Abstract: An apparatus is given for feeding a lubricating and cooling material to a pump or other device having a rotating member that operates intermittently. In particular it deals with methods for delivering lubricant to the pump whenever, and only whenever, the pump is running and with ensuring that the pump is always adequately lubricated when it is running. It is particularly useful for centrifugal pumps on mobile equipment, such as pumps used in cementing in the oil industry.

Abstract: A flange covering a disc of a turbine blade to allow ventilation. A diverted face of the disc is provided with a labyrinth seal with lickers to form a seal. Cutters of the lickers are inclined axially and staggered axially and radially, to off-set the center of gravity of a flexible web of the disc and to encourage deformation of the web towards the disc under the effect of centrifugal forces, to reinforce the contact of a bearing face with a pressure plate of the disc. Thus, hooks usually used to unite the periphery of the web to the disc become superfluous.

Abstract: A water pump (10) and impeller (30) for use in applications such as internal combustion engines. A plurality of holes (40, 44) are formed near the hub and periphery of the impeller (30) of the water pump to provide coolant flow through a cavity (22) housing a seal. The seal (18) is thereby cooled to prevent premature failure of the seal (18) due to overheating.

Abstract: A water pump (10) and impeller (30) for use in applications such as internal combustion engines. A plurality of holes (40, 44) are formed near the hub and periphery of the impeller (30) of the water pump to provide coolant flow through a cavity (22) housing a seal. The seal (18) is thereby cooled to prevent premature failure of the seal (18) due to overheating.

Abstract: A turbine includes a sealing element with a receiving area for sealing the guide blade vanes which are adjacent to each other in the peripheral direction of the turbine. The foot plates of the guide blade vanes extend into the receiving area. The edge area of the foot plates does not have to be reinforced compared to a conventional seal, which enables the entire foot plate to be cooled homogeneously. A closed cooling system can therefore be used for cooling, especially with steam.

Abstract: A shaft structure of a rotor tail end of a gas turbine in which a steam passage for supplying and recovering a steam for cooling rotor blades of the gas turbine extends along a center axis of the rotor assembly of the gas turbine is provided, wherein a center hole of the rotor tail end coaxial to the center axis of the steam passage is formed in the rotor tail end. Provision is also made of a thermal sleeve between the steam passage and the inner surface of the center hole of the rotor tail end, so that a thermal insulation gas layer is formed between the inner surface of the center hole of the rotor tail end and the thermal sleeve. The thermal insulation gas layer is isolated gas-tightly and liquid-tightly from the outside.

Abstract: An apparatus is given for feeding a lubricating and cooling material to a pump or other device having a rotating member that operates intermittently. In particular it deals with methods for delivering lubricant to the pump whenever, and only whenever, the pump is running and with ensuring that the pump is always adequately lubricated when it is running. It is particularly useful for centrifugal pumps on mobile equipment, such as pumps used in cementing in the oil industry.

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: The subcavity between a stator seal assembly and the upstream rotor disc in the interstage disc cavity of a gas turbine is divided into a radially inward region and a radially outward region by an annular baffle that extends from the seal assembly partially across the subcavity toward the rotor disc. The volume of cooling air injected into the interstage disc cavity can be reduced to increase turbine efficiency because the baffle interrupts recirculation in the subcavity to confine ingress of the hot main gas flow to the radially outward region away from the rotor seals.

Abstract: An expansion turbine for low-temperature applications containing a turbine stage into which a cold gas is admitted. A turbine rotor is mounted on a shaft. Also provided is a roller support for the shaft being lubricated with a minimum amount of oil or grease. The roller support contains a roller bearing located adjacent to the turbine stage. The roller bearing is comprised of an inner bearing ring, rollers, and an outer bearing ring supported on the side of the housing. An insulating bush made of ceramic engineering material is arranged between the inner bearing ring and the shaft. The bush thermally separates the inner bearing ring from the cold shaft.

Abstract: A heat shield of a turbo machine is provided with a microstructure. In a preferred embodiment, the microstructure element comprises a plateau, which is arranged on a rib in such a way that the structure has a “T”-shaped cross section. The ribs are preferably embodied as plates set on edge on the heat shield and are aligned with their surface perpendicular to the circumferential direction (U) of the turbo machine. This results in low bending dimensional rigidity in the circumferential direction. In this way, it is possible to accommodate scraping of a component involved in relative motion in the circumferential direction without plastic deformation. Moreover this arrangement gives the maximum possible resistance to a leakage flow. When used at high temperatures, it is furthermore advantageous to provide ways to enable a coolant to be supplied to the microstructure.

