Abstract: A transition element between components of a flue-gas duct of a gas turbine includes a first heat-insulation element for reducing material stresses between the components during operation of the gas turbine. The thickness of the heat-insulation element varies as a function of a spatial variable along the flue-gas duct, to set a prescribed temperature profile in a transition region. A second heat-insulation element is provided for permitting a transition from an internally insulated component to an externally insulated component. The thickness of the second heat-insulation element varies in the opposite direction to the thickness of the first heat-insulation element.

Abstract: A flow stabilizer is provided for reducing low frequency flow oscillations within and the resultant noise from the impeller of a transverse fan. Such oscillations and noise can arise in installations where the fan is located downstream of the heat exchanger in an air conditioning unit. The stabilizer is a vane located between the downstream face of the heat exchanger and the suction side of the impeller. The vane is positioned and oriented so as to reduce localized counter swirling flow that otherwise would cause oscillating blade stall within the impeller and associated noise.

Abstract: A variable diameter shroud ring (21) for the turbine of a gas turbine engine (10) comprises a support structure (25) which carries an annular array of circumferentially spaced apart ceramic segments (26). The radially outer surfaces of the segments (26) are overlaid by a plurality of circumferentially extending metallic sheets (38). The sheets (38) serve to inhibit gas leakage through gaps between the segments (26) as the diameter of the shroud ring (21) is varied.

Abstract: There is provided a cooled stationary blade of a gas turbine in which the portions which can be cooled sufficiently by air are air-cooled, and the portions which are difficult to cool by air are steam-cooled, by which high temperatures can be overcome. In a stationary blade 1, there is formed a serpentine passage 3 in which cooling steam flows and an air passage 10 adjacent to the trailing edge portion and separated from the serpentine passage 3. Also, an outside shroud 4 is formed with an air cooling passage 16 at the outer edge portion and a steam impingement cooling portion 17 and an air impingement cooling portion 18 on the inside of the air cooling passage 16. An inside shroud 11 is provided with an air cooling passage 19 at the outer edge portion and shaped holes 20 formed on the inside of the air cooling passage 19. The air flowing out through the shaped holes 20 performs film cooling.

Abstract: A heating or cooling apparatus for a turbo-machine housing collar that adjusts the diameter of the housing using chambers that are arcs of a circle through which gas is blown onto the ribs of the housing. The gas circulates in a counterflow direction or in alternate directions for adjacent chambers in order to equalize the blowing conditions at every paint of the ribs.

Abstract: A design for a vane segment having a closed-loop steam cooling system is provided. The vane segment comprises an outer shroud, an inner shroud and an airfoil, each component having a target surface on the inside surface of its walls. A plurality of rectangular waffle structures are provided on the target surface to enhance heat transfer between each component and cooling steam. Channel systems are provided in the shrouds to improve the flow of steam through the shrouds. Insert legs located in cavities in the airfoil are also provided. Each insert leg comprises outer channels located on a perimeter of the leg, each outer channel having an outer wall and impingement holes on the outer wall for producing impingement jets of cooling steam to contact the airfoil's target surface. Each insert leg further comprises a plurality of substantially rectangular-shaped ribs located on the outer wall and a plurality of openings located between outer channels of the leg to minimize cross flow degradation.

Abstract: A turbine (18) of a gas turbine engine includes erosion energy dissipaters (44) which comprise of a plurality of inlet orifices (46) and a large diameter outlet orifice (48). The erosion energy dissipater reduces erosion of associated structure due to impingement of particulates entrained in airstreams. Various construction details are described to provide cooling air containing entrained particulates to the high pressure turbine case of a gas turbine engine without eroding the case.

Abstract: A coolable double walled structure, for use and exposure in a hot gas flow environment, includes a jet issuing wall, a target wall spaced from the jet issuing wall defining at least one cavity therebetween. The jet issuing wall includes at least one impingement rail having a greater thickness than the jet issuing wall such that a bottom portion of the impingement rail extends within the cavity formed between the jet issuing wall and the target wall. A number of impingement ports are disposed within each impingement rail to provide flow communication through the jet issuing wall to the target wall. Due to the relatively thick dimensions of the impingement rail, the impingement ports disposed within respective impingement rails can be directionalized so as to provide for local cooling needs. In one embodiment, the entry areas of the impingement ports are bell shaped so as to lower inlet pressure loss.

