Abstract: A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.

Abstract: An exemplary compressor for a turbocharger includes a compressor wheel that includes first and second compressor faces oriented back-to-back and a bore for mounting the compressor wheel to a shaft along a rotational axis of the compressor wheel; and a compressor housing that includes a first air inlet oriented to pass inlet air in an axial direction along the rotational axis to the first compressor face, a second air inlet positioned a distance radially from the rotational axis and oriented to pass inlet air in an axial direction parallel to the rotational axis and radially toward the rotational axis to the second compressor face, and a single volute that receives compressed air from the first and second compressor faces.

Abstract: A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume.

Abstract: A gas turbine engine is disclosed that includes at least first and second gearboxes rotationally coupled to at least one spool. Accessory drive components are mounted on and driven by the gearboxes. The accessory drive components include, for example, a fuel pump, a hydraulic pump, a generator, a lubrication pump, or a starter. The accessory drive components are split between the two gearboxes to reduce the diameter of the nacelle adjacent to each gearbox.

Abstract: A steam turbine with at least two steam chambers which are enclosed by a basically tubular casing and which are separated from each other by means of at least one partition which is arranged in the casing, is characterized according to the invention in that the partition is formed from at least two flat partial surfaces which are formed in an inclined manner relatively to each other.

Abstract: Gas turbine engine systems involving integrated fluid conduits are provided. In this regard, a representative engine casing for a gas turbine engine includes: a casing wall; and a fluid conduit integrated into the casing wall.

Abstract: Gas turbine engine systems involving rotatable annular supports are provided. In this regard, a representative support assembly for a gas turbine engine includes: a rotatable member having a first end located about a first annulus; and a stationary member located about a second annulus; the first end of the rotatable member being rotatably coupled with the stationary member, with at least a portion of the first annulus being coextensive with at least a portion of the second annulus, the first end being operative to rotate locally with respect to a corresponding portion of the stationary member.

Abstract: The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid.

Abstract: A centrifugal turbocompressor including an open-type impeller and a casing compresses a gaseous body that condenses into a liquid. The compressor suppresses erosion due to accumulation of a liquid on a casing surface in the compressor. Such accumulation is possible during the starting time of the compressor, if the gaseous body that has come into contact with the casing condenses on the surface of the casing and changes into liquid droplets, centrifugal force may cause the droplets to accumulate on the surface of the casing positioned outside an impeller, and thus to grow into coarser and larger droplets or a liquid film. If the blade tips of the impeller rotating at high speed scrape the droplets or the film upward, erosion of the blade tips is liable to result.

Abstract: A method of assembling a turbine casing is provided. The method includes inserting a bolt assembly through a first opening defined generally vertically through a first flange extending from a first casing member, such that a portion of the bolt assembly extends a distance upward from an upper surface of the first casing flange and such that the bolt assembly is retained within the first opening. The method further includes positioning a second casing member including a second flange including a second opening defined therein against the first casing member such that a portion of the bolt assembly extends through the opening defined in the second casing flange.

Abstract: An air bleeding passage 31 through which an intake chamber 7 and a crankcase 5 communicate with each other includes at least: a radial passage 31b which is formed in the driving shaft 10 to be directed in the radial direction, and which indirectly communicates with the intake chamber 7; and a radial passage 31a which is formed in a rotor 21 fixed to the driving shaft 10 by press-fitting to be directed in the radial direction, and through which the radial passage 31b in the driving shaft 10 and the crankcase 5 are communicatively connected to each other. An inlet part 61 of the radial passage 31a in the rotor 21 is configured as a cylinder-shaped part 61 protruding from the outer peripheral part 63 thereof, and is placed not to overlap a connecting mechanism 40 in the circumferential direction, the connecting mechanism 40 used for connecting the rotor 21 and a swash plate 24 to each other.

