Abstract: A heat-dissipating assembly for being used in a system frame is provided. The heat-dissipating assembly includes a heat-dissipating device having a plurality of holes thereon, and a securing device engaged with the system frame and having a plurality of engaging elements corresponding to the plurality of holes of the heat-dissipating device for separately connecting the heat-dissipating device with the securing device, and a plurality of supporting flanges for assisting in securing the heat-dissipating device to the securing device.

Abstract: A heat shield for a gas turbine engine hub which facilitates reducing thermal stress in an exhaust frame of a gas turbine engine. The exhaust frame includes the hub mounted within the engine with a plurality of supports. The supports extend radially outward from the hub through a primary flow cavity and facilitate flow to a secondary flow cavity. The heat shield defines the secondary flow cavity such that the secondary flow cavity is radially inward and axially adjacent the hub. The heat shield includes a plurality of thermal stress relieving corrugations.

Abstract: Gas turbine rotor blade tip loss is reduced and loss caused by leakage of working fluid through gap between members constituting an annular flow passage is reduced. Turbine (AT) of a gas turbine (GT) constituting a combined cycle plant (CC) is supported to a turbine casing (4) to be expandable or contractible in turbine shaft (32) radial direction. First blade ring (41) corresponds to first stage turbine stator blades (TS1) and rotor blades (TR1) and comprises a first heating medium flow passage (41P) for steam circulation therein. Second blade ring (42) corresponds to second stage turbine stator blades (TS2) and rotor blades (TR2) and comprises a second heating medium flow passage (42P) for steam circulation therein. Further provided is a communication member (45) for connecting the first blade ring (41) and second blade ring (42) to each other and for communicating the first heating medium flow passage (41P) and second heating medium flow passage (42P) with each other.

Abstract: This invention comprises high temperature fan apparatus for use in displacing high-temperature gases and atmospheres, such as the atmosphere within a high-temperature furnace. The fan apparatus is configured to limit heat transfer through the fan apparatus without the need for separate fan-cooling apparatus thereby preventing bearing damage and generally increasing the fan's operational life. The preferred fan includes a frame supporting the fan. One or more bearings rotatably support a fan shaft. A fan element is supported by the fan shaft, The fan element may be within the furnace interior. Heat transfer through the fan and fan shaft is limited by at least one bore positioned in at least a portion of the fan shaft. Heat transfer through the fan is further limited by thermal barrier material secured with respect to the frame. Oversized bearing structure may additionally be provided to further limit heat transfer from the fan shaft to the bearings.

Abstract: The invention provides a nuclear power station primary pump of the type comprising a drive shaft for rotating a wheel, a heat exchanger, a thermal barrier cover comprising a peripheral skirt provided at its base with a circular end wall, and a diffuser comprising a peripheral skirt provided at its base with a rim. The circular end wall co-operates with the base of the heat exchanger to define a bottom chamber for cold water and includes a central bore provided with a succession of circumferential and superposed rings forming a lip seal of the labyrinth type, and a space is formed between the thermal barrier cover and the diffuser to maintain stagnant cooling fluid.

Abstract: A method of operating a gas turbine having inner and outer shells, with the inner shell being radially movable relative to rotor bucket tip passage in the inner shell for flowing a thermal medium. A pair of passage portions are formed in each of the aft and forward inner shell sections with axially communicating passageways between the passage portions. A thermal medium, preferably from an off-turbine site, is provided for flow through the second-stage aft inner shell section, along axial passageways along the mid-line of the inner shell to a first passage portion of the forward inner shell section. Cross-over paths flow the thermal medium from the first passage portions to second circumferentially extending passage portions of the forward inner shell section, in turn, in communication with axial passageways extending from the forward section to the aft section. A second pair of passage portions flow the thermal medium to an outlet in the aft section.