Abstract: A cooling arrangement for a bladed rotor in a gas turbine engine, wherein each of the blades includes cooling air passages and a cover with curved fins is mounted adjacent to but connected to the rotor and spaced apart slightly from the rotor disc to form a passageway for the cooling fluid. The cooling arrangement includes a tapered, conically shaped inlet formed in the cooling passage which then diverges to form a diffuser near the outer end of the passageway. The cover includes an enlarged inner portion and a thin outer wall portion beyond the free ring diameter. A hammerhead is formed at the outer periphery of the cover whereby the hammerhead will move closer to the disc in response to centrifugal forces, thus sealing the passage.

Abstract: A cabinet having a plurality of compartments adapted to have disposed in a corresponding one thereof one of a plurality of processing unit modules. Each one of the modules includes a case. The case has a motherboard mounting surface adapted to have mounted thereto one of a plurality of differently configured motherboards, each one of the differently configured motherboards having a different arrangement of a CPU, main memory and I/O adapted cards. The case also has a bulkhead mounting surface adapted to have mounted thereto one of a plurality of differently configured I/O bulkheads, each one of the differently configured bulkheads being configured for a corresponding one of the differently configured motherboards. The case has a fan mounting surface adapted to have mounted thereto one of a plurality of differently configured fan assemblies, each one of the differently configured fan assemblies being configured for a corresponding one of the differently configured motherboards.

Abstract: A gas mixer (8) which placed in a flow of gases upstream of a ring (3) that is to be heated or cooled, the gas mixer (8) including a succession of mbers (12, 14, 15) having communication or outlet orifices (16, 17, 18) in large numbers in order to render uniform a rate and temperature of the gas flow. The gas mixer (8) is applicable to gas turbine engines.

Abstract: With the objective of providing a cooling fan and a cooling fan assembly in which the cooling efficiency is high, and which has been lightened, the invention has been composed by a cooling fan 1, a casing 2 composed from a casing main body 3 and a lid part 4 in which a circular aperture 42 is formed, a fan motor 5 arranged within this casing 2, a circuit board 8 and the like. A plurality of radiator plates 32 are arranged in a standing formation in the outer peripheral part 312 of the casing main body 3. The fan motor 5 includes a rotor 7 in which seven fan blades 72 are arranged as projecting toward the outer peripheral direction, and a stator 6 fixed in a base plate 31. The outermost diameter b of the large diameter part 722 of the fan blades 72 is set so that it is larger than the inner periphery of the aperture 42, and the outer diameter c of the inner diameter part 723 of the fan blades 72 is set as smaller than the inner diameter of the aperture 42.

Abstract: The apparatus is a heat pipe with an internal, multiple chamber evaporator for cooling a turbine engine stator vane. The evaporator comprises leading edge, middle, and trailing edge chambers within the stator vane, with the chambers defined by structural support ribs. Each chamber is constructed with a continuous fine pore metal powder wick coating the internal surfaces of the chamber and enclosing the chamber's central vapor space, except the wick at the very trailing edge of the vane is formed by screen embedded in the adjacent powder wick. The evaporator chambers have capillary arteries which extend through the adiabatic section of the heat pipe and terminate in a condenser wick within a heat sink structure exposed to cooler air. A capillary artery also interconnects the wick of the trailing edge chamber to the wick of the middle chamber.

Abstract: A device for mounting a ventilating fan in a portable computer that uses a combination boss and bracket to simplify the assembly process. The fan mounting device of the present invention allows the space occupied by the fan within a portable computer to be minimized and the number of parts necessary for mounting the fan to be reduced. This results in a timesavings during the fan assembly process and improves the total efficiency of the computer assembly process.

