship adjacent an arcuate edge of a disc that is rotatable around a disc axis. The shroud distal end is operably disposed a first distance from the fastener longitudinal axis in a direction of a plane including the fastener longitudinal axis and the disc axis. A leading edge of the shroud, with respect to a direction of windage established by disc rotation, is disposed a second distance from the fastener longitudinal axis that is the same or less than the first distance from the fastener longitudinal axis.

Abstract: A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath.

Abstract: An impeller shroud is configured to receive an impeller. The impeller shroud establishes a plurality of air-bleed holes configured to communicate air with an impeller. The air-bleed holes are circumferentially distributed about the impeller shroud. The circumferential spacing between some adjacent air-bleed holes within the plurality of air-bleed holes is different than the circumferential spacing between other adjacent air-bleed holes within the plurality of air-bleed holes. A diffuser vane is configured to direct pressurized air to the combustor, the diffuser vanes are circumferentially distributed about the blade exducer. The circumferential spacing between some adjacent diffuser vanes within the plurality of diffuser vanes is different than the circumferential spacing between other adjacent diffuser vanes within the plurality of diffuser vanes.

Abstract: A generator system includes a pipe line which includes a control valve for diverting input gas or liquid into a pair of bypass pipe lines, whose output is coupled with two nozzle venture inlets in a turbine housing. Gas or liquid entering the turbine housing through the nozzle venture inlets rotates a turbine impellor having a generator shaft to generate energy. Gas or liquid exiting from the turbine housing, along with diverted input gas or liquid, pass through an ejector device which eliminates back pressure and restores any pressure loss.

Abstract: A turbine that includes a rotor, an inner turbine shell, an outer turbine shell, and a sliding engagement between the inner turbine shell and the outer turbine shell. The inner turbine shell is a single piece construction that completely surrounds at least a portion of the rotor, and the outer turbine shell surrounds the inner turbine shell. A method for aligning turbine components that includes aligning a single-piece inner turbine shell substantially concentric with a rotor and surrounding the single-piece inner turbine shell with an outer turbine shell. The method further includes supporting the single-piece inner turbine shell with respect to the outer turbine shell using a bearing assembly between the single-piece inner turbine shell and the outer turbine shell.