Abstract: A rotor (1) of a turbomachine comprises a basic rotor element (2) and a multiplicity of rotor blades (3, 3′, 3″, 3′″). The rotor blades (3, 3′, 3″, 3′″) are arranged in a distributed manner in at least one row on the circumference of the basic rotor element (2). An area for a row of guide vanes is furthermore provided in front of and/or behind the row of rotor blades. A heat shield element (4) or a plurality of heat shield elements (4′, 4′, 4′″) lined up on the circumference of the rotor (1) is arranged in such a way between the basis rotor element (2) and the rotor blades (3, 3′, 3″, 3′″) of the row of rotor blades that the basic rotor element (2) is completely covered in the areas of the row of rotor blades and the row of guide vanes.

Abstract: In an exhaust gas turbocharger for an internal combustion engine including an exhaust gas turbine and a compressor connected to the turbine so as to be operated thereby, the turbine includes a housing consisting of an inner and an outer shell formed from steel sheets and being arranged in spaced relationship so as to form therebetween an intermediate space.

Abstract: To control the temperature mismatch between the inner and outer bands and covers forming plenums with the inner and outer bands on sides thereof remote from the hot gas path, passages extend from the leading edge of the covers in communication with the hot gases of combustion to the trailing edge of the covers in communication with the hot gas flowpath. A mixing chamber is provided in each passage in communication with compressor discharge air for mixing the hot gases of combustion and compressor discharge air for flow through the passage, thereby heating the cover and minimizing the temperature differential between the inner and outer bands and their respective covers. The passages are particularly useful adjacent the welded or brazed joints between the covers and inner band portions.

Abstract: A stator suitable for high-pressure compressors in gas turbine engines includes two points of ventilation at different temperatures. It is recommended that the upstream section of the stator be constructed with a casing and a shroud, both of which are unbroken around a circumference and made of a material with a low degree of thermal expansion. Downstream the shroud is, however, constructed using angular sectors in a material with a higher degree of thermal expansion.

Abstract: A heat sink-equipped cooling apparatus capable of increasing a size of an air discharge port as compared with a prior art. A fan unit is mounted on a heat sink. The heat sink includes a base formed into a contour having first and second sides defined so that an angle therebetween is substantially 90 degrees. A side wall of the base and a casing of the fan unit cooperate with each other to provide an air discharge port at a position corresponding to sides of the base opposite to the first and second sides while being combined with each other. The air discharge port is constructed so as to permit air sucked through an opening to be discharged therethrough.

Abstract: An article comprising an airfoil surface is provided with a thermal insulating outer layer on at least one region, but not all, of the airfoil surface. The region is selected from the airfoil surface which has been observed to experience more strenuous environmental operating conditions during service operation than the airfoil surface outside of the region. In one form, the thermal insulating outer layer is applied to at least one region of each of a plurality of airfoil surfaces. Each airfoil surface is disposed about an axis of rotation with the region of each airfoil surface facing generally outwardly from the axis of rotation and from each other. The airfoil surfaces are rotated about the axis of rotation while a thermal insulating material contacts at least the regions.

Abstract: A casing for a gas turbine engine having a longitudinal axis extending therethrough, including a first casing portion having a substantially arcuate section and a split-line flange extending from each end thereof and a second casing portion having a substantially arcuate section and a split-line flange extending from each end thereof. The first and second casing portions are mated at each end by connecting together respective pairs of the split-line flanges. A channel is formed in at least one mating surface of the split-line flanges to provide an axial passage therethrough so that air flow provided to the axial passage reduces a temperature gradient between the arcuate sections and the flanges of the first and second casing portions.

Abstract: A fan motor with an improved inhaling structure so as to enhance ventilation efficiency and performance, as well as cooling performance. An outer housing member 7 has a respective face opposite to a drive unit 11. An intake hole 13 of an arbitrary diameter is provided in a first face of the outer housing member 7, while another intake hole 15 of an arbitrary diameter is provided in a second face thereof. Thus, a substantial amount of air is taken in from the two faces of the outer housing member 7, thereby drastically improving the ventilation efficiency. Even though an inhaling passage is not ensured substantially on a top face of the outer housing member 7, the air is able to be inhaled even through a slight clearance due to the other intake hole 15, thus improving the cooling performance. The air taken in from the intake holes 13 and 15 of the outer housing member 7 is smoothly discharged toward the exhaust direction of a fan 5, without striking on walls of a casing 1 and a cover 12.