Abstract: A plasma generator for delaying the onset of rotation stall by tip gap flow control in, for example, an axial flow compressor is disclosed. The tip gap flow control system includes a housing surrounding a rotor of blades and having an inner wall. At least one plasma generating device is coupled to the inner wall of the housing and circumscribes at least a portion of the rotor of blades. A power supply is electrically coupled to the plasma generating device such that when the power supply energizes the plasma generating device, the axial momentum of a fluid flow between the inner wall of the housing and the tips of the rotor of blades in increased in the direction of the fluid flow.

Abstract: Disclosed are retainers for a turbocharger. In one embodiment, the retainer includes a generally annular body that defines a bore and one or more channels. The bore is generally directed along a central axis of the body and can be configured to mate with a nose of a center housing of a turbocharger. The channels can be configured to accommodate vanes associated with a cartridge assembly of the turbocharger. One or more legs may extend from the retainer body and may be configured to mate with and locate the retainer relative to a cartridge assembly for the turbocharger. The retainer can also include a concave portion disposed around a perimeter of the body. The concave portion and the body may be together configured to act as a spring when the retainer is mechanically loaded in a direction having a component parallel to the central axis. Also disclosed are corresponding turbochargers.

Abstract: A compressor casing for an exhaust gas turbocharger is disclosed. The exhaust gas turbocharger has a rotatable turboshaft, a compressor wheel mounted on the turboshaft, and a turbine wheel mounted on the turboshaft. The compressor casing includes a sensor for measuring a rotational speed of the turboshaft. The sensor is embedded in the compressor casing and forms an integral component of the compressor casing.

Abstract: Disclosed is an enclosure for a gas turbine, the enclosure including an enclosure section configured to partially enclose the gas turbine, and at least one other enclosure section, the at least one other enclosure section being configured to assemble with the enclosure section in a manner that associates the at least one other enclosure section with the enclosure section, wherein said at least one other enclosure section and said enclosure section are configured to substantially enclose the gas turbine when the at least one other enclosure section is associated with the enclosure section.

Abstract: Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner.

Abstract: Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine.

Abstract: A single housing is utilized to mount both an internal fan, and an external alternate flow passage closed by a check valve. The alternate flow passage is defined between an inner and outer wall of the single housing, while the fan is mounted within the inner wall.

Abstract: A turbocharger is provided having a turbine wheel and a housing configured to at least partially enclose the turbine wheel. The housing may have a first turbine volute including a first inlet and a second turbine volute having a second inlet. The first and second volutes may be configured to communicate a first and second fluid flow with the turbine wheel. The housing may also have a wall member axially separating the first and second turbine volutes. In addition, the housing may have a valve configured to selectively allow fluid in the first inlet to communicate with fluid in the second inlet.

Abstract: A nacelle assembly includes an inlet section having a plurality of discrete sections. Each of the plurality of discrete sections includes an adaptive structure. A thickness of each of the plurality of discrete sections is selectively adjustable between a first position and a second position to influence the adaptive structure of each of the plurality of discrete sections.

Abstract: A blower comprising: a vane wheel including a pair of grooves, and blades extending in a radial direction of the vane wheel in each groove, and a casing including stationary flow paths facing to the grooves respectively so that the gas urged in the grooves is capable of flowing in a circumferential direction in the stationary flow paths, a guide flow path extending in the axial directions to fluidly communicate with both of the stationary flow paths to enable the gas to flow from one of the stationary flow paths to the other one of the stationary flow paths, an inlet port for introducing the gas into the one of the stationary flow paths facing to the one of the grooves and an outlet port for discharging the gas out of the other one of the stationary flow paths facing to the other one of the grooves.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A fan includes a frame and an impeller. The frame includes a main body, a plurality of guiding elements and a motor base. The main body has an airflow inlet and an airflow outlet. The guiding elements are disposed in the main body and located at the airflow outlet, wherein each of the guiding elements includes an inclined part and an axial extended part, and the inclined par meets the axial extended part at an angle. The motor base connects to the main body. The impeller is disposed on the motor base for providing an airflow, wherein the guiding elements guide the airflow away from the fan.

