Abstract: A turbocharger includes a compressor assembly having a compressor housing defining a ported shroud and a switchable trim compressor. The switchable trim compressor is moveable from an open trim position to a closed trim position, with the closed trim position minimizing a diameter of the air inlet opening and blocking air flow through the ported shroud. The positioning of the switchable trim compressor in the open position increases the diameter of the air inlet opening and allows a recirculation air flow through the ported shroud from an interior of the compressor assembly to a position upstream of the switchable trim compressor at a position near the air inlet opening.

Abstract: A compressor assembly includes a compressor housing and a positive crankcase ventilation (PCV) tube. The compressor housing has an inlet port configured to receive intake air at ambient pressure, an outlet port configured to discharge pressurized air, and a hollow cylindrical section having an inner radial surface and an outer radial surface. The inner radial surface of the hollow cylindrical section defines the inlet port of the compressor housing. The PCV tube is configured to allow airflow between a crankcase of an engine and the inlet port of the compressor housing. The PCV tube extends through the hollow cylindrical section of the compressor housing and beyond the inner radial surface of the hollow cylindrical section.

Abstract: A conduit connection assembly includes a first conduit component having a first mating structure and a second conduit component having a second mating structure adapted to be mated with the first mating structure. A sealing arrangement is provided for sealing between the mating structures. The sealing arrangement includes at least two spaced sealing members defining an intermediate space and the assembly includes a pressure relief opening arranged in communication with the intermediate space between the two spaced sealing members.

Abstract: A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud.

Abstract: A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

Abstract: A gas turbine engine includes an engine core; a fan located upstream of engine core and having a fan diameter; a nacelle surrounding engine core and defining a bypass duct between engine core and nacelle; and a fan OGV extending radially across bypass duct, fan OGV having a radially inner and outer edge, wherein the radially inner edge's axial midpoint is the fan OGV root centrepoint. The engine core includes a compressor system encompassing a first, lower pressure, compressor, and second, higher pressure, compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of outer core casing at an axial position of first flange connection, the first flange connection having a first flange radius, wherein the first flange connection is downstream of an axial position.

Abstract: A turbocharger, with a turbine for expanding a first medium and a compressor for compressing a second medium. The turbine has a turbine housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft. The turbine and compressor housings are connected to a bearing housing in which the shaft is mounted. The turbine housing has a turbine inflow housing and an insert piece for a nozzle ring with guide blades, which is connected on a first cover ring with a flange of the bearing housing. On the flange of the bearing housing multiple protrusions extending radially to the outside distributed over the circumference and first fasteners penetrate the protrusions of the flange of the bearing housing and are in engagement with the first cover ring of the nozzle ring.

Abstract: A turbocharger includes a turbine comprising a scroll passage including at least first and second portions, a gas outlet extending axially from the scroll passage, a turbine wheel including one or more blades disposed in the gas outlet, and structure for establishing a bypass flow between the first and second portions of the scroll passage or for altering gas flow through the turbine. A method for adjusting exhaust gas temperature is also provided.

Abstract: A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

Abstract: A variable flow-restricting turbine assembly for a turbocharger includes a housing, a turbine mounted for rotation in the housing, and a variable flow-restrictor. The variable flow-restrictor includes a first series of angularly-distributed flow-restrictor portions distributed around the turbine wheel and located in an exhaust flow path to the wheel, and a second series of angularly-distributed flow-restrictor portions distributed around the first series and located in the exhaust path. At least one of the first and second series is rotatable in the housing to vary the relative angular positions of the first and second series. The restrictor portions are arranged such that the first portions align with the second portions at each of a plurality of relative angular positions to open flow channels between the portions and such that they misalign between those positions to close the flow channels.

Abstract: A wave disc engine apparatus is provided. A further aspect employs a constricted nozzle in a wave rotor channel. A further aspect provides a sharp bend between an inlet and an outlet in a fluid pathway of a wave rotor, with the bend being spaced away from a peripheral edge of the wave rotor. A radial wave rotor for generating electricity in an automotive vehicle is disclosed in yet another aspect.

