Abstract: A holding device for holding a cooling fan comprising: a duct having a hollow in which a cooling fan is to be fitted; a stopper portion which keeps one operative end of the cooling fan from further moving to hold the cooling fan at a fitting position; and a plurality of elastic wall segments formed in a cooling fan insertion end of a wall of the duct; wherein each of some of the plurality of elastic wall segments is formed with a locking claw for keeping the other operative end of the cooling fan from moving. With this construction, the cooling fan 31 can be more surely mounted in a duct. Consequently, vibration reduction effect and sound reduction effect with respect to the cooling fan is improved.

Abstract: A vacuum pump including a tempering component arrangeable between the suction side flange of the pump and the connection flange of a recipient and having a tempering element.

Abstract: A rotor of a thermally loaded turbomachine, in particular of a compressor or a gas turbine, is mounted such that it can rotate about a rotor axis and is concentrically surrounded by a hot-gas duct or cooling-air duct. A significant improvement to the ability of the rotor to withstand thermal loads is achieved, with little increased outlay in terms of materials, by virtue of the fact that the rotor comprises a rotor core made of a first material, that the rotor core is concentrically surrounded by shielding rings made of a second material, which shield the rotor core from the temperature in the hot-gas duct or cooling-air duct, the second material having a higher heat resistance than the first material, and that the shielding rings are cohesively joined to the rotor core.

Abstract: A forced air induction system for use with a powered vehicle is disclosed as including a centrifugal supercharger supported by the vehicle's engine and a recirculating induction coolant system that cools the supercharger and the compressed induction fluid provided by the supercharger. The induction coolant system operates by providing coolant to the supercharger and to an intercooler of the forced air induction system. The supercharger case includes internal passageways for cooling the transmission and compressor. The forced air induction system further includes spacers and radiant heat shields for rejecting heat transferred conductively and radiantly from the engine.

Abstract: Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.

Abstract: A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component.

Abstract: Described is a cooled gas turbine guide blade for a gas turbine, with a hollow blade profile which comprises an onflow edge onto which a working medium is capable of flowing, and with, for guiding a cooling medium, an onflow edge duct running inside the blade profile along the onflow edge. Furthemore, to the use of such a gas turbine guide blade and to a method for operating a gas turbine with an abovementioned gas turbine guide blade. In order to provide a gas turbine guide blade with an increased lifetime by means of the invention, it is proposed that, in the onflow edge duct, an electrical heating element be provided, which extends approximately completely over the entire length of the onflow edge duct and through which a heating current flows, before the operation of the gas turbine, for the preheating of the gas turbine guide blade.

Abstract: The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal PC representative of tip clearance, sensing a second pressure PB substantially unaffected by tip clearance, forming an actual ratio of the acquired pressure and the sensed pressure, determining an error E having an actual component and a desired component, the actual component being a function of the actual ratio; and commanding a clearance control system to reduce the error.

Abstract: A closed loop inner shroud assembly for a gas turbine. The shroud assembly may include a shroud body, a cover plate, an inlet though the cover plate to the shroud body, a serpentine passageway through the shroud body, and an outlet from the shroud body to the cover plate.

Abstract: A system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to the at least one wheelspace area. The system may also include a plurality of bypass plugs, wherein each of the plurality of bypass plugs is insertable into a bypass chamber opening on each of the plurality of bypass chambers.

Abstract: Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.

Abstract: A drain pump is provided that reduces the operating noise when the head is low. The drain pump has a pump casing, and an impeller. The pump casing has a drain inlet for sucking in drain water at a lower end part and a drain outlet for discharging drain water at a side part. The impeller has a shaft part extending in a vertical direction inside the pump casing, a main blade disposed on the outer circumferential side of the shaft part, an auxiliary blade disposed on the lower side of the main blade, and a disc shaped dish part disposed between the main blade and the auxiliary blade. The dish part has an annular partition part extending upward from the outer circumferential edge part of the main blade, which is disposed at a position lower than the upper end part of the partition part.