Abstract: This ventilation apparatus uses gas under pressure diverted from a cooler area of the turbine that reaches a chamber and (8) successively passes through a cover (6) perforated with flow-restricting apertures (13), and then a wall (7) perforated with distribution apertures (12) before reaching a stator ring exposed to the heat that must be cooled, that economizes the ventilation gas due to the almost unperforated cover (6). This construction can be fitted to high pressure turbine stator rings. The cover and the wall form a single unit and the apertures restricting the flow are in the form of nozzles opening into the volume formed by the unit.

Abstract: A machine for circulating cooling water through manufacturing process equipment includes a combination pump and heat exchanger assembly. The machine has a cast metal pump case with two upwardly opening sockets receiving the lower ends of two tanks, one of them "the suction tank" communicating through the case with the pump impeller intake, and the other "the discharge tank" communicating with the impeller discharge. The tanks are constructed to function as heat exchangers, and they are readily and removably secured to the pump case by threaded fasteners and are sealed therein by compression seals. The discharge tank has electrical heating elements. The suction tank has a motor-operated modulator valve precisely fixed thereon, so as to enable discharging excessively warm water from the process to drain while cool make-up water from city water supply is admitted through the suction tank to the pump.

Abstract: A heat sink apparatus for cooling a highly heat-generative semiconductor device in which a base of a heat sink is made larger in volume in its central portion than in its peripheral portion.

Abstract: A fluid cooled article having a protective coating on a surface, for example an air cooled gas turbine engine article having a Thermal Barrier Coating, includes through an article wall a fluid cooling passage, and typically a plurality of passages, having openings sized to maintain desired fluid flow, unobstructed by coating within the passage at an exit opening. The passage has a first or inlet opening, which establishes the amount of fluid flow through the passage, and a second opening through which the flow exits the passage through a wall surface on which the coating is deposited.

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.

Abstract: A turbo molecular pump comprising a plurality of moving blades and stationary blades arranged alternately in the axial direction in a pump casing having a gas suction port and exhaust port, a thread groove pump stage disposed on the exhaust side of the moving and stationary blades, and a spacer for fixing the position intervals of the stationary blades, characterized in that a heating apparatus includes a radiating plate is provided in a gas passage of the thread groove pump stage, and the radiating plate is connected to a heating portion located on the outside of the pump by a good heat conductor. The heating apparatus heats the gas in the thread groove pump stage to a temperature above the gas sublimation temperature.

Abstract: Layout for adjusting the diameter of a turbine engine ring (5) positioned facing mobile rotor blades (4) and connected to a case element (7). The latter is provided with a cavity (16) communicating with chambers (21, 23) around a gas flow stream (31). A limited air current traverses the cavity (16) and is sufficiently reduced to ensure the development of a heat convection, which renders uniform the temperature of the case element (7) and the ring (5) and consequently the diameter of the latter.

Abstract: A gas turbine engine casing includes a plurality of coaxially interconnected ring members each provided with a flange at each of their axial extents to facilitate interconnection of the ring members by bolts; each ring member is provided with an integral array of inwardly directed stator vanes and carries an abradable sealing material to cooperate with the tips of rotor blades of the engine.

Abstract: The inside of a vacuum pump is heated by means of a first heating unit to a temperature higher than the temperature at which products of reaction discharged from a process chamber are separated, and the inner surface of an exhaust pipe is heated to a temperature higher than the separation temperature by means of a second heating unit. If a vacuum process is carried out in the process chamber in this state, exhaust gas discharged from the process chamber can pass in a gaseous phase through the exhaust pipe and the vacuum pump without separating its unwanted by-products.