Abstract: In a turbine for an exhaust gas turbocharger of an internal combustion engine having a housing part which has a receiving chamber and which comprises a spiral duct through which exhaust gas of the internal combustion engine can flow, the spiral duct having an outlet cross-section via which exhaust gas is directed onto a turbine wheel disposed in the receiving chamber whereby the turbine wheel can be rotated, at least one flow control member is provided which can be moved in the circumferential direction of the receiving chamber and by means of which the flow cross-section can be adjusted, wherein a warp angle of the outer contour region of the wall over which the flow cross-section can be adjusted is smaller than a wrap angle over which the outer contour region thereof extends.

Abstract: A turbine wheel mounted within a housing rotating about a turbine axis; a gas flow control passage upstream of the turbine wheel between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member comprising second and third surfaces opposing the first surface. The movable wall member moves in an axial direction to vary the size of the gas flow control passage. A first gas region of the turbine, being upstream of the gas flow control passage, includes a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage containing the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel. The first gas region comprises the first and second surfaces, and the second gas region or third gas region comprises the third surface.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) grooves extending substantially transverse to a general flow direction of the flow through the nozzle, and there are clearances between the ends of the vanes and the adjacent faces. Leakage flow through the clearance between the end of each vane and the adjacent face having the grooves must proceed across the grooves, and thus a labyrinthine flow passage is presented to the leakage flow. The labyrinthine passage has a greater resistance to flow than would be the case without the grooves. Accordingly, leakage flow is reduced, which is beneficial to turbine efficiency.

Abstract: A variable-nozzle assembly for a turbocharger includes a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. A unison ring engages vane arms that are affixed to axles of the vanes, such that rotation of the unison ring causes the vanes to pivot between a closed position and an open position. The vanes have proximal ends that are adjacent a face of the nozzle ring. A vane sealing member is supported on the nozzle ring and has a portion disposed between the proximal ends of the vanes and the face of the nozzle ring. The unison ring includes cams that engage cam followers. Rotational movement of the unison ring causes the cam followers to be moved axially and thereby urge the vane sealing member against the proximal ends of the vanes.

Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: A compressor includes plural first vanes provided on a shroud side of a diffuser path, and plural second vanes provided on positions of a hub side opposed to the first vanes. The compressor also includes a slide vane mechanism that projects the second vanes into and draws in the second vanes from the diffuser path via the slits of the hub side wall part plate according to a load of the compressor. When the slide vane mechanism projects the second vanes into the diffuser path, end faces of the first vanes and end faces of the second vanes are opposed to each other at the vicinity of the center of the diffuser path.

Abstract: A turbocharger (15) with variable turbine geometry having a blade bearing ring arrangement (1) which has a blade bearing ring (2) and a disk (3) which can be fixed to the blade bearing ring (2) to form a flow duct (4); having a spacer device (5) which is arranged between the blade bearing ring (2) and the disk (3) to set a defined width (B) of the flow duct (4), wherein the spacer device (5) is designed as a guide ring (6) which has spacer profiles (7) whose height (H) corresponds to the width (B) of the flow duct (4).

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 mechanism modulates a fluid flow in a diffuser flow path of a compressor diffuser, including: a shroud disposed on the diffuser flow path and having a cam and a driving wheel fixed base; a diffuser vane having a diffuser guide vane disposed in the diffuser flow path and a diffuser vane shaft fixedly disposed on the diffuser vane that penetrates from the diffuser flow path through the shroud; a driving ring sleeved on the cam and having a moving bar; a sliding block having one end connected with one end the diffuser vane shaft that penetrates through the shroud, and the other end sleeved on a sliding groove formed on the moving bar; a driving wheel disposed in the driving wheel fixed base and having a driving shaft connected to an actuator outside of the compressor; and a driving cable connected to the driving wheel and the driving ring.