Abstract: A symmetrical component of a turbine unit, whose wall is exposed to a hot medium on one side and is subject to nonuniform thermal stress over the circumference, is cooled by a flow of cooling air being guided along the other side of the component. A ring (5) is provided with slots (7) or other openings for the passage of the cooling air. The ring (5) protrudes into the flow of the cooling air. The overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to the higher stress is larger than the overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to a lower stress.

Abstract: The invention provides a turbomachine including a device for supplying pressurized gas, the gas being bled from the compressor of the turbomachine via a bleed orifice and cooled in a cooling cavity disposed within the compressor rotor upstream of the bleed orifice. This arrangement has the effect of cooling the bled gas by heat transfer through the outer wall of the compressor rotor to the gas stream which is being compressed by the compressor upstream of the bleed orifice, and has the result of reducing the drop in the performance of the compressor as a result of the gas being bled off.

Abstract: A blower for flowing cooling air toward a corrugated fin is disposed to face the corrugated fin. The blower is covered with a blower case. Leg portions are integrally formed with and protrude from the blower case to face the corrugated fin at both sides in a corrugated direction of the corrugated fin. The blower case is fixed to a radiation plate by elastic deformation of the leg portions. The leg portions cover the both sides in the corrugated direction of the corrugated fin, so that the corrugated fin is protected from external force.

Abstract: A blower is provided for effectively cooling heat generating parts in a casing of a personal computer and so on, with a heat sink apparatus using the blower and an electronic equipment using the heat sink apparatus. The blower comprises a fan and an outer frame. The outer frame of the fan is made of a highly thermally conductive material such as aluminum. A radiation board is fixed to or formed integrally with a lower surface of the outer frame. Heat generated from a heat generating device is conveyed through the radiation board to the outer frame. The blower is provided with radiation fins so that the heat conveyed to the outer frame is transferred to the radiation fins as well.

Abstract: A turbine casing includes a multilayer casing wall in which an intermediate layer in the form of a non-metallic bulk material, preferably sand, is provided between an inner layer and an outer layer, to cope with high steam states. A method of manufacturing a multilayer turbine casing includes inserting a core representing an intermediate layer into a casting mold while forming a cavity for the inner layer and/or the outer layer. The cavity is then filled with a casting material, with the core expediently remaining as the intermediate layer in the casing wall. Alternatively, first of all a U-shaped profile part is made and an intermediate space formed by the outer layer and the inner layer is filled with the bulk material.

Abstract: An apparatus and method for cooling an impeller for an axi-centrifugal compressor of a gas turbine engine. A curvic coupling joint is used between the aft end of the impeller and the turbine shaft. A generally annular disk-shaped shield structure is attached to the aft face of the impeller and extends from the impeller rim to the turbine shaft just aft of the curvic coupling. The shield structure is offset from the aft face of the impeller thereby forming a cavity therebetween. The shield structure has a plurality of circumferentially space apertures through which cooling air passes to first circulate through the cavity by means of radial vanes to cool the impeller, then exit through the curvic coupling joint. The cooling air is then directed afterward along the turbine shaft to be used to cool high-pressure turbine blades.

Abstract: A steam turbine includes a turbine casing, in which a turbine rotor is accommodated so as to extend along a direction of flow of steam, and a plurality of turbine pressure sections are mounted to the turbine rotor, which includes, in combination, at least two or more of a turbine high pressure portion, a turbine intermediate pressure portion and a turbine low pressure portion. The turbine casing is divided into two casing sections, each of the divided turbine casing sections being further divided into a turbine casing upper half and a turbine casing lower half, and the turbine casing lower halves of the divided turbine casing sections being connected to each other by a fastening member such as stud bolt inserted from a side of the turbine low pressure portion.