Abstract: This invention includes a detection system that can determine if a turbine component, such as a turbine vane or blade, has exceeded a critical temperature, such as a melting point, along any point along the entire surface of the vane or blade. This system can be employed in a conventional combustion turbine having a compressor, a combustor and a turbine section. Included within this system is a chemical coating disposed along the entire interior surface of a vane or blade and a closed loop cooling system that circulates a coolant through the interior of the vane or blade. If the temperature of the vane or blade exceeds a critical temperature, the chemical coating will be expelled from the vane or blade into the coolant. Since while traversing the closed loop cooling system the coolant passes through a detector, the presence of the chemical coating in the coolant will be sensed by the system. If the chemical coating is detected, this indicates that the vane or blade has exceeded a critical temperature.

Abstract: A CPU heat dissipating device includes a base made of heat conductive material, having a plurality of spaced fins defining air passages therebetween. A fan is disposed on the fins to induce force convection. An enlarged channel is formed between the fins to received therein an I-shaped spring plate having four co-planar limbs, each having an arm extending therefrom and substantially normal thereto with a catch formed on the free end of the arm to be received within a corresponding hole formed on a CPU casing. A circular bore is formed on the bottom of the channel and in communication therewith by means of a neck which supports the spring plate thereon. A circular rod is rotatably received within the bore, on which two radially-extending projections are provided.

Abstract: A labyrinth disk includes a main stiffener placed in the middle of the rim immediately below labyrinth elements. Attachment elements are preferably in the form of a bayonet attachment system using teeth fixed on the labyrinth disk crown and teeth fixed on the rotor. Attachment by bolting may optionally be used. The disk may be utilized with turbojets, on the cooling circuit, on the upstream side of the high pressure turbine.

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: The present invention relates to a device for bleeding off and cooling hot air in an aircraft engine, including:at least one hot air take-off at the outlet of the compressors of the engine,a cold air take-off downstream of the fan of the engine,a precooling heat exchanger between said hot air and said cold air.According to the invention, said precooling heat exchanger (18) comprises at least one (12A) of said linking arms (12) between the engine body (2) and the fan shroud (9), the said linking arm or arms (12A) acting as the exchanger, exhibiting a hollow structure traversed longitudinally by at least some of the hot air bled off at the outlet of the low pressure and/or high pressure stages of the compressors (3) of the engine.

Abstract: A method and device for the autolubrication of the rolling bearings of turbomachines. The method and device utilize pressure differences present in the turbomachine for sucking in the lubricating oil. Moreover, a pressure is built up in centrifuges arranged on a shaft, and is used for the direct injection of the lubricating oil into the rolling bearings. For this purpose, an annular element imparting a negative pressure is arranged stationarily on the shaft, and is designed as a negative pressure chamber. The negative pressure chamber is connected via an oil suction conduit to an oil sump holding the lubricating oil and via a first air conduit to a negative pressure region of the turbomachine. The oil sump is connected via a second air conduit to an overpressure region of the turbomachine. A separating point is arranged between the oil suction conduit and the negative pressure region, preferably in the first air conduit.

Abstract: A fan/pins seat assembly includes a pins seat, an integrated circuit mounted on the pins seat, a finned plate mounted to an upper surface of the integrated circuit and including a plurality fins extending upwardly from an upper side thereof, and a board member mounted to the finned plate and having a fan mounted thereon. The pins seat includes a first engaging member provided thereon, and the board member includes a second engaging member formed thereon for releasably engaging with the first engaging member.

Abstract: An arrangement for a dry-gas sliding ring seal in a turbomachine which establishes ambient conditions in the region of the dry-gas sliding ring seals under which no fluid precipitates regardless of whether the machine is operating or not. By supplying heat to the leakage flow during standstill of the turbomachine in a manner similar to that during its operation, an undercooling in the region of the dry-gas sliding ring seal with all its negative effects can be suppressed; and the start-up of the turbomachine takes place starting from a substantially safer operating state.

Abstract: The inter-disk cavity between turbine rotor disks is used to pressurize cooling air. A plurality of ridges extend radially outwardly over the face of the rotor disks. When the rotor disks are rotated, the ridges cause the inter-disk cavity to compress air coolant flowing through the inter-disk cavity en route to the rotor blades. The ridges eliminate the need for an external compressor to pressurize the air coolant.

