Abstract: A rotary machine includes an impeller. The impeller includes a discoid disk that rotates about an axis line, blades disposed circumferentially at intervals on a surface of the disk facing one side in a direction of the axial line and that form a flow path therebetween that extends radially outward from one side in the direction of the axial line, and a cover that covers the blades from a radially outer side. The rotary machine further includes a casing that covers the impeller from the radially outer side and forms a gap between the casing and an outer surface of the cover; a seal portion provided in the gap; and a lid member.

Abstract: A turbine ring assembly includes ring sectors forming a turbine ring, and a ring support structure having two annular flanges, each ring sector having a portion forming an annular base with an inner face defining the inside face of the turbine ring and an outer face from which there project at least two tabs, the tabs being retained between the two annular flanges. Each tab of the ring sectors includes a projecting portion on its face situated facing one of the two annular flanges, this projecting portion co-operating with a housing present in the annular flange. Each tab of the ring sectors includes an opening in which there is received a portion of a retention element secured to the annular flange situated facing the tab. The retention element is made of a material having a thermal expansion coefficient that is greater than that of the material of the ring sectors.

Abstract: A fluid-flow machine includes: a main flow path boundary and at least one row of relatively rotating blades with a gap existing between blade ends and the main flow path boundary. At least one secondary flow duct having one opening each is provided in the main flow path boundary at ends spaced apart in the flow direction, such that the secondary flow duct is connected to the main flow path via the two openings. The structural assembly has at least one support component and at least one insertion component. The support component includes a recess extending in the circumferential direction that receives the at least one insertion component such that the support component surrounds the at least one insertion component largely on its sides not facing the main flow path, and where the insertion component completely surrounds or forms at least one secondary flow duct.

Abstract: A turbine bucket tip clearance control system includes a rotor assembly having a rotor supporting a plurality of axially spaced wheels, each wheel mounting an annular row of buckets, the annular row of buckets on at least one of the plurality of axially-spaced wheels having a radially outer tip shroud provided with at least one seal tooth. A stator assembly includes a radially inwardly facing, axially-stepped surface, formed with radially inner and outer seal surfaces connected by a shoulder. The stator assembly and rotor assembly are moveable axially relative to each other, enabling selective positioning of the at least one seal tooth radially opposite one of the radially inner and outer seal surfaces to thereby selectively alter a clearance gap between the at least one seal tooth and the radially inward facing axially-stepped surface.

Abstract: A structural assembly for a fluid-flow machine includes a main flow path boundary a row of relatively rotating blades with a gap existing between the blade ends and the main flow path boundary. A secondary flow duct is connected to the main flow path via two openings. A structural assembly has at least one support component and at least one insertion component. A structure extending in the circumferential direction and receiving or holding at least one insertion component along the circumference is provided in the support component. Each insertion component forms with at least some of its faces at least part of the main flow path boundary. Each secondary flow duct is jointly limited along at least part of its course by faces of at least two components of the structural assembly.

Abstract: A system (e.g., a chromatography system) includes a rotor, a microfluidic device, a rotor driver, a clamping mechanism, and control electronics. The rotor defines a plurality of first fluid-conveying features. The micro fluidic device defines one or more channels and a plurality of second fluid-conveying features, in fluid communication with the one or more channels. The rotor driver is coupled to the rotor and is configured to rotate the rotor, relative to the microfluidic device, between a first position and a second position such that, in each of the positions, at least one of the first fluid-conveying features cooperates with at least one of the one or more channels to provide for fluid communication therebetween. The clamping mechanism is operable to provide a sealing force to establish a fluid-tight seal between the rotor and the microfluidic device.

Abstract: A method is provided for adjusting a position of a blade ring relative to a rotor in a gas turbine engine. An outer casing surrounds the blade ring and the blade ring surrounds the rotor. The method comprises: determining an amount of vertical movement needed to reposition the blade ring relative to the rotor so that the blade ring is at a desired position relative to the rotor; providing at least one torque pin assembly comprising a torque pin and a variable thickness defining structure; determining a change in the thickness of the variable thickness defining structure so as to effect the necessary vertical movement of the blade ring; changing the thickness of the variable thickness defining structure; and coupling the at least one torque pin assembly to the outer casing such that at least one torque pin engages the blade ring. A gas turbine engine is provided having structure for adjusting a position of a blade ring relative to a rotor.

Abstract: A turbomachine seal assembly includes a base member, a rocker arm pivotally mounted to the base member, and a seal element fixedly mounted to the rocker arm. The seal element is configured and disposed to selectively shift relative to the base member.

Abstract: A hydraulic machine including an impeller which rotates with respect to a fixed structure and about an axis of rotation by a forced flow of water passing through it and at least one device for limiting water leaks is positioned between the impeller and the fixed structure so as to define an operating clearance between the impeller and the fixed structure and including at least one member that can be deformed or moved, while the impeller is rotating and being fed with water, in a redial direction with respect to the axis of rotation of the impeller.

Abstract: A bearing system for a rotor in rotating machines, such as compressors, pumps, turbines, expanders, has points of bearing and sealing for the rotor each being in the form of a combined bearing and sealing formed by a stator situated within a rotating machine house and surrounding the rotor. The stator is formed with a bore, whereby an annular clearance is created between stator and rotor, and the bore is having sectional area gradually increasing in the direction of larger pressure within the rotating machine.

