Abstract: The invention relates to a turbine engine (10), particularly for a helicopter, comprising a gas generator (12) and a free turbine (14) rotated by a gas flow (F) generated by the gas generator. The invention is characterized in that the turbine engine also comprises heating means (26) placed between the gas generator and the free turbine (14), the said heating means (26) being capable of increasing the temperature of the gas flow (f) generated by the gas generator (12) and driving the free turbine.

Abstract: Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring (22) held by a casing (24) of the turbine, and an annular thermal protection sheet mounted between the casing (24) and the ring (22), wherein the annular thermal protection sheet is formed by a plurality of curved plates (54, 56) mounted end-to-end and attached by pins (70) to the casing (24).

Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

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 extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall and the impingement sheet. The baffle has a collector plenum area that receives impingement cooling air from the air supply plenum and a channel in fluid communication with the collector plenum and extending outside the air supply plenum with openings to allow impingement cooling air to pass therethrough and having a series of lands extending into the channel wherein the lands are located in proximity to impingement cooling air outlets in the inner wall.

Abstract: A gas turbine engine system includes a gas turbine engine using vaporized liquefied gas as fuel. The gas turbine engine is configured to ingest intake air from an intake port and direct exhaust gases to an exhaust port. The gas turbine engine system also includes a heat exchanger with a heat transfer fluid therein. The heat exchanger is configured to create at least a part of the fuel by heating the liquefied gas. The gas turbine engine system also includes an intake air temperature control circuit. The intake air temperature control circuit includes conduits configured to direct the heat transfer fluid to the intake port and the exhaust port. The gas turbine engine system also includes a control system configured to selectively direct the heat transfer fluid to one of the intake port and the exhaust port.

Abstract: The invention relates to a turbocharger (1) having a cartridge (K), which is arranged in a turbine housing (2), for the variable turbine geometry, having a bearing housing (3) which is arranged between the turbine housing (2) and a compressor housing of a compressor wheel and in which is arranged a bearing arrangement for a shaft (W) which supports the turbine wheel and the compressor wheel, and having a plate spring (4) which is arranged between the cartridge (K) and the bearing housing (3), wherein the plate spring (4) is constructed from at least two material layers (5, 6) and an isolator (17).

Abstract: The present invention is a turbocharger unit (10) incorporating variable turbine geometry. The unit (10) has a turbine for receiving exhaust gases from an engine having a turbine wheel (14) located inside a turbine housing (12), and an intermediate housing (24) connected to the turbine housing (12), having a recessed portion (28). A spring member is located in the recessed portion (28), and a heat shield (32) for receives apply force from the spring member. There is also a cartridge (36) for providing variable turbine geometry located between a first disk (34) and a second disk (40) in the turbine housing (12); the second disk (40) is held in contact with the turbine housing (12) by a contoured sleeve (26). The apply force received by the heat shield (32) from the spring member transfers through the first disk (34), the cartridge (36), and the second disk (40), locating the cartridge (36) in proximate relationship to the turbine wheel (14).

Abstract: The aim of the invention is to provide a superheated component of a steam turbine installation with high thermal and mechanical resistance. To this end, the component comprises a lining applied to a body of the component, on a hot side facing a steam chamber, said lining being adapted to the contour of the component body. According to the invention, the lining comprises a number of moulded parts, each moulded part comprising a metallic and ceramic composite layer formed from at least one metallic layer and at least one ceramic layer. The ceramic layer is used especially as a insulating layer, and the metallic layer is especially used as a support or for protection against abrasion and/or erosion.

Abstract: A steam turbine (10) having an inner casing (11), in which a rotor (12) that can rotate about an axis (13) is arranged, a steam passage (14) being formed between the rotor (12) and the inner casing (11), in which steam passage there is a multi-stage arrangement of guide vanes (16) secured to the inner casing (12) and rotor blades (17) secured to the rotor (12), in which arrangement hot steam coming from an inlet (15) undergoes work-performing expansion. In a steam turbine of this type, the thermal loading of the rotor and/or inner casing, in particular when starting up, is reduced by virtue of the fact that at least in the steam passage (14) plate-like protective shields (18, 19, 20), which protect the surface of the rotor (12) or inner casing (11) beneath them from the direct action of the hot steam flowing through the steam passage (14), are arranged parallel and close to the surface of the rotor (12) and/or parallel and close to the inner surface of the inner casing (11).