Abstract: The flow path of exhaust gas to the turbine wheel (70) of a turbocharger is influenced by relative motion between two rings of vanes, at least one of which being provided on a vane ring. The outer ring of vanes contains a plurality of vanes (92, 122), the inner ring of vanes contains a plurality of vanes (93, 121), and the inner and outer vanes in registry forming a single generic vane shape. The aerodynamic effect of relative displacement of the outer ring of vanes to the inner ring of vanes produces a modulate-able control of exhaust flow to the turbine wheel.

Abstract: Device for harvesting the energy of a fluid stream comprising a turbine with a rotation axis at right-angle to the fluid stream, the turbine comprising a plurality of blades that during its rotation sweeps an annular area around the rotation axis which has an inner and outer perimeter with a first and second radial distance to the rotation axis, and first and second fluid guide located opposite each other, with the plurality of blades arranged for rotation there between and arranged for guiding the fluid stream towards the at least one blade, wherein the first and second fluid guide are formed each with a guide foil section having a suction side, a pressure side and a guide foil incidence angle, wherein each fluid guide is arranged such that the suction sides of the guide foil sections are facing each other, wherein an open central area around the rotation axis is provided.

Abstract: A variable nozzle for a turbocharger (10) has a nozzle ring (138) supporting an array of vanes (134) that are variable in setting angle. The nozzle ring (138) is rotationally oriented and fixed in position by a plurality of circumferentially spaced, radially outwardly extending locating members (170) that engage corresponding locating grooves (159) in a flange member (157) of the turbocharger.

Abstract: A turbocharged engine includes an internal combustion engine and a variable geometry turbocharger. The turbocharger is adjustable to operate efficiently under various engine operating and environmental conditions. The turbocharger includes a turbine and compressor, with the compressor including a compressor housing, an impeller rotatably mounted in the housing, and an adjustable diffuser vane assembly. The diffuser vane assembly includes a plurality of pivotal diffuser vanes spaced about the impeller and a vane rotation drive that interconnects the vanes and permits simultaneous adjustment of the diffuser vanes to improve the efficiency and operating range of the turbocharger. The diffuser vane assembly also includes a vane locking drive operable to engage the pivotal vanes and prevent vane movement during turbocharger operation.

Abstract: A turbocharger with an exhaust gas-driven turbine includes a variable nozzle formed by a stator supporting fixed vanes and defining bypass openings, and a rotor supporting movable vanes and defining bypass channels. Each fixed vane overlaps with a movable vane by a varying extent dependent on rotational position of the rotor. In a fully open position of the rotor, the movable vanes have a maximum extent of overlap with the fixed vanes, and the bypass channels align with the bypass openings so that some of the exhaust gas flows through the aligned bypass openings and channels, bypassing the turbine wheel.

Abstract: A vane ring assembly which includes a lower vane ring (23), an upper vane ring (31), one or more guide vanes (80) positioned at least partially between the vane rings, and a plurality of spacers (49, 50 or 59) positioned between the lower and upper vane rings (23, 31) for maintaining a distance between the lower and upper vane rings, the vane ring assembly being retained in a turbine housing (102) by a retaining ring (400) which is located in a groove (510) in the turbine housing.

Abstract: A turbocharger comprising a turbine housing where at least one supply channel supplies an exhaust gas. The exhaust gas is fed through a guide grid that forms passages of variable cross-section between the supply channel and a turbine rotor. This guide grid comprises a plurality of vanes of predetermined width in a vane space of about the same width. A vane support ring defines one axial end of the annular vane space and an opposite ring is spaced from the vane support ring by about the width of the vanes to define the other axial end of the annular vane space. To maintain this width, at least two spacers are integrally formed on at least one the rings.