Abstract: Method and apparatus are described for a guard for a rotating member. The guard comprises a shell surrounding the rotating member, and a plenum member concentrically spaced from an interior surface of the shell, the shell comprising an inlet for receiving air and an outlet for discharging the air so that rotation of the rotating member draws air through the inlet and into the plenum member and the air circulates through the plenum member to cool the shell before it exhausts through the outlet.

Abstract: Nozzle assembly for injecting a liquid into a process unit through a cross fitting body having at least one of a first and second crossing passageway therethrough with a tubular member carrying a nozzle being injected through one of the cross passageways to position the nozzle carried on the tubular member for the injection of liquid into the processing unit with the liquid being supplied to the tubular member via the other crossing passageway through which liquid is supplied to openings in the tubular member which is in liquid communication with the first crossing passageway to supply liquid to the nozzle.

Abstract: A gas injector system includes a plenum with a plenum opening in the wall of the plenum. An injector is positioned at a location overlying the plenum opening. The injector includes a injector block affixed to the exterior surface of the plenum wall, a joint between the injector block and the plenum wall, and an angularly inclined injector passage extending through the injector block from an injector passage inlet to an injector passage outlet. The injector block is preferably brazed to the plenum wall for high-temperature applications, or adhesively joined for low-temperature applications.

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: A multi-stage compressor, including a system for the injection of a cooling liquid into at least a portion of the compressor stages to increase the efficiency of the multi-stage compressor by reducing the temperature of the compressed gas produced in the multi-stage compressor. A cleaning solution may also be injected through nozzles used for the injection of the cooling liquid.

Abstract: A shaft seal system prevents working gas in a centrifugal compressor from leaking outside from the compressor. The shaft seal system is of an oil film seal type and located in the compressor in which a plurality of centrifugal impellers are fitted on a single rotary shaft and are adapted to be rotated at a high speed. The system has two kinds of seal rings, that is, an atmospheric side seal ring and a gas side seal ring, which are loosely fitted in a casing in which bearing for rotatably journalling the rotary shaft are incorporated. A sealing sleeve shrinkage-fitted on the rotary shaft is arranged on the inner diameter side of the two kinds of seal rings. The rotary shaft is formed in its center axial part thereof with a bore extending from a suction side end to a position where the oil film seal is arranged, and a plurality of oil feed holes extending through the rotary shaft from the bore to the outer periphery of the rotary shaft.

Abstract: During a standard fired shutdown of a turbine, a loaded rabbet joint between the fourth stage wheel and the aft shaft of the machine can become unloaded causing a gap to occur due to a thermal mismatch at the rabbet joint with the bearing blower turned on. An open or unloaded rabbet could cause the parts to move relative to each other and therefore cause the rotor to lose balance. If the bearing blower is turned off during a shutdown, the forward air/oil seal temperature may exceed maximum design practice criterion due to “soak-back.” An air/oil seal temperature above the established maximum design limits could cause a bearing fire to occur, with catastrophic consequences to the machine. By controlling the bearing blower according to an optimized blower profile, the rabbet load can be maintained, and the air/oil seal temperature can be maintained below the established limits. A blower profile is determined according to a thermodynamic model of the system.

Abstract: An annular turbine frame includes a first ring such as a radially outer casing disposed coaxially about an axial centerline axis and having a plurality of circumferentially spaced apart first ports. A plurality of circumferentially spaced apart hollow struts are joined radially to the first ring by a corresponding plurality of collars. Each strut has radially opposite first and second ends, and a through channel extending therebetween. Each of the collars is disposed between a respective one of the strut first ends and the first ring in alignment with a respective one of the first ports for removably joining the struts to the first ring. Each of the collars includes a base disposed against the first ring and has a plurality of mounting holes for receiving mounting bolts therethrough to removably join the base to the first ring. The base has a central aperture aligned with the first port. Each collar mounting hole has a hole counterbore through a radially outer portion of the collar mounting hole.