Abstract: An aspect of the invention is a turbine blade for a gas turbine, comprising a blade root, adjoining which one after the other are a platform region having a transversely running platform and then a blade profile curved in the longitudinal direction, comprising at least one cavity which is open on the root side and through which a coolant can flow and which extends through the blade root and the platform region into the blade profile. The cavity is surrounded by an inner wall, on the surface of which structural elements influencing the coolant are provided. In order to prolong the service life of such a turbine blade, the invention proposes that a section, lying at least in the blade profile and adjoining the platform region, of the surface of the inner wall be free of structural elements.

Abstract: The invention relates to a radial fan (1), preferably a high-speed radial fan, comprising a blower wheel (8), a housing (2) which receives a rotor (6) and a stator (5) of an electrical drive (4) of the blower wheel shaft (7), and a cooling system. The aim of the invention is to develop one such radial fan in terms of the cooling system required. To this end, paths (30, 37) for a first cooling medium (Ki) and a second cooling medium (K2) are provided in the housing (2), the second cooling medium (K2) being cooled by the first cooling medium (Ki) by means of the housing (2), and said paths (30, 37) are separated from each other by intact material walls (40) of the housing (2).

Abstract: A braking mechanism is provided that is suitable for an expansion turbine that rotates at high speed. Upper end salient poles 26a and 26b are formed in two opposite places on the outer peripheral upper end of a rotating shaft 12, and lower end salient poles 28a and 28b are formed in two opposite places on the outer peripheral lower end of the rotating shaft 12 such that they are staggered in the vertical direction with respect to the upper end salient poles 26a and 26b. A casing 22 is provided in a location facing an outer periphery of the rotating shaft 12, and an excitation coil 30 is provided on the casing 22 for forming a magnetic path between the upper end salient poles 26a and 26b and the lower end salient poles 28a and 28b. By rotation of the rotating shaft 12, and by the magnetic path formed by the excitation coil 30, eddy currents are generated in the casing 22.

Abstract: In a centrifugal fan the diameter of the impeller is rendered less than 20 mm, yet by rotating it under rotational conditions in which the centrifugal force along the impeller periphery is 10,000 m/s2 or more, the static pressure that the fan generates is heightened. At the same time, rendering the vane spacing a predetermined width or less reduces noise. Configuring in this way produces a small-scale, high-static-pressure, low-noise fan for cooling electronic devices. Furthermore, by mounting the centrifugal fan on a heatsink having densely arranged heat-dissipating projections a small-scale, high-cooling-capacity, quiet cooling device is realized.

Abstract: A heat dissipation device includes a cooling fan (15) defining an air inlet and an air outlet (157) oriented perpendicular to the air inlet; a metal foam (11) is arranged in the air outlet of the cooling fan, and a heat pipe (13) has a condensing end (131) being thermally attached to the metal foam. The metal foam forms numerous open cells (118). A plurality of guiding holes (116) are defined in the metal foam facing to a rotor (153) of the cooling fan for an airflow generated by the cooling fan to flow therethrough. The guiding hole (116) has a size larger that that of the open cell (118). The guiding hole has an outer end opened to an outside of the cooling fan (15).

Abstract: The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in external contact with the cold flow (9) exiting the fan duct channel (13) and in close contract with the cooling air stream (29) drawn from said cold flow (9).

Abstract: A pump includes a DC motor (10) defining a chamber (108) and having a rotor (112) and a shaft (110) suitably received in the chamber, a motor shell (20) set around the DC motor, a rear cover assembly (30) jointed to the motor shell, a front cover assembly (40) secured to the rear cover assembly, and a check valve assembly (50) and a diaphragm assembly (60) set between the front cover assembly and the rear cover assembly. The DC motor defines a number of air inlets (116) and air outlets (118) at two side walls (104, 106) thereof, respectively. The shaft is equipped with a rotatable fan (10). The motor shell has a number of ventilation holes (200) in communication with the air outlets. The rear cover assembly defines a number of through-holes (300) communicated to the air inlets. The through-holes, the air inlets, the chamber, the air outlets and the ventilation holes jointly define an air flow path.

