Abstract: The invention relates to an axial compressor disk for a turbomachine, the disk including a bleed system for bleeding air centripetally from the compressor stream in order to cool a turbine, said bleed system comprising channels formed outside the working section of the disk and parallel to said section in an extra thickness projecting away from said working section on a face of said disk, wherein the bleed channels are axially open over substantially their entire radial extent.

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: An improved air-cooling system for high performance, high density electronic equipment comprises, in one embodiment, a single fan having a radial impeller, a baffle having an inlet portion to efficiently direct air into the fan intake, and a two-tiered outlet plenum to direct one airflow specifically at the highest heat-generating components and another airflow at all components. The air-cooling system is designed to provide maximum cooling for a low-height, high heat-generating electronics module such as a server. By using only a single fan that is matched to the low resistance airflow characteristics of the baffle, the air-cooling system offers significant advantages over multi-fan systems. Also described are a computer server and methods of making heat-dissipation equipment.

Abstract: The invention relates to a feed pump for fluidic media, comprising a displacement body that is mounted in a pump housing and equipped with slide bearings and connecting channels that connect the slide bearings to the produce channel on the suction side for recirculating the fed medium that lubricates the slide bearings. The connecting channels are linked to control channels that lead to the exterior and guide channels are provided in the extension of the connecting channels in the housing of the cover. Said guide channels accommodate the valve plungers, each of which has a constriction. The section of the valve plunger lying adjacent to the product channel has a length and a diameter, which correspond to the length and diameter of the connecting channel.

Abstract: A case that is used for an electronic or electric device has an opening portion arranged at a vicinity of a fan motor that generates airflow inside and outside the case. The opening portion has a protection portion for preventing a finger or other matters from entering the fan motor. The protection portion includes a first rib group extending linearly in a lateral direction, a second rib group extending linearly in a second direction vertical direction. Each of the ribs has an inclined surface that is along a direction of the airflow exhausted from the fan motor and faces the inside or the outside of the opening portion.

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 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: The invention is comprised of a venturi tube with a very narrow throat, a compressor fan at the intake end of said venturi tube, a blower fan at the output end, a plurality of turbinate fins on the interior of the intake end, and a means of heat dissipation on the exterior of the intake end of said venturi tube. Instead of a circular cross-section profile, the venturi tube has a cross-section of a polygon with no parallel sides, so that considerably less aerodynamic noise is generated than if the venturi tube's cross-section was circular. In addition, this cross-section results in variances in flow velocity along the cross-section, assuring continuous flow through the unit should a sonic choke occur at any point in the unit. The fans may be of any type and driven by any means appropriate to the respective model of the invention's application, i.e. by internally or externally mounted motor(s), power takeoff, belt drive from an external source of torque, etc.

Abstract: A low pressure turbine casing has a conical annular shell circumscribed about a centerline. A forward flange depends from a forward end of the annular shell and a forward hook extends aftwardly from the forward flange. First and second rails having first and second hooks, respectively, extend aftwardly from the annular shell. First and second cooling holes extend through the first and second rails, respectively. Cooling air feed holes extend through the forward flange. The first and second cooling holes may be radially disposed through the first and second rails, respectively, with respect to the centerline or disposed through the first and second rails at an oblique angle with respect to the centerline. A low pressure turbine casing and shroud assembly further includes a first annular cavity in fluid flow communication with the first cooling holes and the second cooling holes. A second annular cavity is in fluid flow communication with the first and second cooling holes.

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 fan shroud includes a barrel portion which surrounds a cooling fan. The barrel portion includes a first cylindrical portion located within a second cylindrical portion about a cooling fan axis of rotation. A multiple of webs are located between the first and second cylindrical portions which strengthen the barrel portion to an extent that a relatively lightweight inexpensive plastic material may be utilized to form the fan shroud without reducing the strength thereof. The webs also provide a multiple of mounting points which may receive a bracket to retain the numerous cables, conduits, hoses, sensors and the like which must be arranged within an engine compartment.

Abstract: A method of increasing the power generated by a steam turbine includes the step of receiving, at a steam turbine final stage, a steam byproduct with an electrically charged component. An electric field is created immediately proximate to the steam turbine final stage to substantially eliminate the electrically charged component from the steam byproduct and thereby reduce turbulence associated with the steam byproduct.