Abstract: A thermal barrier for a nuclear reactor coolant pump includes a stack of pancake cooling coils encircling the pump shaft where it enters the pump chamber. This stack of coiling coils has an irregular peripheral surface formed by axially extending, diametrically opposed, inlet and outlet tubes which are circumferentially indexed for each pancake coil. The inner surface of a cylindrical cover has a complimentary inner peripheral surface formed by two sets of diametrically opposed cascaded steps so that the volume of the annulus between the coil stack and cover is minimized to reduce stratification of cooling water injected into the cover. A collar around the pump shaft at the opening in the end wall of the cover extends axially into the coil stack to prevent vortices produced by the spinning shaft from flowing across the end wall of the cover, while circumferentially spaced holes in the collar prevent significant alteration of the thermal conditions of the pancake coiling coils.

Abstract: An oil free high speed gas compressor driven by a high frequently electric motor with a soft magnetic armature which holds permanent magnets arranged peripherally and a centrifugal impeller overhung at one or at each end of the shaft of the armature of the motor, wherein the temperature of the armature is held within the characteristic temperature of its permanent magnets by a flow of cooling liquid through a central bore in the armature or by a flow of cooling liquid through a central drilling through a tie-bolt in thermal contact with a bore in the armature.

Abstract: A foil bearing assembly for use in a gas turbine engine is provided. The assembly includes an annular bearing carrier mounted to the housing of the engine. An annular foil carrier disposed within the bearing carrier and carrying a plurality of overlapping foils that engage an outer surface of a journal. The journal is mounted to the rotating assembly of the engine to define a cavity. Disposed in the cavity is a showerhead having an inlet for receiving a flow of cooling air and a plurality of orifices for providing impingement cooling of the inner surface of the journal. The use of a showerhead in a thrust foil bearing is also disclosed.

Abstract: A cooling architecture for flanges of a steam turbine casing, which effectively cools the flanges coupled by bolts to prevent the leakage of the steam caused by a decrease of the fastening force of the bolts. An upper casing 10 and a lower casing 11 are joined together at flanges 12 and 13 which are fastened and secured by bolts to hermetically seal a steam turbine. Pipes 20 are secured so as to be contacted to the peripheral of the flanges 12 and 13, and a side heat insulator 15a is fitted thereto from the outer side. Each pipe 20 is arranged corresponding to each bolt, or a plurality of pipes are arranged corresponding to each bolt 14. The flanges 12 and 13 are heated by the internal high-temperature steam, the ambient air 30 is introduced into the pipe 20 from the lower end thereof due to the natural convection thereby to cool the flanges 12, 13 and the bolts 14. Accordingly, a decrease of the fastening force of the bolts, and steam leakage, hardly occur.

Abstract: A method for cooling the trailing edge 126, 146 region of a stator vane platform 48, 54 and for forming a cooling passage 198, 214 using platform slots in the side of a stator vane is disclosed. Various steps are developed which provide for effective cooling with minimal intrusion into the working medium flowpath 18. In one particular embodiment, the method includes extending a feather seal slot rearwardly with an extension 88, 96 in facing sides 116, 118, or 136, 138 of a pair of vane platforms 48, 54 and for flowing cooling fluid laterally prior to discharging the cooling air for impingement cooling of an adjacent stator vane.

Abstract: The object of the invention is to create a centrifugal compressor with a cooling appliance which is simpler but more effective. This is achieved by the feed device (27) for the gaseous cooling medium (31) opening into the separating gap upstream of the mainly radially extending gap region (20) of the separating gap (18).

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

Abstract: A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.

Abstract: A mechanical seal assembly is adapted for use with a shaft supported by a bearing, the mechanical seal assembly being located near the bearing. The mechanical seal assembly includes a rotating member attached to the shaft and stationary member engaging the rotating member so that, when the shaft rotates, frictional heat is generated. The mechanical seal assembly includes a thermal barrier for reducing the amount of frictional heat reaching the bearing, thereby reducing the effect of the frictional heat on the lubrication of the bearing.

Abstract: A low friction bearing comprises a first element having a first surface. A second element having a second surface is rotatable about a centerline relative to the first element. A flow passage extends radially outward between the first surface and the second surface. The first surface and the second surface are separated by a fluid flow. The two surfaces are complementary and positioned in close proximity. The bearing finds a preferred application in a fluid cooled turbine to create a high temperature, high efficiency turbine.