Abstract: A hot gas duct, such as a combustion casing in a gas turbine engine, includes a duct splitter held within the hot gas duct in at least three, preferably four, locations spaced around a peripheral edge of the duct splitter. At least one, preferably two, of the holding locations each comprise a generally cylindrical mounting that projects through a wall of the hot gas duct to engage an edge portion of the duct splitter by means of a slot formed in a circular face of the mounting. Mutually contacting surfaces of the slot and the duct splitter comprise hard face coatings to combat wear due to vibration and differential thermal expansion and contraction. The mountings have cooling holes that penetrate the mounting, so that coolant can flow through the mountings and into the interior of the hot gas duct to cool the mountings and the hard face coatings.

Abstract: A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a circumferential temperature distribution about the inner surface of the shroud ring, and impinging cooling air on to an outer surface of the shroud ring. More cooling air is impinged onto regions which correspond to the high temperature regions on the shroud ring than to regions corresponding to the lower temperature regions of the shroud ring.

Abstract: A cooling system includes a moving rotor system which in turn includes: a disk on which a plurality of heat conducting structures are distributed, the heat conducting structures having a cross section optimized for maximum surface area to footprint area; the heat conducting structures having a shape to optimize the heat transfer coefficient between the structures moving through the ambient fluid; and a mechanism for generating a mass fluid flow over the conducting structures so that the heat conducting structures are persistently cooled.

Abstract: A heat transfer system is provided for a turbine engine of the type including an annular inlet cowling. The heat transfer system includes at least one heat pipe disposed in contact with an interior of the casing. The heat pipe is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe and into the inlet cowling.

Abstract: A wall structure for a gas turbine engine combustor has an inner wall and an outer wall defining a duct, the wall structure including an outer wall having a radial step and an inner wall overlapping the radial step, a duct being defined between the inner and outer walls for the passage of cooling air; the wall structure being characterised in that the inner wall has a local thickening opposing the radial step. The velocity of cooling air through the duct is maintained and heat transfer subsequently improved.

Abstract: The exhaust-gas turbine comprises a turbine casing, a shaft rotatably mounted in a bearing housing, a turbine wheel arranged on the shaft, and a heat-protection wall, the heat-protection wall defining with the turbine casing an inflow passage leading to the turbine wheel. The heat-protection wall has two seatings, the first seating resting on the bearing housing and the second seating resting on the turbine casing. If the heat-protection wall becomes hot, the two seatings are pressed against the bearing housing and the turbine casing. The turbine casing is pressed outward in the radial direction. Centering of the heat-protection wall and thus also of the turbine casing is ensured by the radially inner seating of the heat-protection wall.

Abstract: The exhaust-gas turbine comprises a turbine casing, a shaft rotatably mounted in a bearing housing, a turbine wheel arranged on the shaft, and a heat-protection wall, the heat-protection wall defining with the turbine casing an inflow passage leading to the turbine wheel. The heat-protection wall has two seatings, the first seating resting on the bearing housing and the second seating resting on the turbine casing. If the heat-protection wall becomes hot, the two seatings are pressed against the bearing housing and the turbine casing. The turbine casing is pressed outward in the radial direction. Centering of the heat-protection wall and thus also of the turbine casing is ensured by the radially inner seating of the heat-protection wall.

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: The present invention relates to a turbine stator of a gas turbine engine comprising a turbine casing (9), a turbine shroud ring (13) and a shroud ring support (11) connecting the shroud ring (13) to the casing (9). The stator is one wherein the support (11) is provided with an element that forms a heat shield positioned on the turbine side. This solution makes it possible to reduce the take-up of play during transient operating phases.

Abstract: A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the casing in order to modify the temperature thereof. A tubular air manifold is disposed around the air flow duct(s). There are also disposed an air feed tube to supply the tubular air manifold with air and an air pipe opening in the tubular air manifold and opening out into the air flow duct(s). The air pipe is provided with a balancing diaphragm for balancing the air flowing through the pipe.