Abstract: A fan housing of a fan unit includes a housing wall standing from the surface of a printed circuit board. The printed circuit board serves to establish the fan housing in cooperation with the housing wall. The fan housing further includes a ceiling wall connected to the housing wall. The ceiling wall extends along a datum plane parallel to the surface of the printed circuit board. A high speed airflow can be generated within the fan housing. The air flow promotes the heat radiation from the printed circuit board. An electrically conductive wiring pattern extending over the surface of the printed circuit board may further promote the heat radiation from the printed circuit board.

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 cooling fan dust guard has provided on the inner side of fan blades multiples of fins at equal distance from one another around the spindle to create disturbance as the fan blades rotate to outwardly expel the airflow so to prevent the airflow carrying dust an easy ingression of the dust into the spindle and help cool down the stator assembly.

Abstract: The invention is comprised of a venturi tube with a very narrow throat, a compressor fan at the intake end of said venturi tube, a blower fan at the output end, a plurality of turbinate fins on the interior of the intake end, and a means of heat dissipation on the exterior of the intake end of said venturi tube. Instead of a circular cross-section profile, the venturi tube has a cross-section of a polygon with no parallel sides, so that considerably less aerodynamic noise is generated than if the venturi tube's cross-section was circular. In addition, this cross-section results in variances in flow velocity along the cross-section, assuring continuous flow through the unit should a sonic choke occur at any point in the unit. The fans may be of any type and driven by any means appropriate to the respective model of the invention's application, i.e. by internally or externally mounted motor(s), power takeoff, belt drive from an external source of torque, etc.

Abstract: An automatic cooling mechanism is provided for an electrical device having a high-temperature element and a rolling shaft. The mechanism includes a fan mounted within the electrical device and a transmission mechanism connected between the fan and the rolling shaft for transmitting rotational kinetic energy from the rolling shaft to the fan to rotate the fan for reducing the temperature of the high-temperature element.

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 frame for a gas turbine engine is provided comprising a central hub having a circumferentially extending flowpath surface enclosing an interior cavity and an annular outer casing connected to the hub by a plurality of struts extending radially from the hub to the casing, wherein the flowpath surface has a plurality of inlets disposed in flow communication with the interior cavity and a plurality of outlets disposed in flow communication with the interior cavity. A flowpath member for a turbine frame hub is also provided having a plurality of inlets and outlets formed therein.

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 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: 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 propeller-type fan including a pressure housing for improving air flow past a motor which powers the fan.

Abstract: A draining and cooling system for gas turbine cushions where the above-mentioned gas turbine has its own drain unit (11), which consists of two essentially concentric rings connected to each other by means of a number of spokes (12, 13). In the draining system described, the lubricating and cooling oil is fed into the gas turbine's drain unit (11) by means of at least a first pipe (14), located inside one of the spokes (12) and is drained by means of at least a second pipe (20), located inside one of the spokes (13).

Abstract: An air flow guide device for mounting on a heat dispensing fan includes a U-shaped frame and each of the three sides of the frame has a curve outer surface. A plate is connected between two distal ends of the frame and extends inclinedly from a top edge of the two distal ends of the frame, and a slot is defined between the two distal ends of the frame and the plate. Air flow smoothly flows over the curve smooth surfaces and is sucked by the fan. The plate prevents the exhausted air from being sucked by the fan.

Abstract: A heat dissipater structure has a heat sink base with peripheral sides thereof folded upwards from the bottom plate and cut into a plurality of lateral plates at proper angles to form wind channels for current conduction and to define a receiving slot at the center for holding a fan. A convex block is disposed on two opposite lateral plates for easily hooking and assembling a cover body so as to allow the air current inducted by the fan to rapidly dissipate the heat absorbed by the bottom plate outwardly through the wind channels formed by the interference of the lateral plates.

Abstract: Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system.

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: A “fan apparatus for the server” includes a fan casing placed at proper location on both sides of the server, and using a fan casing to fix a heat sink fan in order to keep a proper distance from side plate of the server, so that there are maximum air flow passing in and out during the operation to perform heat dissipation; and further, said heat sink fan enables a smoother air flow to decrease occurrence of turbulence and wind shear noise.

Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Abstract: An inner shroud assembly for a turbine comprising a plurality of part-annular segments combining to form an inner, annular shroud adapted to surround rotating components of a turbine, each segment having a pair of end faces that are juxtaposed similar end faces on adjacent segments with gaps therebetween; at least one convection cooling hole in the segment, opening along at least one of the pair of end faces. The cooling hole opens specifically into a diffuser recess formed in one of the pair of end faces for diffusing the flow of cooling air into the gap.

Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Abstract: Provided is a device for supplying seal air to the bearings of a gas turbine engine which allows the seal pressure to be kept even between the front and rear gear boxes without complicating the passages for supplying the seal air to the bearing boxes. Sealing air drawn from a part of high pressure compressor is conducted through passages defined between the inner periphery of the rotors of the high pressure compressor and a high pressure turbine and the outer periphery of the outer shaft, and is distributed to the front and rear bearing boxes. By appropriately providing narrowed parts in these passages, seal air is evenly distributed between the front and rear bearing boxes. Thus, even in case of a failure of one of the oil seals, any concentrated leakage of the lubricating oil can be avoided.

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: An embodiment providing a seal assembly for turbomachinery for controlling flow of a fluid medium in a fluid path comprises a casing having an internal pressure load path and a seal carrier chamber. A movable seal carrier is disposed within the seal carrier chamber and interposed between the pressure load path and an external flow path. In addition, a pressure selecting apparatus is coupled to the pressure load path to control flow therethrough. Moreover, the position of the movable seal carrier moves in response to a pressure differential determined by the pressure selecting apparatus between the pressure load path and the external flow path.

Abstract: A heat dissipating and power cutting-off device of a pump has a heat dissipating ceramics ring fitted in a plastic member to form watertight connection in between to prevent water from flowing to a motor. The plastic member has a pivotal hole for a main blade wheel connected to a shaft of the motor, and for a shaft seal tightly fitted in same and said ceramics ring. The ring has an annular trench forming between on outer and an inner annular portions for increasing contact area with water so that heat passing through said ring can be dissipated to prevent plastic member from getting melted by said heat. A power cutting-off member is connected to the motor, and has a sensing element abutting the ceramics ring to sense a temperature of same for activation of the cutting-off member when a racing of the motor occurs to cause temperature of both the motor and the ring to rise.

Abstract: The invention relates to a fan for producing a fluid flow, particularly an air flow.

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: The invention provides a kind of frame structure for radiator fan. The main specialty is the frame combined with the fan by using of arc clasps on the outer rim to inlay into the grooves in the inner loop of the radiator that makes the frame can be firmly connected to the radiator without any bolt-fixed element. Besides, for designing the folds in the frame bridge elements and spring laminations in the outer rim of inner loop to absorb the fan's vibration energy to prevent the fan falling off and reduce noise.

Abstract: A gas turbine engine including an active clearance control system that facilitates extending a useful life of a rotor assembly in a cost effective and reliable manner is described. The engine includes at least one rotor assembly and an engine casing that extends circumferentially around the rotor assembly, such that a tip clearance is defined between the rotor assembly and the engine casing. The clearance control system includes a plurality of panels that couple to extend circumferentially around the engine. Each clearance control system panel includes a circumferential feed duct that is formed integrally with the panel.

Abstract: A gas turbine engine including an active clearance control system that facilitates extending a useful life of a rotor assembly in a cost effective and reliable manner is described. The engine includes at least one rotor assembly and an engine casing that extends circumferentially around the rotor assembly, such that a tip clearance is defined between the rotor assembly and the engine casing. The clearance control system includes a plurality of panels that couple to extend circumferentially around the engine. Each clearance control system panel includes a circumferential feed duct that is formed integrally with the panel.

