Abstract: Provided is a gas turbine plant that enables active clearance control for ensuring tip clearance of first-stage turbine rotor blades required during start-up and for achieving the minimum tip clearance during load operation. In a gas turbine plant including a cooler in an air system used for cooling second-stage turbine stator blades, a first-stage segmented ring and a second-stage segmented ring that oppose tips of first-stage turbine rotor blades and second-stage turbine rotor blades are supported by the same blade ring member, and a cooling-air for the second-stage turbine stator blades forms a cooling air flow cooling the blade ring, to control thermal expansion of the blade ring and to control the clearance with respect to the tips.

Abstract: A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an outer shell delimiting the combustor and splittable at a parting plane; a plenum enclosing the outer shell; a rotor; a turbine vane carrier encompassing the rotor; a plurality of stator vanes disposed on the vane carrier, and at least two sealing segments forming a ring, each of the at least two sealing segments having an inner edge and a head and a foot section and being movably mounted on the inner edge by the foot section to the outer shell and by the head section to the turbine vane carrier so as to mechanically connect the combustor to the turbine vane carrier.

Abstract: The invention relates to an assembly including a turbine disk (200) for a gas turbine engine and a bearing-supporting journal (100), the turbine disk (200) comprising a radial annular fastening flange (250) secured to a radial annular part (150) of the journal (100) by bolts (200), the bolts (200) passing successively through fastening bores (120, 220) formed in the radial annular fastening flange (250) of the turbine disk (200) and in the radial annular part (150) of the journal (100), which assembly is characterized in that the radial annular part (150) of the journal (100) comprises air circulation openings (110), the openings (110) being formed between the fastening bores (120) of the journal (100).

Abstract: A fan structure includes a base having a receiving section; a sleeve defining a receiving space therein, and having a shaft hole communicating with the receiving space and an engaging end for engaging with the receiving section of the base; a bearing having an axial bore and received in the sleeve; and an insulating rack externally fitted around the sleeve and having a holding section for holding at least one silicon steel plate set therein, which is spaced from the sleeve by at least one first space. With these arrangements, heat produced by the silicon steel plate set during fan operation is isolated by the first space from directly damaging the bearing. Further, since the bearing is stably held in place in the sleeve without the need of using any bonding material, the fan structure can have extended service life and reduced manufacturing cost.

Abstract: Assemblies for cooling an aft bearing assembly mounted to a rotor are provided. An assembly includes a static aft bearing structure configured to surround the aft bearing assembly and including a cylindrical section defining a cavity for disposal of the aft bearing assembly, a plurality of hollow struts extending from the static aft bearing structure, each hollow strut including an outer radial end configured to receive a gas from an air source and to provide a pathway for the gas to flow into the cavity, and a center-body cap disposed over an end of the static aft bearing structure, the center-body cap including a rim configured to create a low pressure region at an interface between the static aft bearing structure and the center-body cap, wherein the low pressure region has a pressure that is lower than a pressure within the cavity.

Abstract: A gas-turbine inlet-air cooling system includes: a spray device configured to spray cooling water into inlet air entered into a compressor of a gas turbine facility to thereby cool the inlet air; and a cooling-water feed system configured to supply the cooling water to the spray device. The cooling-water feed system including: at least one tank configured to reserve the cooling water; a plurality of pipes connected to the tank independently of each other and configured to feed the cooling water to the spray device; and pumps installed for the pipes, respectively.

Abstract: A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.

Abstract: A blade outer air seal (BOAS) of a gas turbine engine has a segmented support ring to support a segmented turbine shroud. The support ring has a cooling air distribution system which includes a plurality of inlet cavities extending axially and inwardly to communicate with an inner cooling air passage within the respective support segments. The inlet cavities each are formed with two recesses defined in respective adjacent two support segments.

Abstract: The present invention relates to an oil-free turbocharger assembly using an airfoil bearing that may be useful in high speed conditions. The assembly can be cooled easily. A heat-proof coating can also be easily applied to the turbo charger's rotating shaft. In one embodiment, an oil-free turbocharger assembly has a constant distance between a journal portion and a rotating shaft so that the mass of the rotating body can be minimized and the rotating body assembly can have a small moment of inertia. The turbocharger in some embodiments of the invention may be cooled by a refrigerant which improves cooling efficiency. Each part of the rotating body assembly in some embodiments may be individually treated with a heat-proof process so that productivity can be improved.