Abstract: A housing for use in high-pressure fluid applications, comprising a first passage defining a first axis (P1) and a second passage defining a second axis (P2), wherein the first and second passages intersect at an opening defined by an intersection at one end of the second passage. When sectioned on a plane normal to the second axis (P2) and not intersecting the first passage, the intersection defines an ellipse (E) in the plane and centred on the second axis (P2), the ellipse having a major axis equal in length to the width (D2) of the intersection and a minor axis equal in length to the height (D1) of the intersection. A wall of the intersection describes a curve in the plane, the curve passing through the points where the major and minor axes of the ellipse (E) meet the perimeter of the ellipse (E), and through points which lie outside the ellipse (E) and which are offset from the ellipse (E) by an offset distance (K).

Abstract: Embodiments of the present disclosure include a fan housing having a first part with a first side wall and a first back wall, a second part having a second side wall and a second back wall, where the first back wall and the second back wall meet to define an axle opening and the first and second side walls meet to define a right circular cylinder parallel with the axle opening. The first part and second part of the housing can be mirror images when positioned with the first and second sidewalls and the edge of the first and second back walls facing each other. Embodiments of the fan housing can also include a motor casing that extends from the first and second back walls away from the first and second side walls. The motor casing can contain and house a motor for turning the impeller contained in the housing.

Abstract: A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component.

Abstract: A device for supplying pulse width-modulated output pulses for the motor of a fan has an arithmetic unit and at least one final output stage. The arithmetic unit and the final output stage are disposed in a rod-shaped housing. A fan encompasses a device that is located in a rod-shaped housing and is used for supplying pulse width-modulated output pulses.

Abstract: Some embodiments of a fluid expansion system include a turbine generator apparatus in which the driven member is arranged on the outlet side of the turbine wheel. In such circumstances, the fluid output from the turbine wheel can flow towards the driven member, for example, to provide heat dissipation to some components of the turbine generator apparatus (e.g., generator electronics or the like). This arrangement of the turbine wheel relative to the driven member also permits the use of bearing supports on both the input side and the outlet side of the turbine wheel.

Abstract: A fan has an impeller, a motor and a frame. The impeller and the motor are disposed within the frame, and the motor is connected to the impeller and drives the impeller to rotate. The impeller includes a hub and an odd number of blade sets. The blade sets are disposed around the circumference of the hub. Bach blade set has a plurality of the blades, and the blades of each blade set can be the same or not. For example, the blades in each of the blade sets have different tilting angles, heights and/or lengths while the blades are connected with the hub. Or the blades in each of the blade sets have different curvatures, arc lengths, thicknesses, or side-view shapes.

Abstract: A gear case assembly includes an upper gear case and a lower gear case accommodating a drive axle, at least one rotation axle receiving power from the drive axle, and a power transmission unit for transmitting the power to the at least one rotation axis. The upper and lower gear cases are horizontally divided, and upper and a lower shrouds are integrally formed on the upper and lower gear cases proximate to ends of the rotation axis. The upper and lower shrouds form a surface for guiding a fluid that flows from an impeller connected to the rotation axle, and are horizontally divided. Scroll cases mounted on the upper and lower gear cases, together with the upper and lower shrouds, define a path for guiding the fluid that flows from the impeller. A common plane divides the upper and lower gear cases, and also divides the upper and lower shrouds.

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: Provision of panels within casings can cause problems where retaining bolts require apertures in the casings, which in turn may reduce the structural strength of that casing. By providing a loose or snug fit ring placed within the casing and appropriate retainer elements secured to that ring which in turn appropriately presents panels it is possible to provide a casing assembly which avoids the necessity of drilling or otherwise forming holes in the casing which may reduce structural strength. The rings, retainers and the panels do not need to be mechanically fixed to the casing although where possible a ring may be secured through bolts in areas of the casing where structural strength is less important. Where there is no bolting between the ring and the casing then dam elements can be provided at each end of the assembly to prevent lateral axial movement and therefore retain panel position within the casing.