Abstract: The invention relates to a turbocharger (1) provided with a turbine housing (2) for turbine wheels, a cartridge (K) for the variable turbine geometry positioned in the turbine housing (2), a bearing housing (3) which is arranged between said turbine housing (2) and a compressor housing of the compressor wheel and in which a bearing arrangement for a shaft (W) carrying the turbine and compressor wheels is mounted and a pane system (4) placed between the cartridge (K) and the bearing housing (3). The inventive turbocharger is characterised in that said pane system (4) consists of at least two material layers (5, 6), an air gap (7) is formed between the material layers (5, 6), the materiel layer (5) is embodied in the form of a conical plate and the other material layer (6) is provided with a bend (8).

Abstract: A fluid pump (10) includes a pumping chamber (14), an inlet (16) and an outlet (18) fluidly connected with the pumping chamber, and a passage (24) fluidly connected between the inlet and the outlet. Fluid flowing through the passage bypasses the pumping chamber. In one example, the fluid pump (10) pumps coolant within a vehicle cooling system between a heater core (23b) and a vehicle engine (23a).

Abstract: An embodiment of the present invention provides an air conditioning system located upstream of the inlet system for a gas turbine. The air conditioning system may comprise at least one conditioning module for adjusting the temperature of the airstream. The at least one conditioning module may have a plurality of forms including at least one of the following systems: a chiller, an evaporative cooler; a spray cooler, or combinations thereof. The specific form of the at least one conditioning module may be determined in part the configuration of the gas turbine.

Abstract: A gas turbine engine is provided with a seal disk that rotates in a closely spaced relationship to a stationary vane. The stationary vane is provided with an abradable tip. The seal disk is provided with alternating portions of a relatively insulating material and a relatively abrasive material. The insulating material can assist the seal disk in resisting thermal expansion. The abrasive material abrades the abradable tip of the stationary vane, ensuring a close, rotating fit.

Abstract: An exhaust-gas turbocharger for an internal combustion engine, in particular of a motor vehicle, includes a turbine housing, a bearing housing, a guide vane carrier, a flow passage component which forms a portion of a flow passage in a turbine of the exhaust-gas turbocharger, and guide vanes, which are disposed on the guide vane carrier such that they can pivot in an annular passage formed between the flow passage component and the guide vane carrier. At least one securing bolt secures the guide vane carrier to the bearing housing. The securing bolt extends through the guide vane carrier and into the bearing housing in a plane parallel to the annular passage.

Abstract: A heat shield arrangement for local separation of a flow channel within a turbine engine, with respect to a stator housing radially surrounding the flow channel is provided. The heat shield includes two axially opposite joining contours which are each engageable with two components which are axially adjacent along the flow channel. Each provides a complementary reception contour for the joining contours. At least one of the reception contours has an axial clearance, in which the associated joining contour is axially displaceably mounted. At least one seal is provided between the axially displaceable joining contour and the reception contour. The seal is mounted movably within the reception contour or the joining contour in such a way that the seal is deflectable against a surface region of the reception contour or of the joining contour.

Abstract: A hermetic compressor with internal thermal insulation, comprising: a compression cylinder having one end closed by a valve plate provided with a discharge orifice and having a front face against which is mounted a cylinder cover internally defining a discharge chamber; and a spacing duct having one inlet end hermetically mounted to the front face of the valve plate and open to the discharge orifice and an outlet end hermetically mounted to the cylinder cover and open to the interior of the discharge chamber, said spacing duct defining a hermetic fluid communication between the interior of the compression cylinder and the discharge chamber maintaining the cylinder cover spaced from the valve plate and defining, with the latter, an annular plenum around said spacing duct.

Abstract: This wet compression invention with a vaporizable fluid mist demonstrates major performance improvements over the relevant art in achieving a high degree of saturation, providing sensible cooling, strongly reducing the temperature increase due to compression work, reducing excess diluent air flow for downstream combustion, reducing compression noise, and increasing the achievable compressor pressure ratio?.