Abstract: In an industrial pump, a bearing provided in a pump main body rotatably supports both end sides of a rotating shaft to which an impeller is attached. A shaft seal apparatus is arranged in adjacent to the bearing. The shaft seal apparatus is cooled by a cooling water introduced from an external portion. A shaft seal case is fitted to an inner peripheral surface of a bracket accommodating the shaft seal apparatus in accordance with a shrink fitting. A cooling water is circulated in a boundary portion between the bracket and the shaft seal case. It is omitted a work for closing an opening portion of a cooling means for circulating the cooling water by welding.

Abstract: A gas turbine including exhaust chamber defined by a cylindrical casing wall and a bearing case that supports a bearing part of a rotor in the casing wall, struts provided at equal intervals in circumferential direction of the bearing case and extending in tangential direction of the bearing case to couple the casing wall and the bearing case, a diffuser unit having an outer diffuser at the inner periphery of the casing wall and an inner diffuser at the outer periphery of the bearing case, a cooling chamber in which the outer diffuser and the inner diffuser are coupled by a strut cover, led to a portion between the casing wall and the outer diffuser, a portion between the bearing case and the inner diffuser, and the insides of the strut cover, and a partition wall that covers the outer periphery of the bearing case.

Abstract: A refractory metal core for use in casting a turbine engine part has a main portion and a plurality of tabs extending from the main portion. An end portion having a first edge which joins together the plurality of tabs and a second edge, opposed to the first edge, located internally of an exterior boundary of the cast part may be provided.

Abstract: There is provided an exhaust section of a gas turbine and a gas turbine that can cool a strut and the periphery of a bearing without decreasing the efficiency of the gas turbine. A structure of an exhaust section of a gas turbine has: a casing in which a gas path part is formed; a bearing part that rotatably supports moving blades of a turbine section; a strut that extends inwardly from the casing and supports the bearing part; an opening formed in the casing; and a cooling flow channel that extends from the opening toward the bearing part along the strut to guide air at a lower temperature than an exhaust gas flowing in the gas path part to the gas path part and opens into the gas path part at a position downstream of a last-stage moving blade of the turbine section.

Abstract: A turbocharger, especially a turbocharger for a motor vehicle, has a turbine housing and a bearing housing. The turbine housing and the bearing housing are fitted with a common cooling device. The turbine housing includes a flange for attaching to an exhaust gas manifold. The flange is formed with a coolant inlet, a coolant outlet, and an oil supply pipe.

Abstract: The present application thus provides for a turbine component cooling system. The component cooling system may include a turbine component, an airflow passing adjacent to the turbine component, and a seal positioned adjacent to the turbine component. The seal may include a number of apertures so as to allow the airflow to pass therethrough.

Abstract: A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided.

Abstract: A high temperature centrifugal pump includes non-linear fluid flow paths between the pump housing and seal housing to reduce fluid flow therebetween. In another aspect, the invention provides a drive shaft of variable diameter to compensate for different amounts of thermal expansion to maintain a more consistent gap profile between the drive shaft and thermal insulators or other components positioned around the drive shaft. In yet another aspect, a tube heat exchanger may be placed in fluid communication with the seal housing to re-circulate and cool the fluid therethrough.

Abstract: A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide from a carbon dioxide source and a method of using a stream of carbon dioxide to cool hot gas path components. The turbine power generating system includes a compressor, a combustor, a turbine, a generator, and at least one shaft linking the compressor and turbine and generator together such that mechanical energy produced from the turbine is used to drive the compressor and the generator. Carbon dioxide that is sequestered from the exhaust of the turbine may be stored and injected back into the turbine to cool hot gas path components of the turbine.

Abstract: A running-gap control system of an aircraft gas turbine with a core engine including a turbine whose blade rows have a running gap 13 to the turbine casing 12, with the turbine casing 12 being surrounded by a core-engine ventilation compartment 15 enclosed by a fairing 2 of the core engine, with the fairing 2 forming an inner wall of a bypass duct 1. Air from the bypass duct 1 can be introduced via at least one inlet nozzle 5 into a cooling-air distributor 7 by a control system 6, 10, 11 and the air is subsequently returned to the bypass flow 3.

Abstract: Disclosed is a solution to automate a seal oil float trap by-pass for a hydrogen cooled generator. An automated by-pass system is coupled to an existing manual by-pass system for a float trap for a hydrogen cooled generator. The automated by-pass system includes at least one solenoid valve and a controller that controls opening and closing of the solenoid valve. The automated by-pass system can also include manual valves, orifices and limit switches. The controller activates the solenoid valve to allow the seal oil to drain. The controller can also provide a notification alarm that the hydrogen cooled generator is being purged.