Abstract: In order to create an adjusting ring for the synchronous alteration of the angle of pitch of guide vanes of a compressor having several bearing points for mounting on a compressor housing of the compressor, which can be manufactured at least partially from materials with a low coefficient of thermal expansion and is, nevertheless, compatible with a metallic compressor housing with respect to temperature, it is suggested that the adjusting ring comprise curved ring segments each arranged between two adjacent bearing points, the curvature of the ring segments decreasing during an increase in the temperature of the ring segments so that the bearing points between the ring segments are displaced outwards in a radial direction.

Abstract: The heat sink of the present invention applicable to at least two heating elements including two integrated circuit packages includes a base member fixed to the integrated circuit packages and having a plurality of fins, and air cooling means provided at a substantially central position of the base member. This construction allows an improvement in reliability, a reduction in noise, and a reduction in power consumption.

Abstract: An improved heat insulation assembly for a thermal turbo-engine having hollow spaces, is provided with the assembly including a heat-insulating material enclosed within a heat-resistant cover that is formed such that it permits an increase in the inner volume, and the heat-insulating material being a heat-insulating material which increases its volume upon heating to such an extent that the cover is expandable until contact with the inner side of a corresponding hollow space.

Abstract: Rotary fluid handling apparatus employing a wheel to provide multi-stage compression or expansion. A wheel having a first set of vanes includes a shroud about those vanes with a second set of vanes outwardly of the shroud. One set of vanes provides for low specific speed flow while the other set of vanes provides for high specific speed flow. A transfer passage interconnects the outlet of the first stage with the inlet of the second stage. The difference in temperature between the inlet flow to the system and the outlet flow from the system may be exchanged to increase efficiency. The multi-stage wheel and associated passages may be configured for either compression or turboexpansion.

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.

Abstract: An engine case of a gas turbine engine is selectively coated with a thermal barrier coating to control axial clearance between rotating and stationary airfoils. The coating is applied to the thinner portions of the engine case to retard thermal expansion of these portions of the engine case during transient conditions of the gas turbine engine operation. The selectively coated engine case responds substantially uniformly to heating and thermal expansion during transient conditions, thereby reducing axial vane lean in gas turbine engines.

Abstract: In an arrangement for influencing the radial clearance of the blading of an axial-flow, highly loaded compressor which essentially comprises a rotor (1) equipped with moving blades (2) and a blade carrier (3) which is equipped with guide blades (4) and is hung in a casing (5), the blade carrier (3) has long and narrow mountings (7) for the guide blades (4), at least one hollow space (9) being arranged in the guide-blade roots (8), a hollow space (10) being present in each case in the embedded state in the peripheral direction between the guide-blade root (8), the two mountings (7) for a guide blade (4) and the blade carrier (3), a further hollow space (11) being present in each case in the peripheral direction between the blade carrier (3) and the mountings (7) for two successive guide blades (4), which hollow space (11) is defined by a plurality of segments (12) distributed over the periphery and connected to the guide-blade roots (8), and the hollow spaces (9, 10, 11) being filled with insulating material (

Abstract: An electronic component cooling apparatus capable of permitting a heat sink to exhibit satisfactory cooling efficiency and increasing durability of a motor. A plurality of radiation fins are provided on a base of a heat sink in a manner to surround an impeller including blades and fixed on a rotor of a motor. The radiation fins are arranged so as to be in conformity to a direction of flowing of air from the impeller being rotated. The blades each are constructed so as to permit air to be sucked in from a side of webs and discharged through an air passage defined between each adjacent two of the radiation fins.

Abstract: A high temperature, centrifugal pump includes a thermally isolated and dynamically air cooled shaft seal. Carbon graphite insulators formed of plural elements juxtaposed together (46) insulate the seal assembly (34) from the pump housing (16). A hollow drive shaft limits heat conducted from the impeller during operation while a fan (56) forcibly flows air past the seal assembly to conduct heat energy away from the shaft seal. The insulator (46) reduces heat energy conducted to the seal assembly (42).