Abstract: A direction-switchable pneumatic cylinder includes: a cylinder body with two intakes, several exhaustion ports and a rotary shaft; and a predetermined number of movable wheels and fixed wheels arranged in the cylinder body and interlaced with each other. Each of the movable wheels and fixed wheels is formed with several vents concentrically arranged into an inner circle and an outer circle. The rotary shaft is fitted through the movable wheels and fixed wheels. The fixed wheels are not rotatable, while the movable wheels are synchronously rotatably with the rotary shaft. The outer circles of vents of the fixed wheels and the movable wheels are aligned with one intake, while the inner circles of vents of the fixed wheels and the movable wheels are aligned with the other intake. When high-pressure gas is guided into the pneumatic cylinder from one intake, the airflow will flow through the outer circles of vents to drive the movable wheels and the rotary shaft in one direction.

Abstract: A variable nozzle device for a turbocharger comprises an annular arrangement of vanes disposed in a nozzle formed between an inner wall and an outer wall, the outer wall being constituted by an axially displaceable member, wherein the axially displaceable member is displaceable by an action exerted from the side of the inner wall.

Abstract: A method for distributing effects of a circumferential hot streak condition in a turbine includes communicating a control signal to a rotator moving a stator ring with the rotator in response to the control signal.

Abstract: A turbocharger comprising a turbine housing where at least one supply channel supplies an exhaust gas. The exhaust gas is fed through a guide grid that forms passages of variable cross-section between the supply channel and a turbine rotor. This guide grid comprises a plurality of vanes of predetermined width in a vane space of about the same width. A vane support ring defines one axial end of the annular vane space and an opposite ring is spaced from the vane support ring by about the width of the vanes to define the other axial end of the annular vane space. To maintain this width, at least two spacers are integrally formed on at least one the rings.

Abstract: One of the swing shafts 32 of the nozzle vanes 31 is selected so as to operate as swing drive shaft 33 that projects to the outside. As the swing drive shaft 33 is driven to revolve, all the nozzle vanes 31 are driven to turn by a same angle by way of the driving lever 21 and the coupling ring 18 linked to it. Therefore, it is only the swing drive shaft 33 that projects to the outside, the projecting part can be sealed in a simple and reliable manner to improve the sealing effect and the durability of the variable geometry turbocharger. Additionally, since the rotary motion of the swing drive shaft 33 is directly used to driven the nozzle vanes 31 to swing, the mechanism for transmitting the driving force is simplified.

Abstract: In an exhaust turbocharger for an internal combustion engine including a turbine and a compressor, which is driven by the turbine, wherein the compressor comprises a compressor impeller in a flow duct, a transfer component with flow passages extends radially around the compressor impeller in the axial direction of the impeller and provides for communication with the flow duct. To provide for variable adjustment of the effective flow cross-section of the transfer duct, a transfer ring is provided which comprises two component rings, which are rotatable relative to one another.

Abstract: An axial turbine for aeronautical applications has a casing housing a stator, which is provided with an array of airfoil profiles, which are positioned angularly equidistant from one other about the axis of the turbine, define associated spaces between one another for the passage of a flow of gas and are hinged to an annular structure, each one about an associated hinge axis incident to the axis of the turbine; in service, the airfoil profiles are simultaneously actuated to rotate by an identical angle of adjustment by means of a ring actuated by actuators outside the casing and connected to each airfoil profile via an associated lever.

Abstract: A vane for a stator of a variable-geometry turbine, in particular for aeronautical engines, has an airfoil profile and a pair of hinge portions, which are carried by the airfoil profile and enable the airfoil profile to be coupled to a support structure of the stator so as to be rotatable about an axis of adjustment; the vane also has internal channels that allow a flow of air to pass through in order to cool the hinge portions.

Abstract: A vaned diffuser for a centrifugal compressor has provision for selectively adjusting the pitch of the vanes in order to accommodate variable load conditions. Each of the vanes is rotatable about a pivot pin near its leading edge and is engaged with an actuation member near its trailing edge. The actuation members are attached to a common ring which can be selectively rotated to move to the vanes in unison. The ring is supported by rollers at its outer periphery and is positioned at the outer periphery of a diffuser wall such that there is no forward facing step projecting into the flow stream.