Abstract: The invention relates to a rotor for thermal turbomachines in a steam power process with a centrally arranged hollow space, several axis-symmetrical hollow spaces, at least two pipes with different diameters and lengths, and at least two through-openings in the mantle, whereby at least one opening is arranged in the turbine part and at least one opening in the compressor part or the middle part, and the openings of the various pipes overlap in the warm operating state in the turbine part, while they overlap in the compressor part and middle part in the cold operating state. At the waste gas side end of the rotor, the hollow space is in the cylindrical part limited by the inside wall of the through-pipe and is provided for supplying steam. The pipe is surrounded in the cylindrical part by another hollow space that is arranged concentrically around the pipe and is provided for removing steam.

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

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

Abstract: A turbine shaft includes an inflow region for fluid, in particular steam, and at least two recesses spaced apart axially from one another and from the inflow region, for receiving at least one turbine blade in each case. A cavity in the turbine shaft is associated with the inflow region and is connected to a feed line and a discharge line for fluid for cooling the turbine shaft. A steam turbine and a method for cooling an inflow region of a turbine shaft disposed in a steam turbine, are also described.

Abstract: In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling passage is formed. The air enters a cavity from the air passage and is discharged to a gas passage through an air hole, a passage and a seal. Thus, the cavity is sealed at a high pressure. Cooling air is supplied from the air passage to a rotating blade through a cooling air hole, a cooling air chamber, a radial hole and a lower portion of a platform. The stationary blade is cooled by the air through the air passage. The cooling air can be supplied to the rotating blade at a low temperature and a high pressure as they are. Accordingly, the air can be also supplied to the rotating blade when a rotor is cooled by vapor.

Abstract: A pump assembly for conventionally driven centrifugal pumps having a rolling element comprised of product lubricated ceramic or hybrid anti-friction bearings. The ceramic bearings are comprised of ceramic balls and ceramic races, whereas the hybrid bearings are comprised of ceramic balls with races made of another material. The ability of these bearings to perform well with poor lubrication allows the fluid that is being pumped to be used to lubricate and cool the bearings. An alternate embodiment comprises a double suction pump with the same durability and cost saving advantages.

Abstract: A turbine shaft, in particular for a combined high-pressure/intermediate-pressure steam turbine accommodated in a common casing and a method of cooling a turbine shaft of a steam turbine. The turbine shaft has a cooling line in its interior for guiding cooling steam. The cooling line is connected on one side to an outflow line and on the other side to an inflow line. Steam cooling of the turbine shaft of a combined high-pressure/intermediate-pressure steam turbine can thereby be achieved by feeding steam from the high-pressure part through the inflow line to the intermediate-pressure part and through the outflow line.

Abstract: A seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet inter-segment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a platform and radially extending ribs, and the seal fits tightly in the groove providing an axial and a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross-section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.

Abstract: A thrust bearing assembly for a surface mounted centrifugal pump utilizes the pump liquid for lubrication of a thrust bearing and radial bearings. The thrust bearing mounts to the rearward end of the intake chamber. A communication passage extends between the thrust chamber and the intake chamber. A circulation tube leads from the intake chamber to the rearward end of the thrust chamber. A portion of the water being delivered to the intake chamber is diverted through the circulation tube, where it circulates through the thrust bearing and back to the intake of the pump. The shaft passes through the thrust chamber to an electrical motor. A mechanical seal seals the shaft at the rearward end of the thrust chamber.

Abstract: The method and apparatus for supplying an anti-oxidizing gas to, and simultaneously cooling a shaft and a fan blade used in, a special atmosphere, heat treatment chamber and for minimizing corrosion of the shaft and fan blade comprises the steps of and structure for: providing an elongate enclosure around an end section of a shaft having an outer end mounting a fan blade; surrounding a portion of the enclosure surrounding a portion of the shaft section located inwardly of a point where the fan blade is mounted to the outer end of the shaft section with a water jacket; directing water into the water jacket surrounding the portion of the enclosure surrounding the portion of the shaft section within the shaft enclosure; supplying anti-oxidizing filler gas to the chamber through the enclosure; and directing the gas to and through the enclosure along the shaft section, into and through the fan blade and then into the chamber for establishing a preheated, special atmosphere in the chamber.

Abstract: A rotor disc (15) has an axially enlarged hub portion (18) with a bore (20) through which a turbine shaft (19) extends in a coaxial, radially spaced apart relationship, the annular gap between the hub portion (18) and the shaft (19) receives a flow of temperature regulating fluid. The shaft (19) is provided with axially extending elongate projections (22) to increase the turbulence and relative velocity of the temperature regulating fluid adjacent the projections (22).