Abstract: A vacuum pumping apparatus is presented having a Peltier element based device to provide a dual role of cooling for bearings/drive-motor and heating for sections prone to depositing reaction products. A housing (7) having the bearing and motor sections is provided with a Peltier element based device (20) to absorb the waste heat generated in the bearings and the drive motor, and transfer the waste heat to another section (17) of the apparatus to be released. The released heat may be used to heat that section of the device to facilitate vacuum processing, wherein reaction products are prone to sublime and deposit.

Abstract: To contain high energy fragments generated by a hub burst, a compressor containment assembly in a gas turbine engine includes a diffuser housing having an arcuate portion that defines a channel which traps the high energy fragments and an axial facing U-shaped which imparts flexibility. The assembly also includes a concave back shroud having a series of grooves that create resistance for the fragments as they slide along its surface. At its radial outer end the back shroud has an annular rim that absorbs some of the energy and delays the shearing of bolts. A bumper is disposed between the back shroud and a turbine wheel to limit the deflection of the back shroud during a hub burst.

Abstract: A parallel plate heat sink used in conjunction with an air moving device which provides an annular flow of air against the heat sink is further provided with enhanced flow deflector means which selectively block potential exhaust paths so as to redirect the flow of air to the region under a central hub of the fan. This transforms otherwise stagnant air volume in the center of the heat sink into a primary cooling region thus lowering conduction losses and electronic component junction temperatures.

Abstract: Turbo aero engine including a heating arrangement for the internal portions (12) of turbine disks on revving up so as to reduce the temperature gradient in the disks. Heating gas passes through pipes (11) integral with the stator and reheats the disks by passing through a gasket (13) designed with the tongues (18) and orifices (20 and 22) which allow the gas to circulate towards the zones to be heated when the revving up has firstly heated the portions of the machine close to the pipes (11) and then makes it possible to interrupt the communication when the temperatures even out and the original heat expansions become uniform and offset the orifices (20 and 23).

Abstract: A turbine shroud includes an annular shroud support joined to an annular outer casing and spaced radially inwardly therefrom to define an annular flow duct for receiving compressor bleed air. A plurality of shroud panels are joined to the shroud support and have a radially inner surface positionable radially above turbine rotor blades to define a tip clearance therebetween. An isolation shield is joined to the shroud support radially above the panels and includes a plurality of open-ended cells facing radially outwardly in the duct toward the outer casing for inducing drag in the bleed air flowable axially through the duct to thermally isolate the shroud support from the bleed air for controlling the tip clearance.

Abstract: Rotary fluid handling apparatus employing a wheel to provide multi-stage compression or expansion. A wheel having a first set of vanes includes a shroud about those vanes with a second set of vanes outwardly of the shroud. One set of vanes provides for low specific speed flow while the other set of vanes provides for high specific speed flow. A transfer passage interconnects the outlet of the first stage with the inlet of the second stage. The difference in temperature between the inlet flow to the system and the outlet flow from the system may be exchanged to increase efficiency. The multistage wheel and associated passages may be configured for either compression or turboexpansion.

Abstract: A turbopump which operates at cryogenic temperatures to pump cryogenic liquid fuels to high pressure which includes a rotating group including a shaft mounted turbine to directly drive a multistage pump with the rotating group being supported on process fluid foil journal bearings and a hydrostatic and hydrodynamic hybrid thrust bearing.

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.

Abstract: A low profile fan body for cooling an electronic component has a fan frame supporting a fan, which is mounted on a fan base forming a heat sink or heat transfer body. The fan has plurality of fan blades received within a plenum chamber defined within the heat sink. Each fan blade defines a first axial edge, a second axial edge on a substantially opposite side of the blade relative to the first axial edge, and a radial edge extending between the first and second axial edges. The heat sink defines a base portion for engaging an exposed surface of the electronic component, and a plurality of heat fins spaced relative to each other along the periphery of the sink and defining the plenum chamber. A pressure differential surface is disposed between the radial edges of the fan blades and the fins for directing air flow in the axial direction of the fan.