Abstract: A variable geometry system for a turbocharger includes a sliding piston disposed within a turbine housing between a primary exhaust gas volute and turbine blades. The sliding piston is axially displaceable within the turbine housing to increase or decrease the volumetric flowrate of exhaust gas to the turbine. The sliding piston is positioned by an actuator having reciprocating movement translated through a rotating sleeve with a first pin engaging a helical slot for axial motion of the piston and a second pin engaging an alignment slot for maintaining axial alignment of the piston.

Abstract: A stator assembly of an axial flow rotary machine has a compressor bleed system. The compressor bleed system includes an axially translating valve ring. The valve ring is movable between an open and closed position and includes guide roller and guide track having guide walls which urge the valve ring axially against resilient seal members. The track is contoured to provide a mechanical advantage when the valve ring is moved to the closed position. A liner is adapted to engage the stator assembly to form the track.

Abstract: A ring support system for use in a variable pipe diffuser. The ring support mechanism includes at least three axle shafts and at least three roller bearings rotatably mounted to the axle shafts, an inner ring having a groove disposed in the outside diameter, and an outer ring having a corresponding groove disposed in the inside diameter. The at least three axle shafts are circumferentially mounted in the outer ring such that the rollers are positioned partially within the groove of the outer cylinder such that the roller bearings define a diameter nearly equal to the outside diameter of the inner ring. The inner ring is positioned within the at least three roller bearings such that the at least three roller bearings are in axial sliding contact with the groove of the inner ring and in rolling contact with the groove of the inner ring. The ring support system provides rotational and axial support of the inner ring.

Abstract: A backlash adjustment mechanism for use in a variable pipe diffuser having inner and outer rings and a casing. The backlash adjustment mechanism includes a drive shaft and a pinion gear attached thereto, a rack gear fixedly attached to the inner ring. The backlash adjustment mechanism is comprised of a housing having a cylindrical body positioned concentrically about a first centerline and having a bore disposed axially though the body positioned about a second centerline. The drive shaft is rotatably disposed concentric with the second centerline within the bore. The inner ring is positioned such that it meshes with the pinion gear. The housing is disposed within the casing and rotatably operable to effect an adjustment of the backlash between the pinion gear and the rack gear.

Abstract: An axial restraint system for use in a variable pipe diffuser having an inner ring rotatably positioned within an outer ring. The axial restraint system includes a housing fixedly mounted to the outer ring and having a mounting hole disposed therein in perpendicular arrangement to the inner ring. A shaft having a first end and a second end and having a bearing pad mounted to the first end. The second end of the shaft is threadably engaged within the mounting hole and rotatably operable to effect an adjustment of the position of the bearing pad. The shaft is positioned such that the bearing pad contacts the inner ring and thereby limits the axial movement of the inner ring relative to the outer ring.

Abstract: A drive positioning mechanism for use in a variable pipe diffuser for a centrifugal compressor. A rotational drives means is fixedly attached to the housing of a centrifugal compressor with a pinion gear mounted thereto. A rack gear is mounted to the inner ring and adapted to engage in meshing arrangement with the pinion gear. The rotational drive means is operable to position the inner ring between a fully open position and a partially closed position. A travel limiter is provided to positively limited the travel of the inner ring at the filly open and the partially closed positions.

Abstract: An air handling system comprising a track having a lower extent for supporting an object to be conveyed by the flow of pressurized air and an upper extent having a plenum chamber for receiving pressurized air and for directing it in contact with the object to be conveyed for effecting movement of the object. The track also has air-directing louvers between the upper and lower extents and an aperture in the upper extent. An impeller is mounted adjacent to the aperture of the upper extent of the track. A tapering input duct with an inlet end and a circular outlet end are mounted adjacent to the impeller with a circular screen in the outlet of the duct adjacent to the impeller. The screen has a centrally disposed hole. A baffle is mounted adjacent to the screen. The baffle includes a plurality of pie-shaped segments each with an arcuate outer edge overlying the periphery of the screen and with V-shaped interior edges with a hole. The segments are similarly configured.