Abstract: A method of cooling the flow in radial gaps formed between rotors and stators turbo machines is provided. The method includes the step of using water as a cooling fluid for the stator part adjacent to the radial gap. To this end, either at least one recess is formed in the interior of the stator part adjacent to the radial gap or at least one cavity is arranged at the stator part. The recess or the cavity is connected to both a feed line and a discharge line for the cooling fluid.

Abstract: A heat radiation device for a thin electronic apparatus includes a rectangular plate-shaped base, a rectangular intermediate plate stacked on the base, a rectangular box-shaped cover stacked on the intermediate plate, and a fan. A depression is formed at a center portion of the base. A plurality of parallel fins are provided to form a discharge port for cooling air. The depression and the discharge port are connected via an arcuate communication portion. A circular opening is formed in the intermediate plate at a position corresponding to that of the depression, and the fan is attached to the circular opening. The intermediate plate and the base are connected together such that heat can be conduced therebetween. When the end surface of a side plate provided at each longer side of the cover is caused to abut the intermediate plate and/or the base, an intake port for cooling air is formed at a shorter side of the cover.

Abstract: A portable apparatus includes a housing having an inclined board for formed a cut-off opening and having one or more apertures formed in the inclined board and communicating with the cut-off opening of the housing for preventing the aperture of the inclined board from being blocked and for allowing the air to be drawn into the housing with a fan device which is secured to the inclined board. A stand is secured to the housing and is engaged with the flexible sheet members disposed below the housing for positioning and for preventing the flexible sheet members from blocking the apertures.

Abstract: A cooling system for turbomachinery includes a compressor bleed air passageway for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages in communication with a cavity within the inner barrel in which the flanges of the turbine and compressor rotors are secured to one another. The exit ends of the passages have swirl devices for turning the flow from the general axial direction to a tangential direction corresponding to the direction of rotation of the combined rotors. A leakage seal is provided between the rotor and the stationary component to provide a pressure drop across a plenum and cavity to increase the velocity of air flowing into the cavity. Consequently, cooling air is supplied the cavity at a tangential velocity approaching the rotor velocity with reduced windage and lower temperature, thereby improving the performance of the turbomachinery.

Abstract: A turbine casing supports a row of nozzle vanes through which are flowable hot combustion gases. A baffle surrounds the casing to define a cooling duct. A nacelle surrounds the turbine casing to define a bay having an inlet for receiving bay air, and an outlet for discharging the air. The cooling duct includes an inlet which receives the bay air for flow along the turbine casing for selective cooling thereof.

Abstract: A heat sink comprising a conductive plate (1) to be applied onto the surface to be cooled, the thickness of which gradually increases from the edges (4) towards a central portion (5) according to a curvilinear profile (6) having an upwardly turned concavity, so that an air flow hitting the plate is deflected towards its edges with a substantially horizontal outlet direction. The conductive plate (1) has preferably arranged thereon a plurality of cooling fins (7) extending in a substantially radial way from the central portion (5) to the edges (4) of the plate.

Abstract: A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing cooling air from the cavity through the passages through the tip of the trailing edge into the hot gas path. Each passage is partially turbulated and includes ribs in an aft portion thereof to provide enhanced cooling effects adjacent the tip of the trailing edge. The major portions of the passages are smooth bore. By this arrangement, reduced temperature gradients across the trailing edge metal are provided. Additionally, the inlets to each of the passages have a restriction whereby a reduced magnitude of compressor bleed discharge air is utilized for trailing edge cooling purposes.

Abstract: In a turbine rotor, an aft shaft wheel and the final-stage wheel of the rotor are coupled together, including by a rabbeted joint. During shutdown and startup of the turbine, a thermal mismatch between the aft shaft wheel and final-stage wheel is avoided by respectively heating and cooling the aft shaft wheel to maintain the thermal mismatch within acceptable limits, thereby avoiding opening of the rabbeted joint and the potential for unbalancing the rotor and rotor vibration. The thermal medium may be supplied by piping in the aft bearing cavity into the cavity between the forward closure plate and the aft shaft wheel.