Abstract: This invention provides a small, high efficiency, oil-free turbine-driven alternator (i.e. turboalternator) suitable for conversion of stored energy in a process gas to electrical power, facilitating recapture of energy during operation that would otherwise be wasted. The turboalternator includes a turbine and a generating device operatively connected together by a rotating shaft capable of rotating at high speeds. The rotating shaft is supported by foil gas bearings.

Abstract: A heat insulating structure for an expansion turbine includes an adiabatic expansion device including an expander body that includes an outlet passage for refrigerant fluid at a central portion thereof and an introduction chamber for refrigerant fluid communicating with an inlet of the outlet passage on an outer peripheral portion thereof, and a turbine impeller that is rotatably provided at the inlet and braked by a braking device. The adiabatic expansion device adiabatically expands refrigerant fluid by rotating the turbine impeller with refrigerant fluid that flows from the introduction chamber to the outlet passage side. A heat-insulating layer, which surrounds the entire periphery of the outlet passage over the entire length of the introduction chamber, is formed between the introduction chamber and the outlet passage. Accordingly, it is possible to improve turbine efficiency by reducing transfer of heat of refrigerant fluid from the introduction chamber to the outlet passage.

Abstract: A method for designing a fan having a motor which drives an impeller comprises providing an outlet guide vane assembly which includes a hub and a plurality of guide vanes that extend radially outwardly from the hub, attaching the hub to the motor, determining an approximate amount of heat which is generated by the motor during operation of the fan, determining an approximate surface area which is required to dissipate the heat into a surrounding air stream, and configuring the guide vanes to comprise a total surface area which is approximately equal to the required surface area. In this manner, the heat generated by the motor during operation of the fan can be dissipated by the guide vanes.

Abstract: A gas turbine engine component includes a platform and an airfoil extending from the platform. The platform includes an outer surface. A cover plate is positioned adjacent to the outer surface of the platform. A cooling channel extends between the outer surface and the cover plate and receives cooling air to cool the platform and the airfoil.

Abstract: A locking and fixing device for a heat shield element which can be connected to a rotor unit of an axial-flow turbomachine is described, which heat shield element can be arranged along a heat shield row axially directly next to at least one blade provided in a blade row and has, axially facing the blade, at least two projections of rib-like design which are spaced apart in the circular circumferential direction, are raised above a side wall section facing the blade and define a clear intermediate space which extends in the circular circumferential direction and into which a locking lug provided on the blade can be fitted. A method for producing a device in this respect is also described.

Abstract: A system for cooling the impeller of a centrifugal compressor in a turbomachine, this compressor (10) supplying an annular diffuser (12) comprising an end-piece (26) that extends downstream and along the impeller of the compressor and that is covered on the upstream side by an annular metal sheet (90) that delimits, with the impeller of the compressor, a first annular passageway (39) to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway (98) to carry away a portion of the air flow coming out of the diffuser.

Abstract: A conductive heat transfer system may include a heat conductive element to thermally couple the pump motor of a liftgate assembly to an outer surface of a pump motor housing assembly.

Abstract: An downstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located downstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the downstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.

Abstract: A fan motor having a small thickness and its impeller's blades formed to have a longer length in the diametrical direction than a width in the axial direction. Since the blade of the fan motor has a tooth structure or chamfers at its edge end in the diametrical direction, turbulence is forcibly evoked in an airflow to promote the turbulent diffusion, thereby suppressing the trailing vortex and reducing the aerodynamic noises, and thus the ventilation efficiency is improved.

Abstract: A pump including a pump housing, a fluid inlet, a fluid outlet, a pumping chamber in fluid communication with both the fluid inlet and the fluid outlet, a motor for pumping a working fluid, and a plate that is at least partially constructed of a heat conductive material and that at least partially defines the pumping chamber. The plate can transfer heat from the motor to the working fluid in the pumping chamber.

Abstract: A heat dissipation device includes a heat sink including a heat conducting portion and a plurality of fins extending from the heat conducting portion. The heat conducting portion has a base portion for contacting a heat generating device, and two wing portions extending from the base portion. The heat sink has two slits extending through two opposite sides thereof. A fan holder having a fan mounted thereon is attached to a face of the heat sink. The fan holder includes two brackets each having a rib engaged in a corresponding slit of the heat sink to thereby attach the fan holder to the heat sink, and a faceplate having the fan thereon. The faceplate has an ear secured to a corresponding wing portion of the heat sink by a screw and a tab extending upwardly beyond a top end of the heat sink.

