Abstract: A screw compressor includes a housing and a screw rotor disposed in the housing and rotatable relative to the housing for compressing a refrigerant, the housing and the screw rotor having a rest condition, and an operating condition wherein at least one of the housing and the rotor deflect from the rest condition, and structure for at least one of reducing deflection from the rest condition and evenly distributing deflection from the rest condition when the rotor is in the operating condition, whereby clearance between the housing and the rotor is optimized in the operating condition.

Abstract: A very thin fan motor with an attached heat sink that has high heat radiation and air cooling effects in a small, flat, thin package, that has a simple and easily assembled overall structure as a fan motor, and that has superior cooling efficiency.

Abstract: A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, on the other hand, adjacent to the heat shield carrier.

Abstract: In a gas turbine, blade ring cooling passages are provided inside a first blade ring and a second blade ring. The blade ring cooling passages are connected with each other through a communication pipe that is arranged in an axial direction of the blade ring. From outside of a wheel chamber, cooling air to cool down stationary blades is sent with pressure into an inside of the stationary blades that are installed on an inner wall of the blade rings. Thermal shields are provided on outer surfaces of the blade rings and communication pipes through gaps therebetween. In the gaps between the outer surfaces of the blade rings or the outer surfaces of the communication pipes and the thermal shields, partitions are installed to stagnate the cooling air to cool down the stationary blades.

Abstract: A high-pressure turbine nozzle-vane band for a gas turbine engine. The band includes an inside surface supporting at least one guide vane having a trailing edge that is directed towards a downstream end of the band, and an outside surface, opposite the inside surface, from which a flange extends radially, defining firstly, upstream from the flange, a passage for cooling-air, and secondly, downstream from the flange, a cavity. The inside surface of the band is provided, between the trailing edge of the guide vane and the downstream end of the band, with a coating forming a thermal barrier enabling a temperature gradient generated in the band by the air spinning in the cavity to be increased.

Abstract: A component for use in a flow path of a gas turbine engine. The component includes a body having an exterior surface mountable in the gas turbine engine so the exterior surface is exposed to gases flowing through the flow path of the engine. The body has a cooling hole extending through the body to the exterior surface for transporting cooling air from a cooling air source outside the flow path of the engine to the exterior surface of the body for providing a layer of cooling air adjacent the exterior surface of the body to cool the surface and create a thermal barrier between the exterior surface and the gases flowing through the flow path of the gas turbine engine. The cooling hole is defined by an elongate annular surface extending through the body of the component and terminating at the exterior surface of the body. The hole has a length, a maximum width less than about 0.

Abstract: Turbine insulation is disclosed, and comprises blankets, ribs and coupling members. The blankets define, with the turbine, an annular channel in receipt of the turbine vertical joint and a pair of longitudinal channels each in receipt of a respective turbine horizontal joint. A pair of ribs are positioned in each longitudinal channel, in volume-filling relation thereto and overlapping the blankets disposed, respectively, fore and aft of the vertical joint. A pair of ribs are positioned in volume-filling relation to the annular channel and overlapping the blankets disposed, respectively, on the upper and lower arcuate portions of the housing. A coupling member is positioned in each longitudinal channel at its intersection with the annular channel, in volume-filling relation to a void defined by the housing and the ribs and in lapped relation to the ribs.

Abstract: A fan holder (10) for mounting a fan (30) to a heat sink (20) includes a rectangular base (12). The base is attached to the heat sink, and supports the fan thereon. An opening (14) is defined in the base, for providing airflow access from the fan to the heat sink. A pair of tabs (16) depends from each of opposite sides of the base. Each pair of tabs is disposed at respective opposite ends of the respective side of the base. A stop (161) integrally extends from each tab, the stop engaging in a corresponding slot of the heat sink. A handle (163) integrally extends from each tab, for facilitating manual operation whereby the tab is moved resiliently. In a preferred embodiment, each stop is orthogonal to both the tab and the base. In an alternative embodiment, each stop is orthogonal to the tab and parallel to the base.