Abstract: A super steam turbine (100) into which high-temperature steam of 650° C. or more is introduced is provided with an inner steam pipe (120) which is disposed through an inner casing (110) and an outer casing (111), an outer steam pipe (130) which is welded to the outer casing (111) and disposed outside of the inner steam pipe (120) along the inner steam pipe (120) with a prescribed space therebetween, and a radiation heat shielding pipe (140) which is disposed along the inner steam pipe (120) between the inner steam pipe (120) and the outer steam pipe (130) to face a welded portion of at least the outer steam pipe (130), wherein cooling steam (160) is flown between the inner steam pipe (120) and the outer steam pipe (130), respective component parts are made of a suitable heat-resisting steel having prescribed chemical composition ranges.

Abstract: A coolable segment for a turbomachine such as a combustion turbine, which turbomachine is operated with a hot fluid. The segment comprises a cooling wall extending in an axial direction and in a circumferential direction orthogonal to the axial direction; a hot fluid surface to be exposed to the hot fluid. Between the wall and the surface a cooling structure is arranged which is permeable to cooling fluid and provides cooling surfaces for cooling by heat transmission through radiation. The cooling structure comprises either a netting, in particular a wire netting or a porous material.

Abstract: A heat dissipation device includes two heat sinks (30) mounted on two electronic components (16) which is mounted within a server (10), two fans (40) mounted on a mounting plate (14) of the server facing the heat sinks for blowing cooling air to the heat sinks, and a fan duct (20). The fan duct includes a top plate (24), a pair of side plates (22) extending from opposite sides of the top plate, a pair of partition walls (26) extending from a middle portion of the top plate, and a stop wall (264) connected between ends of the partition walls. The fan duct is hermetically connected to the mounting plate and the bottom plate thereby cooperatively forming a sealed passage therebetween. The passage includes an inlet (28) adjacent the fans and two separate outlets (29) between the side plates and the partition walls respectively for accommodating the heat sinks therein.

Abstract: A seal arrangement, for example a brush seal 8? in a gas turbine engine, includes thermal matching means for matching the rates of response of a supporting ring 14?, 16? of the seal, and of a rotatable component 4 with which the seal cooperates, to thermal changes in the environment of the seal induced by changes in operating conditions. The thermal matching means may comprise a slugging mass 24 and/or thermal insulation 28. Alternatively, or in addition, the region 24 of the housing at which the seal 8? is mounted may be made from a relatively low thermal expansion material. These measures reduce the rate of expansion and contraction of the seal 8? as the temperature in the engine varies so as to match more closely the rate of expansion and contraction of a rotatable component with which the seal cooperates.

Abstract: A turbine shroud assembly asymmetrical cooling element such as a shroud segment or a baffle includes an arcuate panel. The panel has a plurality of cooling apertures extending through the panel and an axially extending midline of the panel parallel to an axis of rotation of the arcuate panel. A symmetric portion of the cooling apertures have a symmetrical density of aperture inlets that is symmetric with respect to the axially extending midline. An asymmetric portion of the cooling apertures have an asymmetrical density of aperture inlets that is asymmetric with respect to the axially extending midline. One exemplary cooling element includes a high density area of the cooling apertures in the asymmetric portion having a higher density of aperture inlets than in the symmetric portion. A low density area of the cooling apertures in the asymmetric portion has a lower density of aperture inlets than in the symmetric portion of the cooling apertures.

Abstract: A casing arrangement (20) for surrounding a rotary component (16) of a gas turbine engine (10) especially a turbine is disclosed. The arrangement (20) comprises an annular casing member (22A) surrounding a bladed rotary section, such as a turbine stage. An array of gas path liner segments are suspended from the casing at a nominal clearance gap form the tips of the rotary blades. Running clearance is determined by expansion and contraction of the casing which, in turn, is controlled by a supply of heat transfer fluid passed through heat transfer holes in the casing. The casing arrangement described includes a passive pressure bleed effective during engine deceleration to reduce a pressure differential driving the fluid flow in order to avoid too rapid contraction of the casing as a result of overcooling.

Abstract: A gas turbine engine vane assembly provides double impingement cooling of a vane platform. An impingement structure disposed adjacent the vane platform defines at least first and second plenums in fluid flow communication, respectively defined in part by the vane platform. The vane platform has first and second surfaces defined within the first and second plenums, and which are cooled by successive impingement of secondary cooling air flow through the impingement structure.