Abstract: In a gas turbine plant and a gas turbine power generator plant, as a device of reducing the heat transfer from the gas turbine to the compressor, for instance, an air flow path for circulating part of compressed air from the compressor toward the gas turbine is formed between the gas turbine and the compressor. With the air flow path, which is a heat transfer reducing device, the heat conducted from the gas turbine to the compressor can be reduced by cooling or interception, and accordingly the temperature on the compressor side does not rise high, making it possible to prevent the performance of the compressor from deteriorating.

Abstract: A cooling system has a drive motor which is to be cooled by a cooling medium. A cooling medium circuit conducts the cooling medium. A hydrodynamic machine comprising a working space can be filled with a working medium. The working medium is the cooling medium, and the hydrodynamic machine has a seal which is cooled and/or lubricated by the cooling medium. A cooling medium pump for circulating the cooling medium is in the cooling medium circuit. A pick-off is in the cooling medium circuit in the region of the cooling medium pump. Via the pick-off, the cooling medium is branched out of the cooling medium circuit. The branched-off cooling medium is conducted directly through or past the seal to cool and/or lubricate the latter, and the cooling medium which is conducted through or past the seal is supplied to the cooling medium circuit upstream or downstream of the working space.

Abstract: A fluid flow machine includes a housing with a connecting piece for a working fluid on an intake side, and a pressure side. At least one impeller is mounted on a shaft, which is held in the housing by radial and axial bearings, and a cooling arrangement is provided for at least one bearing. A revolving part of the axial bearing is designed as a cooling fluid transportation device, wherein a suction connection leads to the intake side of the impeller.

Abstract: A bearing device of a gas turbine power generation equipment provides damping vibration of a shaft and lubricates and cools the bearing main body. The bearing devices have sleeves provided on the outer circumference sides of the bearing main bodies and bearing housings holding the respective sleeves via O-rings while each forming an annular clearance passage between each of the outer circumferences of the sleeves and a corresponding one of the bearing housings. The bearing housing has a feed-water hole communicating with the clearance passage and adapted to feed water thereto. The sleeve has a lead water hole communicating with the clearance passage and is adapted to lead water to the bearing main body, and a discharge hole which communicates with the clearance passage and is adapted to discharge water therefrom.

Abstract: A steam turbine with at least one magnetic bearing for the shaft is provided, a metal paneling being attached in the area of a magnetic bearing. The metal paneling consists of metal rings insulated from one another. Further, cooling air ducts are provided in the area of the magnetic bearing.

Abstract: A steam turbine having an exhaust-steam casing for directing an exhaust-steam mass flow, a shaft bearing for mounting a turbine shaft, and at least two bearing struts, by means of which the shaft bearing is fastened to the exhaust-steam casing, is characterized according to the invention in that each of the at least two bearing struts has a cooling cavity arranged in the respective bearing strut for directing a coolant, and the cooling cavities of the at least two bearing struts are connected in a fluidically conductive manner via a closed-off connecting cavity in the region of the shaft bearing.

Abstract: A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage.

Abstract: The temperature rise of a wheel space between a high-pressure turbine and a low-pressure turbine is suppressed. Cooling air is led from outside a casing 17 to a wheel space via a low-pressure turbine initial stage stator blade 5 and a diaphragm 11. An upstream side space seal portion 41 is adapted to restrict and divide the upstream side space into an outer circumferential portion 25 and an inner circumferential portion 27 and to allow cooling air to the upstream side space outer circumferential portion 27 to blow out into the upstream side space outer circumferential portion 25. Also, a downstream side space seal portion 42 is adapted to restrict and divide the downstream side space into an outer circumferential portion 26 and an inner circumferential portion 28 and to allow cooling air to blow out into the downstream side space outer circumferential portion 26.

Abstract: A system for cooling a gas turbine engine control component comprises a control component, at least one duct in fluid communication with the component and the atmosphere, and a valve assembly located with the duct for modulating airflow to the component. A method for cooling a gas turbine engine control component comprises the steps of: a) providing a system for cooling the component, the system comprising at least one duct in fluid communication with the component and the atmosphere and a valve assembly located with the duct for modulating airflow to the component; b) exposing the system to a first condition where cooling of the component is required; c) opening the valve assembly in response to the first condition; d) exposing the system to a second condition where cooling of the component is not required; and e) closing the valve assembly in response to the second condition.

Abstract: A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.

Abstract: A propeller is mounted aft of the rear rotor supporting bearing of a gas turbine. The propeller is driven either by the rotor shaft or by the exhaust gases flowing through the exhaust frame of the turbine. The rotating propeller blows cooling air on the rear bearing. The cooling air can then be circulated through the exhaust frame to cool the exhaust frame as well.