Abstract: A charge air conditioning system, including a charge air booster, a refrigerant-to-air intercooler which is integral with the charge air booster, and a refrigeration system for supplying refrigerant to the refrigerant-to-air intercooler.

Abstract: A heat dissipation apparatus for a notebook computer with a desktop central processing unit is described. The heat dissipation apparatus has a heat pipe, a first heat exchanger, a first fan, a second heat exchanger, and a second fan. The heat pipe couples with the desktop central processing unit to absorb heat therefrom. The first heat exchanger couples with the heat pipe directly above the desktop central processing unit. The first fan blows on the first heat exchanger to remove internal heat. The second heat exchanger couples with the heat pipe to absorb the residual heat from the heat pipe and the second fan blows on the second heat exchanger to remove the residual heat. The second fan starts working when the internal temperature of the notebook computer is too high. Both the first fan and second fan comprise two inlets respectively, and therefore the cold air is from both inside and outside of the notebook computer.

Abstract: The invention relates to a motor-fan unit (1) comprising a casing (10), a turbine (12) housed in the casing to generate an air flow therein, a motor (14) for driving the turbine, a support (20) for the motor, also forming a cover that closes off the casing on one side (10a) thereof, and a motor control module (30) associated with at least one radiator dissipating heat generated by components of the control module and exposed to the air flow generated in the casing. The control module (30) is mounted on the motor support cover (20) on the outside thereof and the radiator is at least partially engaged through at least one opening made in the motor support cover and opening laterally into the casing.

Abstract: A pump, particularly for washing machines, dishwashing machines or the like, having a housing and a heating device for the continuous heating of a liquid, particularly water, is proposed, in which the heating device is constructed as the circumferential wall of the housing and on one face of the heating device is arranged in sealing manner a base and on another face of the heating device is sealingly arranged a cover of the housing.

Abstract: A fan duct assembly includes a base (1), a first plate (20), a second plate (30) pivotably connected to the first plate, a connection member (40) pivotably connected to the second plate, and a fan cover (70) connected with the connection member. The base is mounted over a heat sink, and includes a pair of side panels (3). Each side panel has a horizontal portion (7), a slant portion (9) and a vertical portion (11). The horizontal portions, slant portions and vertical portions define a pair of locking apertures (13), respectively. The connection member has a pair of latches (52). The latches can be selectively engaged in any one pair of the locking apertures and orientations of the plates can be varied. Accordingly, outside cooling air from the fan cover can be guided through the connection member to the heat sink from a variety of directions.

Abstract: A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.

Abstract: A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.

Abstract: A method for forming a thermally isolating gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is positioned within the turbine housing with an outer baffle arranged about the floating liner and an inner baffle arranged within the floating liner. The inner and outer baffles are welled or brazed to the floating liner assembly to form a unitary assembly creating a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

Abstract: A heat dissipation apparatus for a computer system having a heat source. The heat dissipation apparatus includes an outlet, a temperature gradient maintaining device and an unpowered fan. The outlet is disposed on one side of the computer system. A thermal convection route exists between the heat source and the outlet. The temperature gradient maintaining device provides and maintains a temperature difference between the heat source and the outlet. The unpowered fan has a plurality of blades and is disposed on the thermal convection route.

Abstract: A heat-dissipating module includes a lower housing, a first magnet portion, a second magnet portion and a circuit board. The lower housing is made of a highly thermal conductive material. The upper housing has an opening in the center thereof, wherein when the upper housing and the lower housing are jointed together, an outlet is defined. The first magnet portion includes a plurality of first magnets. The second magnet portion has a plurality of second magnets, wherein a permanent magnetic field is formed between the plurality of first magnets and the plurality of second magnets. The circuit board is disposed between the first magnet portion and the second magnet portion and having a plurality of winding coils, wherein when a current is applied to the plurality of winding coils, the permanent magnetic field is repulsed to rotate the blade portion, and an ambient air flow is inhaled from the opening and exhaled via the outlet.

Abstract: Where gas turbine engine structure eg combustion equipment, is to be air impingement cooled, the surface which receives the air jets is so shaped as to produce boundary layer separation zones 34, 38 and 44 in the cooling air, as it spreads across the surface. Mixing of the boundary layer with the remainder of the air flow results, followed by the re-establishment of the boundary layer. The new boundary layer is cooler than the original layer and so provides more effective cooling.