Abstract: An apparatus for cooling a gas turbine engine annular rear turbine frame includes a first plenum box having an inlet for receiving cooling air and an annular first manifold tube in fluid communication with a first outlet of and extending in a first circumferential direction away from the plenum box. The first manifold tube is circumscribed radially outward of and around a centerline and has axially spaced apart first arcuate sections circumscribed about and perpendicular to the centerline. Each of the first arcuate sections of the first manifold tube has a corresponding portion of a first plurality of impingement cooling holes disposed through the first manifold tube and aimed generally radially inward. In one embodiment the impingement cooling holes are aimed towards a first circumference on the frame and A cooling air bleed is preferably connected to the plenum box with a selectable on and off control valve therebetween.

Abstract: An airfoil with a reduced heat load for use in either a turbine or a compressor of a gas turbine engine comprises having at least one heat reducing dimple on the body of the airfoil or on the associated endwall of the airfoil. The body of the airfoil is comprised of a leading edge, a trailing edge, a pressure side and a suction side. The length of the heat reducing dimple in the expected direction of hot gas stream flow is at least equal to or greater than the width transverse to such direction. The heat reducing dimple is located on the airfoil or endwall so as to reduce the heat load as the hot gas stream flow passes from the leading edge to the trailing edge.

Abstract: A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and spaced apart to define first and second cavities separated by a septum therebetween. An aft bridge extends along the first cavity and includes a row of outlet holes therein. The septum includes a row of inlet holes. And, turbulators are disposed in rows inside the first cavity, and extend from the first sidewall toward the second sidewall. The turbulators are aligned with the inlet holes for multiple impingement cooling thereof.

Abstract: A device for thermally insulating casing parts of a steam turbine contains a shim element that can be inserted into a bearing region of supporting bearings of the casing parts. The supporting bearings face one another and the shim element has a number of holes formed therein.

Abstract: A cooling system for dissipating heat from a heat source is disclosed. The cooling system comprises a heat sink associated with a divider member. The heat sink includes a heat conductive base portion having a surface adapted to contact the heat source. The base portion has a peripheral wall member extending from the heat conductive base portion wherein the peripheral wall member defines a chamber therewithin and a heat sink device exterior located on the opposite side of the peripheral wall member from the chamber. A plurality of openings extend through the peripheral wall member between the heat sink device exterior and the chamber. An intake airflow path extends from the heat sink device exterior through a first portion of the plurality of openings to the chamber. An exhaust airflow path extends from the chamber through a second portion of the plurality of openings to the heat sink device exterior.

Abstract: An electronic component cooling apparatus capable of permitting a sufficient amount of air to be fed to an electronic component to be cooled. An impeller which includes a plurality of blades for sucking air from one side in an axial direction of a revolving shaft of a motor is fixed on a rotor of the motor. A casing having a cylindrical cavity defined therein in which the motor and impeller are received is constructed of a peripheral wall arranged so as to surround the impeller and a closing wall for closing an end of the cavity on the other side in the axial direction. The peripheral wall is formed at a portion thereof in proximity to an end thereof on the one side with a lateral discharge port through which air suckedly introduced into the cavity is discharged so that a surrounding portion for surrounding a whole circumference of the impeller is left at a portion of the peripheral wall in proximity to an end on the other side.

Abstract: A turbine engine includes a rotatable turbine having a peripheral tip and a backface. A heat shield is positioned adjacent the backface and includes an integral ring extending from a peripheral edge of the heat shield to a position spaced radially outwardly from the peripheral tip of the rotatable turbine to form a tip clearance between the ring and the peripheral tip. The turbine comprises a material having a coefficient of thermal expansion at least approximately four times greater than the coefficient of thermal expansion of the heat shield such that the turbine expands toward the ring as a result of heat within the engine, thereby reducing the tip clearance to minimize air flow along the backface and improve efficiency of the engine.