Abstract: Disclosed is a thermoelectric fan for use with radiant heaters, particularly catalytic heaters. The thermoelectric fan of the present invention comprises a housing sub-assembly coupled to a thermal plate sub-assembly, the housing sub-assembly comprising a shrouded circulating air moving member, such as a fan blade, powered solely by the conversion of heat from a separate heater into electricity via an integrated thermoelectric module. Also disclosed is a self-powered fan that can safely perform in hazardous atmospheres while converting radiant heat to circulate air. The thermoelectric fan of the present invention ensures that the air within the space to be heated is more effectively distributed and temperature gradients are minimized. Also disclosed are methods for assembling, installing and safe operation of the thermoelectric fan.

Abstract: A pump includes a rotatable rotor installed in a motor part and at least one impeller installed in a pump part, capable of being rotated together with the rotor in unison. The rotor and the impeller are accommodated in a casing, and the impeller has an inlet at an inner periphery thereof and an outlet at an outer periphery thereof. A housing is arranged in both sides of an axial direction of the impeller and has an outer peripheral part coupled to the rotor at a rear side portion thereof, and the outer peripheral part is projected outwards further than a gap between an outer peripheral surface of the rotor and an inner peripheral surface of the casing in which the rotor is rotatably accommodated.

Abstract: A cooling fan assembly for cooling a heat exchanger includes a shroud having a plurality of stators extending radially to support a hub. A flow-guide including an outer rim and inner rim surrounds the shroud and extends to the heat exchanger. The outer rim extends from the heat exchanger to the stators. The inner rim extends annularly about the axis and curves convexly from the outer rim. A fan unit includes a plurality of fan blades extending radially from a motor supported by the hub. Each fan blade includes a leading edge facing the stators and a trailing edge facing in the opposite direction with a blade tip extending therebetween. A fan section extends from the inner rim and axially about the fan blades. The stators are disposed between the heat exchanger and the fan blades. The stators have a front edge facing the heat exchanger and a back edge facing the fan blades. Each stator is connected to the inner rim with the front edge extending radially outward and farther than the back edge.

Abstract: A fan heater includes a heater body, an electric unit, a plurality of fan assemblies, and a heating element. Each of the fan assemblies is mounted with the adjacent fan assembly to form a fan unit within the receiving cavity, wherein the fan unit is operatively coupled with the electric unit for being driven to rotate by the electric unit. The heating element is mounted within the receiving cavity in a vicinity of the air outlet, and electrically connected with the electric unit for being heated up at an elevated temperature, wherein the fan assemblies are adapted to draw air flowing from an air inlet to an air outlet via the heating element, so as to heat up the air drawn by the fan unit, and deliver the heated air to a predetermined heating zone from the air outlet.

Abstract: A supporting frame with locating function mainly includes a supporting portion and a plurality of connecting portions. The supporting portion is provided at a central area with a plurality of hollow spaces, and is connected at an upper side to a fan and at a lower side to a radiator. The supporting portion is provided on a rim area with fixing holes, via which fastening elements are extended to connect the supporting portion to the radiator. Each of the connecting portions includes an axially extended connecting hole, in which a locating mechanism is received. The connecting portion is connected at an upper side to the supporting portion, and at a lower side to a main board via screwing and elastic elements of the locating mechanism. With the supporting frame, the fan and the radiator can be quickly assembled to the main board.

Abstract: In one embodiment of the invention, a pump includes a pump housing, an impeller, and a motor. The pump housing has a pump chamber and a heat receiving plate to couple to a heat generating unit, such as a CPU. The impeller is provided in the pump chamber. The motor couples to the impeller to rotate it. A region of the heat receiving plate projects further outward than other regions to couple the heat receiving plate to the IC chip.