Abstract: A housing including an outer casing provided with bearer hooks for stator rings and sealing rings. The hooks are discontinuous angularly and joined to a casing by tenon and mortise assemblies. The hooks and the casing may therefore be made in different materials, the hook material having good resistance to heating and the other material lending itself better to machining and forming. Ventilation, clearance piloting and heat protection are facilitated.

Abstract: A steam turbine that can effectively operate with the steam at the higher temperatures, while maintaining the strength of turbine constituent components despite the high steam temperature of the steam is provided. The steam turbine includes a casing, a rotor, a plurality of turbine stages, a steam pass, a nozzle box, and a cover plate. The rotor is rotatably installed in the casing. The turbine stages are disposed in the turbine, at least one of the turbine stages including a turbine nozzle and including a moving blade that is fixed to the rotor. The steam pass includes the turbine stages. The nozzle box is placed in a space between the casing and the rotor for providing a heated steam into the steam pass. The cover plate is arranged along an outer surface of the nozzle box.

Abstract: An arrangement for cooling or heating of a flange bolt for turbines comprises one or more boreholes, that extend through the bolt, and inlet and outlet pipes that are connected to each end of the borehole. A cooling or heating medium such as air, steam or any other fluid flows through an inlet pipe into and through the borehole thereby cooling or heating the bolt, and exits from the borehole via an outlet pipe. The cooling or heating arrangement enables direct cooling or heating of the bolt itself and ensures stable bolting forces throughout the operation of the turbine. The flange bolts with this arrangement may be applied to gas turbines or steam turbines operated at elevated steam temperatures and pressures.

Abstract: The present invention concerns a wind power installation comprising a ring generator and a housing having a heat-conducting housing portion in the region of the ring generator. Previously known structures suffer from the disadvantage that mechanical vibrations and oscillations of the generator can be perceived as acoustic disturbance and interference. The object of the present invention is very substantially to eliminate that disadvantage. A wind power installation comprising a ring generator and a pod housing, which surrounds the ring generator, of the wind power installation, wherein the pod housing has a heat-conducting housing portion in the region of the ring generator and a predetermined spacing is provided between the outside periphery of the ring generator and the heat-dissipating housing portion.

Abstract: An axial flow fan of high efficiency and low noise level is provided. The fan includes a motor, an impeller having a plurality of blades around a hub fitted to the motor, and a fan casing having an air inlet on one side and an air outlet on the other, wherein a radial position with a maximum setting angle in a blade section, and a radial position with a contour of a leading edge portion in a fluid flowing direction forming a projecting apex in the flowing direction are located between 60% and 80% of the outside diameter of the impeller.

Abstract: An apparatus for cooling of electronic components of the present invention are provided with a heatsink and a blower with an electric drive. The heatsink comprises a base and heat exchanging means. The electric drive comprises a stator and a rotor with an axle; the stator is rigidly built-in to the heatsink. The blower comprises a radial type magnetized impeller as the rotor. The base provides thermal contact with the electronic component and the heat exchanging means. The base is comprised of at least two layers composite material thereof including at least one layer of electrically insulating material and at least one layer of thermally and electrically conductive material that including the stator.

Abstract: In an exhaust gas turbocharger including a compressor wheel, the compressor wheel is cooled by at least one nozzle which is arranged in close axial proximity to the axis of rotation of the compressor wheel for spraying the backside of the compressor wheel near the center thereof with coolant whereby the coolant, utilizing the centrifugal forces of the rotating compressor wheel, is completely distributed over the entire wheel back surfaces.

Abstract: A power system includes a device for extracting energy from a hot gas stream to power a driveshaft. An evaporative duplex counterheat exchanger is disposed in flow communication with the energy extracting device. The duplex exchanger includes a first heat exchanger having a first main flow channel, and a counterheat channel joined in flow communication therewith. A second heat exchanger includes a second main flow channel adjacent the counterheat channel. And, an evaporative fluid is injected into the counterheat channel to evaporatively cool the flow through both main flow channels.

Abstract: An airfoil. The airfoil may include a first number of cooling holes and a second number of cooling holes positioned within the airfoil. The first number of cooling holes and the second number of cooling holes each may include a turbulated section and a non-turbulated section.