Abstract: In a turbine rotor, a thermal mismatch between various component parts of the rotor occurs particularly during transient operations such as shutdown and startup. A thermal medium flows past and heats or cools one part of the turbine which may have a deleterious thermal mismatch with another part. By passively controlling the flow of cooling medium past the one part in response to relative movement of thermally responsive parts of the turbine, the flow of thermal medium along the flow path can be regulated to increase or reduce the flow, thereby to regulate the temperature of the one part to maintain the thermal mismatch within predetermined limits.

Abstract: A gas turbine having cooling structure disposed on an outside peripheral side in a radial direction of a movable vane in which the cooling efficiency is further improved and sealing structure disposed on an inner peripheral side to suppress leakage of sealing air and prevent invasion of combustion gas into the turbine disc and enlargement of sealing air clearance is prevented. Outwardly in the radial direction, a gap between ring segment (90) and impingement cooling plate (92) disposed on the outer periphery thereof, is divided in the axial direction by a pressure partition plate (97) extending in a circumferential direction so as to provide plural cavities adjusted to different pressures, thereby forming a cooling structure in the ring segment (90). Inside in the radial direction, a static vane inside diameter side cavity (53) and downstream cavity (31) are formed by a box (57) for sealing the static vane inside diameter side cavity (53).

Abstract: A centrifugal blower assembly for a heat exchanger system of an automotive vehicle is described. The centrifugal blower assembly includes a diffuser section interposed between the centrifugal blower housing and a heat exchanger housing in the heat exchanger system. The diffuser section has a pair of non-linear, curved side walls which allow for expansion of the air flowing therethrough to minimize air flow separation against the side walls of the diffuser.

Abstract: A heat dissipating fan includes a casing, a stator seat, a fan wheel, and a lid. The casing includes a compartment for receiving the fan wheel, and a bottom wall that defines the compartment has an axle tube formed thereon. The casing further includes an air outlet defined in an end edge thereof and communicated with the compartment. The fan wheel includes a number of blades and an axle that is rotatably received in the axle tube. The lid is engaged on top of the casing and includes an air inlet. Each blade includes an upper section extended beyond the air inlet, while a lower section of each blade is below the lid. When the fan wheel rotates, ambient air is driven into the casing via the air inlet of the lid to carry heat in the casing away via the air outlet of the casing. The heat dissipating fan may drive more air by increasing an active area of the blades with reduced noise.

Abstract: A passive clearance control system is provided in the turbine section of a gas turbine engine in which turbine casing nozzle vanes and rotor blades are provided. The rotor blades are arranged on a rotor and preferably fitted with a shroud. The tips of the blades or shroud are surrounded by shroud segments suspended in the turbine casing, and a clearance between the tips and the shroud segments is formed and has a width which is controlled by a heating-cooling channel system. The channel system is supplied with a stream of air from the compressor section of the gas turbine and bypasses the combustion chamber to reach, via a plurality of metering holes, an annulus bounded by a stator ring. In a preferred aspect of the present invention, a ring-shaped orifice plate interacting with the metering holes is provided within the annulus which closes these metering holes to a varying degree depending on the temperature of the air stream reaching the heating-cooling channel system.

Abstract: A cooling structure around the output shaft of an L-shaped vertical gas turbine, for cooling the output shaft effectively by a natural ventilation. A gas generator 5 is arranged horizontally whereas an output turbine 1 is arranged vertically, and a pump or the like is driven by an output shaft 3. A cylinder 20 is fitted in a space 12 between the output shaft 3 and a cylindrical casing 13 and is fixed at a cylindrical flange 20a. Cooling air 30 is caused to flow upward from between the cylinder 20 and the output shaft 3 by the ejector effect of an exhaust gas from below a baseplate 8 and by the vacuum in the casing and then to flow downward from the upper end of the cylinder 20 between the cylinder 20 and the cylindrical casing 13, so that it flows out from the lower portion into the package. The output shaft of the L-shaped vertical type gas turbine having a compact narrow space is effectively cooled therearound by the natural ventilation without providing any fan or the like.