Abstract: A fan has a fan, an impeller and a motor. The impeller is disposed in the fan frame, and the motor is disposed in the fan frame for driving the impeller. The fan frame has a housing, a base and at least one connecting element. The housing has an inlet and an outlet, and the base is disposed in the housing and at the outlet. The connecting element is disposed between the housing and the base. The base has a first airflow guiding structure disposed on the circumference of the base. The housing has a second airflow guiding structure disposed on the inner circumference thereof and adjacent to the outlet. The first airflow guiding structure and the second airflow guiding structure are correspondingly disposed.

Abstract: A pump for liquids at positive pressure, includes a pump chamber (18) accommodating an impeller (24), wherein the impeller (24) is axially biased against a non-rotating support element (48) which determines the axial position of the impeller (24). The shaft (42) may be coupled to a drive shaft (64) through a magnet coupling (56, 62).

Abstract: A turbine stage in a turbomachine comprising ring sectors (20) arranged about a turbine impeller (18), and an annular support (50) supporting the ring sectors and attached to a turbine casing (22), this annular support being able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Abstract: A gas turbine engine has a nacelle, a plurality of pipes and a drains assembly, the drains assembly including a drains mast that extends through the nacelle and provides an outlet for the pipes. The engine is characterised in that drains assembly has a connection block defining internal passages and is arranged to connect between the pipes and the drains mast. The connection block also has lateral connections to the pipes enabling the nacelle to have a lower profile; thereby reducing aerodynamic drag.

Abstract: A method and apparatus to reduce the axial thrust in rotary machines such as compressors, centrifugal pumps, turbines, etc. includes providing additional peripheral restrictive means (7) attached at the peripheral portion of the disk forming the subdividing means (4) on the side facing the rotating rotor (2). An additional ring element at the periphery of the subdividing means forms additional radial (11) and axial restrictive means (15). Such peripheral restrictive means (7, 11 and 15) function as sealing dams, which combined with the outward flow induced by the rotating impeller, form self-pressurizing hydrodynamic bearings in the axial and radial planes, improving rotordynamic stability. Additionally, a stationary ring element in the center of the cavity forms a seal with the rotor, reducing leakage to suction.

Abstract: A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumferentially about the rotor, and positioning the casing a distance from the plurality of rotor blades. The distance is selected to facilitate increasing an amount of initial resistance created between the casing and the plurality of rotor blades after a bladeout.

Abstract: A vacuum pump for producing low or high vacuum has a housing having a gas inlet and a gas outlet, a pumping system located in the housing, a motor for driving the pumping system, and a control electronics for controlling operation of the pump and likewise located in the housing, with the pumping system and the control electronics being located in separate housing sections of the housing.

Abstract: A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamber including a radially inner surface and a radially outer surface. The radially inner surface includes an arcuate flow surface. The flow surface includes a first portion and a second portion extending downstream from the first portion. The impeller chamber includes a variable area wherein a first cross-sectional area is defined between the radially outer surface and the first portion, and a second cross-sectional area is defined downstream from the first cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. A method of operating the compressor assembly is also included.

Abstract: Guide case (24) for use in conjunction with a water turbine (20), with a helical top wall (35) of the annular chamber (27) extended downstream of the inner wall (39) of the inlet port (30). The extension is wetted on its downstream side by the top water entering the inlet port, and on its upstream side by the bottom water. The extension serves to keep the top water separate from the bottom water until the velocity vectors of the two water streams have been aligned, therefore reducing turbulence at the point where the waters mix and merge, and enabling more of the energy to be extracted from the water.

Abstract: A transition duct for a gas turbine engine typically contains one or more non-turning fairings. These fairings disturb the air flow through the duct, leading to flow separation and aerodynamic inefficiency. The invention proposes non-axisymmetric perturbations in the duct end walls to minimise these undesirable aerodynamic effects. This permits the construction of shorter and lighter transition ducts, with more pronounced curvature.