Abstract: A system to hydrostatically augment the thrust load capacity of a bilateral compliant foil hydrodynamic fluid film thrust bearing for a turbomachine is disclosed. A plurality of channels and fixed orifices are provided in the bearing thrust plate to deliver and regulate compressor bleed air flow to the compressor side of the bilateral compliant foil hydrodynamic fluid film thrust bearing which includes additional channels and orifices to direct the bleed air against the bearing rotor thrust disk. After impinging on the rotor thrust disk, the bleed air flow exits the thrust bearing through a plurality of variable orifices comprised of the hydrodynamic thrust bearing elements which are controlled in their flow conductance by the axial position of the rotor thrust disk. The bleed air may then pass through the adjacent journal bearing which functions as a fixed orifice.

Abstract: For fitment into the stuffing box of a centrifugal pump. A spiral-groove is cut on the outer surface of the rotor of a pair of tapered bearing surfaces. The groove is 0.02 mm deep, 2 mm wide, and its circumferential length is 50 cm. Barrier-liquid is fed to an entry-mouth of the spiral-groove, and groove generates a pressure in the stuffing box high enough to overcome process pressure. The barrier-liquid may be water. The interface between the bearing surfaces is sealed from the process-fluid and from the outside.

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: A thrust bearing assembly for a surface mounted centrifugal pump utilizes the pump liquid for lubrication of a thrust bearing and radial bearings. The thrust bearing mounts to the rearward end of the intake chamber. A communication passage extends between the thrust chamber and the intake chamber. A circulation tube leads from the intake chamber to the rearward end of the thrust chamber. A portion of the water being delivered to the intake chamber is diverted through the circulation tube, where it circulates through the thrust bearing and back to the intake of the pump. The shaft passes through the thrust chamber to an electrical motor. A mechanical seal seals the shaft at the rearward end of the thrust chamber.

Abstract: A centrifugal pump having a sealing flushing system. An annular flush ring insert having a plurality of radially spaced flush holes is provided adjacent the seal to be flushed so as to permit the seal to be flushed at a number of different places around the pump shaft and from a plurality of different radially spaced directions. The flushing fluid flows through a gland, into and through the flush ring insert, flushes (i.e. cleans and/or cools) the seal, and then flows on into the fluid being pumped.

Abstract: A seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet inter-segment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a platform and radially extending ribs, and the seal fits tightly in the groove providing an axial and a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross-section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.

Abstract: A gas turbine rotor steam gland includes a steam inlet supply scroll for supplying steam through radial slots to an axially extending passage in the rotor for steam cooling of hot gas path component parts. The scroll decreases in diameter in the circumferential direction of cooling medium flow to match its velocity with the surface speed of the rotor. An aft labyrinth seal is provided about the rotor. Forwardly of the scroll, a plurality of labyrinth-type seals are interspersed with extraction ports. The extraction ports, except for the final forwardmost extraction port, are maintained at a pressure below the pressure of the inlet supply steam whereby steam leakage past the seals flows into the extraction ports for removal. The final forward extraction port is maintained at sub-ambient pressure such that final steam leakage past the forward seals and ambient air leakage past the forwardmost seal combine and are extracted from the steam gland.

Abstract: A chemical processing centrifugal pump is provided with a triple cartridge seal arrangement including a first seal axially spaced from a pair of concentric seals. The passageway along the pump shaft between the single seal and the radially inwardmost concentric seal is filled with a pressurized barrier inert gas so as to create a gas seal while a barrier chamber defined between the concentric seals is filled with a pressurized barrier liquid. Accordingly, the concentric seals are lubricated by the barrier liquid disposed in the barrier chamber while the inboard seal is lubricated by the fluid being pumped. Optionally, the single seal may be lubricated by barrier liquid if such a pressurized liquid is used instead of the inert gas to fill the passageway.

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: The invention relates to a rotating machine part having, in particular, a flat housing or base with an essentially cylindrical outer wall or with symmetrically distributed projections which are arranged in particular in the form of a star, in particular a rotor (1) of a cycloid propeller, the cylinder axis or rotor axis being the same as the rotation axis and the machine part or housing rotating in an atmosphere or a medium which is able to transmit heat to a sufficient extent to produce a required cooling effect on the machine part or housing or in its interior.