Abstract: In an exhaust gas turbocharger for an internal combustion engine comprising a compressor and an exhaust gas turbine mounted on a common shaft, the exhaust gas turbine includes a rotor with radial and semi-axial flow inlet areas and a single-flow duct surrounding the rotor and having port regions in the form of annular nozzle structures with guide vanes disposed adjacent each flow inlet area which are divided from one another by a ring of streamlined shape which is mounted to the guide vanes of one of the adjacent nozzle structures, said guide vanes having at least portions which are movable for adjusting the flow cross-section of the respective annular nozzle structures for controlling the flow through the radial and semi-axial flow inlet areas.

Abstract: An exhaust-gas turbocharger for an internal-combustion engine, the exhaust-gas turbine of which comprises a rotor with an at leash partially diagonal throughflow direction and a spiral guide channel surrounding this and having a mouth region in the form of an angular nozzle, and a variable guide blade cascade with guide blades being arranged in the mouth region. In order to design guide blade cascades with a simpler construction than that of known versions, at the same time with an increase in their operational reliability, according to the invention the guide blades are divided in such a way that they form a divided guide blade cascade with a stationary guide-blade cascade part and with a guide-blade cascade part assigned to this and rotatable concentrically relative to the axis of rotation of the rotor.

Abstract: The invention relates to secondary power system apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The invention integrated power unit (IPU) performs the function of both an APU and an EPU, while avoiding the use of hazardous monofuels. The IPU includes a turbine engine operable on pressurized ambient air, or on pressurized stored air, along with jet engine fuel. The structure of a combustion chamber for the engine which is able to use pressurized air from two separate sources; of a control able to selectively operate the engine as an EPU, as and APU, and to effect operating transition from EPU to APU; and of a complete secondary power system with the IPU are all disclosed.

Abstract: An improved variable geometry diffuser assembly is provided. This assembly includes a variety of features that reduce the leakage and improve the precision within the assembly. These features include: sealing disks mounted to the vane; cantilevered vanes mounted for rotation to coolside diffuser wall only, thereby reducing the effects of thermal growth on the assembly; and self lubricating, non-metallic bushings for supporting the various components in the assembly thereby reducing friction and any need for lubrication. Each vane is coupled to a single unison ring through an arm member also employing non-metallic bushings.

Abstract: In order to pump up fish in a gentle manner from a cod end being towed by a vessel by means of a fish pump located at the end of the cod end, a throttle valve for adjusting the admission of the catch to the pump is positioned in the inlet suction channel of the pump. A direct sea water inlet to the pump inlet is provided in the form of openings with throttles for adjustment of the direct sea water inflow. Thus, the ratio between the fish from the cod end and sea water supplied directly to the pump is controlled.

Abstract: Nozzle shafts and a nozzle drive mechanism are disposed on the side of a bearing casing and a compressor whose temperatures are lower than that of a turbine, and elements slidable in the radial direction of the turbine wheel are eliminated from the nozzle drive mechanism so that any adverse effects due to oxidization at high temperatures and slide wear can be eliminated. Thus durability and reliability of the device can be improved.

Abstract: An improved driving linkage device for adjusting a variable nozzle mechanism in a supercharger turbine or a variable diffuser mechanism in a compressor. The driving linkage device is provided with a driving ring for driving a variable nozzle mechanism in a supercharger turbine or a variable diffuser mechanism in a compressor, one or more sets of adjusting links, each set consisting of three levers connected in a U-shape and having two opposed ones coupled to the driving ring and a fulcrum for supporting the lever not coupled to the driving ring. One end of one adjusting link is coupled to an actuator to achieve the adjustment of a variable nozzle mechanism in a supercharger or of a variable diffuser mechanism in a compressor.