Abstract: A hermetic motor compressor unit for household and similar refrigeration appliances, comprising a sealed casing having a bottom that forms a sump for holding lubricating oil. Inside of the casing is a compressor and driving motor that share a common hollow crankshaft that rotates about a vertical axis. To ensure effective lubricating oil flow into the hollow crankshaft, a means for providing suction comprising a sleeve is rigidly fixed to the lower end portion of the crankshaft. A fluted member made of a material with a lower thermal conductivity than the material from which the hollow crankshaft is made that is connected to the stator of the drive motor is inserted into the sleeve to draw the lubricating oil from the sump. The lubricating oil is drawn in from the oil sump into recesses in the fluted member when the sleeve is rotated into the position in which it allows the recesses to communicate with lower apertures in the sleeve. This occurs during the downstroke of the fluted member.

Abstract: A vacuum pump including a housing having a suction opening in its high-vacuum region, a gas outlet opening in its high pressure region, pump-active cooperating rotor and stator components arranged in the housing for pumping gases from the suction opening to the outlet opening, with an end of the pump-active components adjoining the high pressure region being connected with the gas outlet opening via intermediate chamber, a heating device provided in the intermediate chamber and connected with stator components, which are located in the high pressure region, by a connection having a high thermal conductibility, and thermal resistance elements for separating the heating device from the housing.

Abstract: An improved structure computer heat dissipater, the heat sink base of which has four lateral walls of appropriate length with a plurality of draft guide ducts cut inward through them. The cut surfaces thereof are utilized as flow direction separators set to a particular angular arrangement to create a predetermined air flow path. Disposed on the bottom plate are thermal dissipation protuberances that collect the concentrated thermal energy developed by the heat generating electronic component in a computer. The air stream drawn in by the fan conveys the heat absorbed by the thermal dissipation protuberances along the air path formed by the flow direction separators and rapidly discharges it through the draft guide ducts.

Abstract: An air pump assembly (10) is provided which has a through flow type air-driving device (12) supported on an apertured partition wall (18) with the air-driving device (12) at one side and the motor (50) at the opposite side. The wall (18) is sandwiched between opposed pump and motor housings (14and 16) providing complementary ducts (27and 28) which communicate with opposed end caps (25 and 26) mounted on the end walls (21 and 22) of the pump and motor housings (14 and 16). The pump housing end wall (21) is apertured for air flow into the air-driving device (12) from the end cap (25) and its side wall supports an air outlet connection (13). A circuitous inlet passage to the air-driving device (12) is formed through end cap (26), ducts (27 and 28) and end cap (25). A circuitous outlet passage is formed from the air-driving device (12) through the motor housing (16), apertured partition wall (18) and motor housing (16).

Abstract: In a multi-stage turbine wherein at least one turbine wheel supports a row of buckets for rotation, and wherein the turbine wheel is located axially between first and second annular fixed arrays of nozzles, a cooling air circuit for purging a wheelspace between the turbine wheel and the second fixed annular array of nozzles comprising a flowpath through a shank portion of one or more buckets connecting a wheelspace between the turbine wheel and the first fixed annular array of nozzles with the wheelspace between the turbine wheel and the second fixed annular array of nozzles.

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 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 method of actively controlling the clearance between the rotating components and the stationary components of a combustion gas turbine engine includes employing an active control system that controls the temperature of bleed air that is delivered to the stationary and rotating components to control the thermal growth thereof and to avoid a pinch point. The active control system includes one or more sensors and controls the operation of heat sources interposed within the air passages that deliver bleed air to the stationary and rotating components.

Abstract: A centrifugal pump with a floating ring seal (34) provided in a sealing chamber (32) for pumped fluid and web-like flat pieces arranged in the sealing area (32) between the outer wall and the floating ring seal (34) extending in a longitudinal section approximately parallel to the pump shaft (14). At least one closable ventilation opening (47) is arranged in the head area of the sealing chamber (32), in addition to one blade-like flat piece (60, 60a) which is disposed on the peripheral wall (48) on both sides of the ventilation opening (47). From a cross-sectional point of view, both flat pieces (60, 60a) are inclined towards each other and define an antechamber with a slit (70) which is parallel to the pump shaft (14) at a distance from the peripheral wall. Preferably, the blade-like flat pieces (60, 60a) are fixed to the radial wall (55) and the free blade edge parallel thereto defines a radial slit with the other radial wall.