Abstract: A modular computing system that includes an enclosure with a rack. A plurality of modular bricks that each include heat-generating electronic components are mounted in the rack. A fan brick that includes at least one fan is also mounted in the rack. The fan brick exchanges air between each modular brick and the fan brick to cool the electronic components in each of the modular bricks.

Abstract: A turbocharger including center housing with a thermally decoupling flange is provided. The flange, which extends generally radially outward from a body of the center housing, has a connection portion that can be used to mount the center housing to a turbine housing of the turbocharger. A curved portion of the flange is disposed between the connection portion and the housing body and provides a thermal decouple for reducing the thermal gradient in the connection portion. The curved portion can also increase the flexibility of the flange to reduce the stresses therein that result from temperature variations in the center housing.

Abstract: A bearing housing includes inner and outer shells through which a rotor shaft may extend. A service tube is fixedly joined to the inner shell and extends through a service aperture in the outer shell. A flexible coupling sealingly joins the service tube to the outer shell at the service aperture for permitting differential thermal movement between the inner and outer shells at the service tube.

Abstract: A vacuum pump has a casing having an inlet port and an outlet port, a flange integral with the casing and having a peripheral inner surface defining the inlet port and an end surface for connection to a container to be evacuated, and exhaust means for drawing in a gas through the inlet port and discharging the gas through the outlet port. A coating of material having low heat conductivity is disposed on the end surface of the flange.

Abstract: A rotor assembly for a gas turbine engine, having a rotor member with axially spaced-apart front and rear end portions. A thermal shield is located axially downstream of the rear end portion of the rotor for thermally shielding the same from the hot surrounding environment. The thermal shield includes a rear coverplate and an axial gap between the rear coverplate and the rear end portion of the rotor member.

Abstract: A coolable rotor blade having an airfoil having two serpentine passages is disclosed. Various construction details are developed for providing cooling to the leading edge region and the trailing edge region of the airfoil. In one detailed embodiment, the airfoil trip strips in the passages having constant height and constant pitch over each leg in most legs of the passages except for the legs closest to the edge regions of the airfoil.

Abstract: A gas turbine capable of minimizing the clearance between each of the rotor blades and partition ring, uses a structure in which the upstream thermally insulating ring is installed on the downstream blade ring.

Abstract: A radiation apparatus for dispersing heat generated by a processor of an electronic device includes a radiator bonded to the processor and an axial fan for drawing external air into the casing. The axial fan has a nose-shaped spindle with a nose tip close to the radiator to evenly channel the wind generated by the rotating axial fan to the radiator to disperse heat. The invention prevents reverse air flow at the air exit of the rotating axial fan spindle.

Abstract: Disclosed is a gas turbine blade, in which a ceramic covering, which is mechanically fastened to a metal platform, is arranged in a manner that the metal platform is protected against a hot gas in a hot gas duct of a gas turbine.

Abstract: A stage of turbine blades (40) in a gas turbine engine (10) is surrounded by an array of shroud segments (42). The upstream ends of the segments (42) have plenum chambers (54) into which cooling air is fed from a compressor (12) via one hole (66) of a pair of holes, the other being numbered (68). Air from the plenum chambers (54) passes out to film cool the interior surface of each respective segment (42). Air from holes (68) passes out to convection cool the exterior surface of each segment (42), which effect is enhanced by the provision of ribs (80) and fences (82).

Abstract: A wall structure for a gas turbine engine component is provided which comprises a wall having a first side facing a flow of hot gases and a second side exposed to a source of cooling fluid. The wall has a plurality of holes formed therethrough, and an outer layer disposed on the first side. The holes greatly increase the wetted surface area of the wall exposed to cooling flow.