Abstract: Aspects of the invention are directed to systems for reducing the cooling requirements of a ring seal in a turbine engine. In one embodiment, the ring seal can be made of a ceramic material, such as a ceramic matrix composite. The ceramic ring seal can be connected to metal isolation rings by a plurality of pins. The hot gas face of the ring seal can be coated with a thermal insulating material. In another embodiment, the ring seal can be made of metal, but it can be operatively associated with a ceramic heat shield. The metal ring seal can carry the mechanical loads imposed during engine operation, and the heat shield can carry the thermal loads. By minimizing the amount of ring seal cooling, the ring seal systems according to aspects of the invention can result in improved engine performance and emissions.

Abstract: A turbine shaft may be used to remove a heat load from pliant bearings without requiring the use of a process fluid for cooling the turbine shaft. The turbine shaft comprises a heat conductive sleeve disposed between an outer surface of a tie rod shaft and an inner surface of a bearing journal; the heat conductive sleeve having a sleeve inner surface separated from a sleeve outer surface by a sleeve thickness; the heat conductive sleeve having a first end separated from a second end longitudinally about a center axis; the sleeve outer surface being in physical contact with the inner surface of the bearing journal; and the heat conductive sleeve having a thermal conductivity that is greater than a thermal conductivity of the bearing journal.

Abstract: The invention relates to a method and a device for cooling thermally stressed regions in a turbo machine which has a live-steam feed line (9), an inflow region (17), a housing (2) and an exhaust-steam region (7), a flow medium flowing through the turbo machine (1) and leaving in the exhaust-steam region (7) during operation, part of the flow medium from the live-steam feed line (9) being passed to the exhaust-steam region (7) and cooled by means of a heat exchanger (8) before entry into the turbo machine (1) and entering the turbo machine (1) via the inflow region (17), thermally stressed regions that are located in the inflow region (17) being cooled by the f low medium that has been cooled in this way.

Abstract: The device and method are used for heating a central section of a rotor mounted for rotation in a gas turbine engine.

Abstract: A method for assembling a rotor assembly for a gas turbine engine is provided. The engine includes an engine casing, a plurality of rotor blades, and at least one turbine shroud assembly. The method includes mounting a plurality of case segments together circumferentially to form the casing around the plurality of rotor blades and the at least one turbine shroud assembly, wherein each of the case segments includes at least two mounting flanges and a channel defined therebetween. The method also includes applying a thermal barrier coating to an inner surface of the channel and at least a portion of each mounting flange to facilitate maintaining axisymmetric running tip clearances between the plurality of rotor blades and the least one turbine shroud assembly during a cruise operation. The thermal barrier coating also facilitates controlling axisymmetric running tip clearances during a take-off operation such that an exhaust gas temperature and a specific fuel consumption is reduced.

Abstract: A cooling fluid pump includes a casing having a cylindrical pump chamber inside and an outer surface, the pump chamber having an inner surface, an impeller mounted rotatably inside the pump chamber and having a number of pump vanes, the impeller further having an axial end, a fluid path defined around the impeller in the pump chamber so that a fluid flows through the fluid path upon rotation of the impeller, a discharge port formed in the casing for discharging the fluid inside the fluid path and a suction port formed in the casing for suctioning the fluid into the fluid path upon rotation of the impeller, a protrusion formed on a portion of the inner surface of the pump chamber opposed to the axial end of the impeller, thereby separating the fluid discharged from the discharge port and the fluid suctioned from the suction port as well as pressuring the fluid flowing in the fluid path, and a heat receiving portion formed on a part of the outer surface of the casing overlapping the protrusion.

Abstract: Embodiments of the invention relate to a turbine vane having a fail safe cooling system. According to embodiments of the invention, the vane can have multiple concentric layers of radial cooling holes extending about the vane; each layer being fluidly connected to the adjacent layer or layers. Such fluid communication can occur through one or more plenums in the vane or in the shrouds bounding the radial ends of the vane. Coolant can initially be supplied to the innermost layer of cooling holes. From there, the coolant can sequentially progress through successive outer layers. Between two adjacent layers, the coolant can flow in opposite directions. Not only does such a system provide needed cooling to the vane, but the multilayer redundant cooling system can avoid or delay catastrophic failures that can occur if the vane surface is damaged, such as by impact.

Abstract: A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section, and an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section. The annular heat shield member includes a plurality of slots formed on a surface of the heat shield member in a radial direction of the annular heat shield member.