Abstract: A turbine shroud assembly includes forward and aft hangers, an axisymmetric plenum assembly, ceramic shroud segments, ceramic spacers, and forward and aft rope seals. The plenum assembly supplies impingement cooling to the shroud and the hangers. The impingement cooling to the forward and aft hangers is controlled independently to improve blade tip clearance. The rope seals are radially inward from the hangers and reduce cooling flow leakage. The turbine shroud assembly can operate in a higher temperature environment using less cooling flow than the prior art.

Abstract: An attachment apparatus and method for interlocking attachment of a scraper blade with a drive shaft of a scraped surface heat exchanger includes a blade having dual attachment beams and a central locking member, and at least one pin having dual fingers each for interlocking with a respective attachment beam.

Abstract: A jacket ring for the low-pressure-turbine region of a gas turbine, having a plurality of lined-up segments which are arranged between a moving blade ring with a shroud band and the casing of the gas turbine, which carry a run-in lining and which hold guide blades in a positive-locking manner, wherein each segment comprises a hot-gas-side seal carrier and a casing-side securing element, the seal carrier and the securing element are at the greatest possible distance from one another and only have common contact points which are as small as possible, and the securing element is axially supported directly on the casing of the gas turbine.

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

Abstract: A computer cabinet includes a top panel and at least one side panel connected to the top panel and a fan assembly. The fan assembly includes a fan and a fan housing. The fan housing has a top half and bottom half. The top half and the bottom half form an internal cavity. An air inlet is located within one of the top and bottom halves. The fan is located within the internal cavity and directs air from the air inlet towards an open end of the housing.

Abstract: A rotary compressor machine, such as a combustion air charger, includes a rotatable shaft (18) having at least one compressor wheel (20,22) thereon and disposed within a housing (12,14). A donut-shaped heat exchanger (36) is located within the housing (12,14) between the compressor wheel (22) and an outlet (32) from the housing and has radially inner and outer peripheries (40,42). The outer periphery (40) defines an inlet for the heat exchanger (36) for gas discharged by the compressor wheel (20). The heat exchanger is provided with radially inner and outer flow paths defined by tubes (92) and includes a combined manifold and tank (44) which is secured and sealed to a header plate (88) receiving the tubes (92). The combined manifold and tank (44) includes first, second and third axially spaced walls (96,98,100) with each having a central opening (110,112,114).

Abstract: A turbo-molecular pump of high safety and reliability was presented, so that if an abnormal condition should develop on the rotor side, it will not lead to any damage to the stationary portions such as the stator or pump casing to cause loss of vacuum in a vacuum processing system. The turbo-molecular pump includes a rotor; a stator assembly surrounding the rotor; and a casing portion surrounding the stator assembly, wherein at least a partial clearance is formed between the stator assembly and the casing portion, so that, when an abnormal torque is applied from the rotor to the stator assembly, direct impact transmission is prevented from the stator assembly to the casing portion.

Abstract: A turbine shroud cooling system used in a gas turbine engine for controlling tip clearance between a turbine shroud assembly and turbine rotor blades comprises a cooling air passage for selectively directing a cooling air flow between components to be cooled and a turbine shroud support assembly for controlling the tip clearance and then later re-directing the cooling air flow to cool a downstream turbine component.

Abstract: A hydrodynamic component with at least two rotating impellers which form a working chamber for a working circuit. A closed circuit coupled to the inlet to the working chamber and to the outlet from the working chamber. The closed circuit is pressure tight. Pressure control for the closed circuit.

Abstract: A turbine wall includes a metal substrate having front and back surfaces. A thermal barrier coating is bonded atop the front surface. A network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.

Abstract: A cooled turbine shroud segment for a gas turbine engine, having an axially extending shroud ring segment with an inner surface, an outer surface, an upstream flange and a downstream flange. The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate is disposed on the outer surface of the shroud ring between the upstream flange and the downstream flange, with an impingement plenum defined between the impingement plate and the outer surface. Axially extending cooling bores in the ring segment extend between the impingement plenum and an outlet. A trough adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.

Abstract: A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direction of the gas turbine. A concave portion is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.