Abstract: A vane pump includes a rotor accommodated in a rotor chamber; a plurality of vanes attached to the rotor, each of the vanes having a leading end adapted to make sliding make a contact with an inner peripheral surface of the rotor chamber. Further, the vane pump includes working compartments surrounded by inner surfaces of the rotor chamber, an outer peripheral surface of the rotor and the vanes, the working compartments being adapted to undergo a volume change as the rotor is rotatably driven; an inlet port through which a working fluid is drawn into a working compartment whose volume is being increased; and an outlet port through which the working fluid is discharged from a working compartment whose volume is being decreased; and one or more blade base members protruded from portions on the outer peripheral surface of the rotor between the vanes adjacent to each other.

Abstract: A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segment. The shroud support includes a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge. An annular shroud ring structure includes a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger. Cooling air is extracted from a compressor positioned upstream of the turbine shroud assembly.

Abstract: A method for assembling a gas turbine engine includes coupling a rotor assembly including a plurality of rotor blades about a rotatable main shaft of the gas turbine engine. The main shaft is aligned in an axial direction of the gas turbine engine. A shroud assembly is coupled to the gas turbine engine. The shroud assembly includes a plurality of shroud segments circumferentially coupled about the rotor assembly such that a shroud spacing gap is formed in the axial direction between adjacent shroud segments. A cooling fluid source is coupled to each shroud segment such that cooling fluid is channeled through each shroud segment into a corresponding shroud spacing gap to facilitate positive purge flow through the shroud spacing gap.

Abstract: A fan case and a fan unit realize a fan motor attaching structure in which a fan motor is fixed without a tightening part while the number of functional parts is decreased. The fan case is formed in a box shape having an opening formed by a bottom face, side faces, a front face, and a rear face, and the opening is substantially similar to an outer shape of at least the two fan motors. The front face includes a handle, and the rear face has an opening to expose a connection surface of a connector electrically connected to the fan motor. The side face includes a first latch and a second latch, which are provided so as to be projected toward the opposite side face. A ventilating hole and a bent portion are provided in the bottom face.

Abstract: A turbo machine having a rotor and a stator is at least partially provided on a flow-guiding part with a catalytic coating. The catalytic coating (7, 7?) comprises at least one oxide of a transition metal or an oxide of a mixture of transition metals, wherein the transition metals are elements from groups I B, in particular Cu, Ag, Ag, II B, in particular Zn, Cd, Hg, III B, in particular Sc, Y, IV B, in particular Ti, Zr, Hf, V B, in particular V, Nb, Ta, VI B, in particular Cr, Mo, W, VII B, in particular Mn, Tc, Re and/or VIII B, in particular Fe, Ru, Os, Co, Rh, Ir, Ni, Pd, Pt.

Abstract: An aerofoil made from a sheet metal blank which is bent in the shape of an aerofoil such that it has a leading edge, a trailing edge, a pressure side and a suction side, and the blank is joined at the trailing edge. The regions of the sheet metal blank that form the leading edge, trailing edge and pressure side of the aerofoil comprise a plurality of perforations. The suction side region of the sheet metal blank is imperforate.

Abstract: A duct fan comprises a housing (4) having substantially the shape of a rectangular parallelepiped and inside thereof an impeller (5) and a motor for rotation thereof. The fan has also a member for connecting an inlet side of the housing to an upstream duct part for sucking air in therefrom and a member for connecting an outlet side of the housing to a downstream duct part for exhausting air thereto. The impeller is a radial impeller having the axis of rotation substantially perpendicular to the direction of the main transport of air from the inlet to the outlet. The outlet connecting member is designed to define an airflow path tapering substantially conically in the outlet towards the end of that member adapted to adjoin to a said downstream duct part.

Abstract: A serial fan includes a frame, a plurality of rotor vanes, at least one motor for driving the rotor vanes and a support connected to the frame through a plurality of connecting parts for receiving the at least one motor. The plurality of rotor vanes are arranged in series in the frame along an axial direction and the plurality of connecting parts are disposed therebetween to minimize space occupied by the serial fan in the axial direction, and effectively increase the blast pressure.