Abstract: An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) is adjoined to said second seal (8) and respectively loaded with the turbine cooling air (B?, C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal (8) is guided and separated from components (10) and flowing-off air masses by a flow-guiding means (16) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.

Abstract: Means for cooling a bearing assembly supporting a rotor stage of a gas turbine engine after engine shutdown. The engine comprises a combustion section, a compressor for the delivery of air to the combustion section, and a bearing assembly supporting a rotor stage. The means for cooling a bearing assembly comprises a means operable to generate a signal representative of turbine duct temperature immediately prior to engine shutdown, a means for determining the duration for cooling after engine shutdown as a function of the signal representative of turbine duct temperature, and the compressor operable as a cooling means to deliver cooling air to the rotor stage after engine shutdown. Thereby the amount of heat conducted to the bearing assembly is limited such that the temperature of the bearing assembly is limited to below a predetermined temperature.

Abstract: The invention relates to an inter-turbine casing (40) for a turbofan (2), comprising an outer ring (44), an inner ring (54), and an intermediate ring (52) between the inner ring and the outer ring, the inner (54) and intermediate (52) rings having respective openings (540, 520) for the passage of cooling air. The casing is distinguished in that it comprises at least one sealing device (80), arranged between the outer ring (44) and the intermediate ring (52), with a base (82), provided with at least one orifice (90) for the passage of cooling air, and a peripheral skirt (84) which is able to be compressed and expanded elastically, the base (82) bearing against the outer ring (44) and the peripheral skirt (84) bearing against the intermediate ring (52).

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may be shortened relative to conventional clips and may include a cooling channel proximate to a point of attachment to the combustor basket.

Abstract: A compact assembly of a liquefied natural gas, (LNG)-mixed hydrocarbon refrigerants, (MR), arranged on a single shaft assembly for individual expanding the LNG and MR streams including sealing means for separating and isolating the processing of a LNG stream and MR stream at a pre-selected location intermediate the ends of the single shaft assembly. The liquefied natural gas, LNG, stream is coupled to a hydraulic turbine expander mounted on the single shaft assembly adjacent a first end thereof. The hydraulic turbine expander has two phase expansion capabilities. The hydraulic expander is enclosed in a vessel mounted between one end of the sealing means and beyond the first end of the shaft assembly for isolating the expander. The LNG stream and the vessel are arranged to traverse a pre-selected path within the vessel. The compact assembly may include a induction motor means mounted to the shaft assembly adjacent the sealing means.

Abstract: A vertical centrifugal pump having a support bearing arranged above the pump and including an axial bearing (22) and a radial bearing (23). A housing (24) encasing the support bearing (22, 23) is directly connected to the flow-carrying housing (25) of the centrifugal pump. Lubrication, and optionally cooling, of the support bearing (22, 23) are performed by the pumped medium, which is conveyed to the support bearing (22, 23) through a connection leading from the pressure zone (28) of the flow-carrying housing and is discharged into the suction zone (29) of the pump, and a pump shaft seal (31) is disposed on the opposite side of the support bearing (22, 23) from the flow-carrying housing of the centrifugal pump.

Abstract: A turbomachine for low-temperature applications has a housing, a rotor shaft disposed in the housing, an impeller disposed on one shaft end of the rotor shaft, to which a cold gas is applied, and an electrical machine integrated into the housing. During operation of the turbomachine, a cold zone (K) forms within the housing, in the impeller-side end, and a warm zone (W) forms at the end facing away from the impeller. The housing has at least two compressed gas connectors for a compressed gas, of which one connector is disposed in the cold zone (K), and the other is disposed in the warm zone (W). A control device establishes the flow-through direction for the compressed gas based on temperatures in the cold and warm zones, and controls valve devices on the compressed gas connectors accordingly.

Abstract: A high-speed universal motor running at over 10,000 or even over 20,000 rpm includes a non-rubbing water repellent sleeve that protects the bearings from moisture damage. Rather than having a sliding contact seal that can quickly wear out under such high speeds, the sleeve is made of material having a low solid surface energy so that the seal material itself repels waters on its own. TEFLON is the preferred material, which is relatively soft, so to prevent the compressibility of the seal from affecting the axial positioning of parts on the motor shaft, the seal is installed such that the seal does not contribute to the critically precise positioning of the shaft and the parts mounted to it. In some embodiments, for example, the relatively soft seal simply overlies a much stiffer, accurately machined metal spacer.