Abstract: An apparatus and system for thermally isolating a gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is assembled within the housing with an outer baffle surrounding the floating liner and an inner baffle disposed within the floating liner. The floating liner creates a thermally isolated device to cover and protect the housing from high temperature. Openings formed in the outer baffle, floating liner and inner baffle create a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

Abstract: A machinery unit with a heat barrier which separates a part that is hot during operation from a cool part of the machinery unit. The machinery unit includes a fastening mechanism for holding the two parts together and at least one or more force-transmitting elements for producing a flux of force between the two parts. The present invention results in a less complicated, compact heat barrier due to the fact that the hot part and the cool part includes flange-like plates which are disposed adjacent one another at a spaced distance apart. The plates are joined together by one or more force-transmitting metal elements and the junction is made through a minimal cross-sectional area sufficient for the transmission force.

Abstract: An insert assembly is provided for a rotary machine wherein the rotary machine comprises a rotor and a casing. The rotor comprises a generally longitudinally-extending axis. The casing is generally coaxially aligned with the axis. The casing circumferentially surrounds and is radially spaced apart from the rotor. The insert assembly comprises a channel circumferentially disposed on the rotor and an insert circumferentially disposed in such channel such that the insert assembly is configured to thermally isolate frictional heat from the rotor to the insert.

Abstract: This invention relates to a method and an apparatus for the cooling of the casing (1) of the turbines (2, 3) of jet engines, in which cooling air is diverted from a bypass flow and supplied to the outer side of the casing via an inlet duct (8) provided with a shut-off element (5). According to the present invention, the cooling air is supplied to a first chamber (6) in which it is divided by volume. One portion of the cooling air is issued to the casing (1) via orifice holes (10), while another portion is ducted via several tubes (9) to a second chamber (7) which annularly encloses the casing (1) in the area of a low-pressure turbine (3).

Abstract: An article, for example a turbine engine component such as a shroud, airfoil, etc., comprises a wall having a first wall surface subject to a first temperature, for example from the flow stream of the engine. The wall includes a second wall surface, substantially opposite the first wall surface, for exposure to a cooling fluid, for example cooling air. The second wall surface includes a plurality of adjacent ribs protruding from the second wall surface to facilitate transfer of heat from the second wall surface. The ribs comprise a plurality of elongated rib portions each spaced apart one from another across a gap between rib portions, the gaps having a gap length in the range of about 0.002-0.05″.

Abstract: A method for forming a thermally isolating gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is positioned within the turbine housing with an outer baffle arranged about the floating liner and an inner baffle arranged within the floating liner. The inner and outer baffles are welled or brazed to the floating liner assembly to form a unitary assembly creating a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

Abstract: An apparatus and system for thermally isolating a gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is assembled within the housing with an outer baffle surrounding the floating liner and an inner baffle disposed within the floating liner. The floating liner creates a thermally isolated device to cover and protect the housing from high temperature. Openings formed in the outer baffle, floating liner and inner baffle create a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

Abstract: In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than that of the circumferential rib are, respectively, formed in plural lines, so that it is possible to suppress heat deformation in the axial direction which largely contributes to reduction of the tip clearance compared to head deformation in the circumferential direction more efficiently.

Abstract: A serpentine, slit fin (26) is provided for a heat sink device (10) used for cooling a electronic component (12) having a surface (14) that rejects heat. The heat sink (10) includes a plate (16) having first and second surfaces (18, 20), with the first surface (18) configured to receive heat from the surface (14) of the electronic component (12). The fin (26) is bonded to the second surface and includes a plurality of offset sidewall portions (48). In one form, a fan (22) is spaced above the second surface (20) to direct an impingement airflow (24) towards the second surface (20) substantially perpendicular to the second surface (20), and the serpentine, slit fin (26) underlies the fan (22) and is bonded to the second surface (20).

Abstract: A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).

Abstract: An article, for example a turbine engine component such as a shroud, airfoil, etc., comprises a wall having a first wall surface subject to a first temperature, for example from the flow stream of the engine. The wall includes a second wall surface, substantially opposite the first wall surface, for exposure to a cooling fluid, for example cooling air. The second wall surface includes a plurality of adjacent ribs protruding from the second wall surface to facilitate transfer of heat from the second wall surface. The ribs comprise a plurality of elongated rib portions each spaced apart one from another across a gap between rib portions, the gaps having a gap length in the range of about 0.002-0.05″.