Abstract: An article comprising an airfoil surface is provided with a thermal insulating outer layer on at least one region, but not all, of the airfoil surface. The region is selected from the airfoil surface which has been observed to experience more strenuous environmental operating conditions during service operation than the airfoil surface outside of the region. In one form, the thermal insulating outer layer is applied to at least one region of each of a plurality of airfoil surfaces. Each airfoil surface is disposed about an axis of rotation with the region of each airfoil surface facing generally outwardly from the axis of rotation and from each other. The airfoil surfaces are rotated about the axis of rotation while a thermal insulating material contacts at least the regions.

Abstract: A compact heat exchanger system 52 for a duct 32 of a gas turbine engine 10 is disclosed, the heat exchanger system being disposed between two locations having an adverse pressure gradient. Various construction details which reduce the impact of the system 52 on engine efficiency, provide acceptable levels of drag, and reduce the possibility of foreign object damage are developed. In one embodiment the system has a low profile inlet 58 adjacent the inner wall 36 of a fan duct and has a flow path 56 extending from the inlet 58 to the outlet 62 which is continuous under all operating conditions of the engine.

Abstract: A rotating shaft for pumping or degassing hydrogen from molten metal comprising a motor connected to the upper end of a hollow shaft. An impeller is connected to the lower end of the shaft in the molten metal. The shaft is telescopically housed within a heat resistant shield shaft. The shield is clamped in a state of longitudinal compression to prevent tensile forces from damaging the shield as the impeller is being rotated.

Abstract: A fan shroud for an internal combustion engine has a greater clearance from the cooling fan on the exhaust side of the engine than on the suction side. The greater clearance on the exhaust side aggressively increases the flow of cooling air on the exhaust side in the engine compartment. This equalizes the temperature throughout the engine, thereby reducing engine damage due to overheating.

Abstract: A rotary pump having a housing defining a flow path, a stator attached to the housing, a rotor which contacts the stator and rotates thereabout, a motor for rotating the rotor and semiconductor-based electronic components which draws the heat created by the frictional contact between the stator and rotor away from blood flowing through the housing. The rotary pump can be a centrifugal pump having a housing with a base plate, a rotor with rotor blades and a stator wherein the base plate and the rotor are shaped and proportioned such that blood is prevented from stagnating/collecting between the rotor blades and base plate.

Abstract: A gas turbine engine has an assembly of circumferentially spaced rotor blades each having a radial tip. A plurality of seal segments mounted for radial movement circumscribe the rotor blades. Each segment is connected to the casing through a seal carrier provided with a flexible membrane which divides high pressure air from low pressure into two channels.

Abstract: An apparatus for moving a stream of molten metal in a bath of molten metal having a pumping member, a pump housing, a power device, a connecting element to connect the power device to drive the pumping member in motion, and a shielding element rotatably mounted on the pump housing and drivingly connected to pumping member. The connecting element comprises a pumping shaft having an upper end connected to the power device, and a lower end drivingly connected to the shielding element to rotate the pumping member when the power device is actuated. The shaft and the shielding element have a first and a second coefficient of thermal expansion, respectively. The shaft is telescopically disposed in the shielding element out of contact with the molten metal and formed a chamber between the shaft and the shielding element sufficient to permit thermal expansion of the shaft without imposing a radial thermal stress on the shielding element.

Abstract: A heat sink mounted on a heat producing element for cooling the heat producing element attached on the printed board of the electronic apparatus, having a heat sink body made of a good heat conductive material and a fan assembly installed inside the heat sink body. The heat sink body is efficiently air-cooled by a cooling air generated by the rotation of the fan assembly. The cooling air forcibly cools a base and a fixing wall of the base adjacent to the heat producing element and plate-like radiating fins or a pin-like radiating fins are protruded on the heat sink body to radiate the heat effectively. The position of the fan assembly is at the center of the heat sink body or is at the offset position from the center of the heat sink body. The heat sink of the present invention can be installed in a portable electronic apparatus such as a portable computer.