Abstract: A device for lubricating a component in a turbomachine, in particular a shaft bearing in a turbojet, the device comprising an annular support part defining a lubrication chamber around the component, an annular cover mounted in sealed manner on the part and including a lubricating oil inlet, and an annular channel for passing a flow of pressurizing and cooling air, which channel is formed between the part and the cover, and communicates with ducts in the support part and an annular enclosure formed in the cover for passing the pressurizing and cooling air.

Abstract: A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the seal, and exhaust the fluids through a gap between adjacent turbine vanes. The seal may include an elongated cooling channel for channeling cooling fluids from a supply to an exhaust channel at a first end. The cooling system may remove heat from the turbine vane shroud, the seal, and other related components, thereby reducing the likelihood of premature failure.

Abstract: The object of the present invention is to provide: high-reliability and long-life CO2 refrigerant compressor-use bearings that uses bearing materials high in wear resistance and in baking resistance, and; such a compressor, air conditioner, refrigerator, and hot-water supply machine that each employ these bearings.

Abstract: An air cooled bearing comprising means for imparting a swirl component to the cooling air flowing toward the bearing. By imparting a swirl component to the cooling air the amount of work imparted on the cooling air by the rotating cage and rolling elements of the bearing can be reduced and in some cases substantially eliminated.

Abstract: A CO2 compressor for an air conditioner of a motor vehicle is suggested having a sealing device, assigned to the driveshaft of the CO2 compressor, which is implemented as a sliding ring. The CO2 compressor features a lubrication device, in which the sealing device is supplied a lubricant flow effected by centrifugal forces.

Abstract: A sanitary centrifugal pump with a hygienic mechanical seal flushing system. The pump has a housing with a pumping chamber defined therein. An impeller is at least partially contained in the housing and is connected to a shaft for rotation. The rotation of the impeller creates a first liquid flow path through the pumping chamber between the inlet port and the outlet port, and the first liquid flow path creates a high pressure area in the pumping chamber. The pump includes additional seal flushing passages by which liquid is delivered to the seal cavity from the pumping chamber and returned back to the pumping chamber, to cool and flush at least a portion of the mechanical seal in the seal cavity.

Abstract: A hot gas path assembly, suitable for use in the hot gas path of a gas turbine, has as a hot gas duct wall an impact-cooled gas-impermeable element and a transpiration-cooled gas permeable element. The gas-permeable element is a run-on covering for the sealing tip, and the gas-impermeable element is a blade foot of a turbine blade. Coolant is led in series through an impact-cooling element to cool the gas-impermeable element, and through the gas-permeable element for transpiration cooling and, if appropriate, also cools the sealing tip. Coolant thus is utilized particularly efficiently. Subdividing walls are arranged for the lateral subdivision of the coolant path, particularly in the circumferential direction, into segments. Because of the subdivision, in the event of damage to the gas-permeable element in one segment, the other segments remain essentially uninfluenced. Redundant cooling orifices may ensure coolant flow even when flow resistance in a transpiration-cooled element rises.

Abstract: A gas turbine stator including at least a first injector providing a passage for a main cooling air stream into a pressurized chamber. An evacuation mechanism discharges air coming from an internal labyrinth gland of a first cavity towards a lower-pressure second cavity. A second injector evacuates the air contained in the second cavity towards a main duct. The stator further includes a third injector designed to generate an overpressure close to the internal labyrinth gland in the pressurized chamber.

Abstract: A compact rotary compressor unit within internal intercooling includes a rotary shaft (10) with at least one compressor wheel (14,16) mounted thereon for rotation therewith. The compressor wheel (14,16) has an inlet end (18) of relatively small diameter and a radial discharge end (20) of relatively large diameter. A nominally donut-shaped intercooling heat exchanger (42) is centered about the shaft (10) to receive compressed air from the compressor wheel and cool the same. Both the compressor wheel (14,16) and the heat exchanger (42) are confined in a housing (28).

Abstract: A system and method of cooling a steam turbine having internal moving components to a predetermined temperature by controlling a flow of nitrogen through the turbine, thus decreasing the downtime associated with maintaining the turbine. This provides a more efficient and cost effective method of operating a power plant.

Abstract: A coolant pump for an engine includes a pump case main body and a pump drive shaft journaled therein. The pump drive shaft has a plurality of blades mounted thereon and is rotatable about a pump drive shaft axis. The coolant pump also includes a partition member and a lid. The partition member and the pump case main body define a pump chamber configured to house the blades. The partition member also defines a pump chamber inlet port. A fluid inlet chamber is defined by the partition member and the lid. The fluid inlet chamber provides fluid communication between a fluid inlet port and the pump chamber inlet port.