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: An integrated cooling system for a turbocharger, suitable for an internal combustion engine. A cooling air shroud surrounds a portion of an interstage duct in a two-stage turbocharger, and may also surround a part of the outlet from the turbocharger. A fan on a turbocharger shaft is driven by the turbocharger turbine to draw air into the cooling air shroud, and pass the cooling air in heat exchange relationship with compressed air flowing through the turbocharger. The fan may also be used to precompress air compressed in the turbocharger.

Abstract: A split ring is disposed on an inner wall of a gas turbine casing. The split ring is composed of a plurality of split segments that are arranged on the inner wall of the casing in circumferential direction. A predetermined clearance is formed between the inner face of a split segment and the rotor blade tips. The split segments are arranged so that a predetermined circumferential clearance is formed between the split segments in order to allow the thermal expansion of the segments. A circumferential end face located upstream side of the segments with respect to the direction of the rotor blade rotation is connected to the inner face by a transition face having a surface formed as an inclined plane. The inclined plane prevents the swirl flow caused by the rotating rotor blade from impinging the upstream end face and, thereby, suppresses a temperature rise of the split segment at the upstream end face.

Abstract: The present invention relates to an improved fan structure used for a heat sink, and such fan comprises an axle having a first fan member and a second fan member coupled to each end of the axle, and a plurality of leaves arranged in opposite directions are disposed on the first and second fan members such that when the fan is in use, the first fan member is installed onto a heat sink and the second fan member deeply embedded into the heat sink. The hot air conducted to the heat sink is drawn and discharged by the leaves in opposite directions such that the cold air drawn by the leaves of first fan member blows towards the fins of the heat sink to accomplish the convection of the outside cold air and the hot air from the heat sink, which can accelerate the discharge of the hot air.

Abstract: A thermal insulator between the turbine and the compressor of a gas turbine engine is provided and at the same time it enables the air that has passed through the compressor to be heated by the heat of the hot turbine. A gas turbine engine comprises a centrifugal compressor for compressing air that is drawn or sucked into the compressor, a compressed air passage supplying the air compressed by the compressor to a burner, and a turbine driven by means of combustion gas generated in the burner. The compressor and the turbine are provided on a rotating shaft adjacent to each other in the axial direction. Evaporation sections on the radially inner side of a plurality of heat pipes provided in a radial form face towards the outer periphery of the rotating shaft between the compressor and the turbine, and condensation sections on the radially outer side of the heat pipes face towards the compressed air passage.

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: A gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air (70) from a compressor flows through cooling holes (61) of an impingement plate (60) to enter a cavity (62) and to impinge on a segmental ring (1) for cooling thereof. The cooling air (70) further flows into cooling passages (64) from openings (63) of the cavity (62) for cooling an interior of the segmental ring (1) and is discharged into a gas path from openings of a rear end of the segmental ring (1). Waffle pattern (10) of ribs arranged in a lattice shape is formed on an upper surface of the segmental ring (1) to thereby increase the rigidity. A plurality of slits (6) are formed in flanges (4, 5) extending in the turbine circumferential direction to thereby absorb the deformation and thermal deformation of the segmental ring (1) is suppressed.

Abstract: In a heat shield (10), in particular for the stator of gas turbines, which heat shield (10) is composed of a plurality of individual segments (10a, b; 20a, b), whose end surfaces (15a, b) respectively abut one another so as to form a gap (12), and which have cooling holes (13a, b) for cooling purposes in the region of the end surfaces (15a, b), through which cooling holes (13a, b) a cooling fluid is blown out into the gap (12), cooling is ensured, even when the gap is closed, by a chamber (11), which is widened relative to the gap (12) and into which the cooling holes (13a, b) open, being arranged in the region of the gap (12).

Abstract: Improved housings for computing devices are disclosed. One improvement pertains to a multi-axis ventilation system. Another improvement pertains to a push button latch for a portable computer. Still another improvement pertains to a media bay ejection system provided with a dampener. These improvements can be provided separately or in any combination in a given computing device.