Abstract: A machine includes a rotor supported to rotate about a rotational axis and an actuator arranged to act on the rotor and control a position of the rotor about the rotational axis. A bladed turbomachine wheel is coupled to the rotor and has blade tips that pass closely to an adjacent, non-rotating surface. A sensor is adjacent to the turbomachine wheel and arranged to sense the blade tips and output a position signal representative of the position of blade tips relative to the sensor. A controller is coupled to the sensor and the actuator and is adapted to receive the position signal from the sensor and generate and send a control signal to the actuator to control the position of the rotor based on the position signal from the sensor.

Abstract: A leaf seal assembly (20) for providing a seal between a first member and a second member (10), the leaf seal assembly comprising a plurality of leaf elements (22) and a first substantially planar cover plate (24a), the leaf elements being arranged in a pack, with a first edge of each leaf element being adjacent to the first cover plate, wherein each leaf element comprises a first shoulder (30a) in the first edge, the first shoulder being arranged so as to form a first gap (28a) between the first edge of each leaf element and the first cover plate over a portion of the first edge.

Abstract: A tilting-segment radial bearing for a single-shaft turbomachine is provided, having a support ring, a tilting-segment mounting and a tilting segment, which in the installed state of the tilting-segment radial bearing is supported on the support ring such as to be seated on top and be radially displaceable by the tilting-segment mounting. The mounting has a preload device, by means of which the tilting segment is preloaded in the direction toward the shaft of the single-shaft turbomachine when the operating rotational speed of the single-shaft turbomachine is above a predetermined tilting-segment preload rotational speed, such that the tilting segment can be radially moved without preload when the operating rotational speed of the single-shaft turbomachine is below the tilting-segment preload rotational speed.

Abstract: An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.

Abstract: A passage wall section of an annular flow passage of an axial turbomachine is provided. A guide ring has a first toothing arrangement which is in contact with a second toothing arrangement arranged on a sidewall of a circumferential groove which accommodates the guide ring, wherein for axial displacement of the displaceable guide ring, the guide ring is rotatable in a circumferential direction.

Abstract: An oil cooled runner, for a rotary seal between an engine case and a shaft rotationally mounted to the case, includes an annular runner ring having a platform with a radially outer seal engagement surface and a radially inner surface, and an oil distributor having a radially inner portion in communication with a source of liquid lubricant and an outer lubricant casting cone with a rim disposed radially inwardly from the inner surface of the platform.

Abstract: The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor (12) having rotor blades (10) of a turbomachine (14), especially a gas turbine, and a casing (18) that surrounds at least sections thereof and comprises at least two segments (16a-d), the clearance control system having at least one adjusting device (20), which can be coupled to at least one segment (16a-d) of the casing (18), and by means of which the at least one segment (16a-d) can be moved radially in relation to a rotational axis (D) of the rotor (12) for adjusting the running clearance (L), wherein each segment (16a-d) of the casing (18) is coupled to at least three adjusting devices (20) of the clearance control system. The invention also relates to a turbomachine (14), especially a gas turbine, as well as to a method for adjusting a running clearance (L).

Abstract: An article of manufacture has a body formed in part of a first metal alloy and in part of a second metal alloy, the second metal alloy having a thermal coefficient of expansion that is less than the thermal coefficient of expansion of the first metal alloy. A BOAS segment for a gas turbine engine is disclosed wherein the formation of cracks due to thermal mechanical fatigue in the body of the disclosed BOAS segment is minimized, if not eliminated, through a unique construction of the disclosed BOAS segment, whether original equipment manufacture or a repaired blade outer air seal. A method for manufacture of a BOAS segment and a method for modifying a BOAS segment are disclosed.

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 method and system for adjusting the clearance between a stator member and the tip of a rotor member in a rotor apparatus. The system comprises a position adjustment mechanism for adjusting the radial position of the stator member to any one of at least two and preferably three different radial positions. The system further comprises a variable pressure chamber having a first pressure state and a second pressure state. The system is arranged for applying a force for maintaining the stator member in either one of said at least two radial positions when said chamber is in said first pressure state and for allowing the position adjustment mechanism to adjust the radial position of the stator member between said at least two positions when the chamber is in said second pressure state.

Abstract: A compressor stator vane and rotor blade tip clearance control assembly in which a plurality of stator vane segments each with vanes extending inward are connected to an annular sync ring through eccentric cranks so that circumferential movement of the sync ring will produce radial displacement of the vane segments and control the clearance between the blade tips. An actuator piston is rigidly fixed to the sync ring and forms an actuator chamber with stationary actuator housing. Bleed off pressure from one of the compressor stages is used to move the actuator piston, which moves the sync ring to radially displace the vane segments.

Abstract: A steam turbine casing position adjusting apparatus capable of employing a compact low-resolution actuator is provided. A steam turbine casing position adjusting apparatus 40 includes turbine casings 21 and 37, a rotor 23, and actuators 14 and 15 that move the turbine casings 21 and 37 in the axial direction. The actuators 14 and 15 are disposed radially outside outer peripheries forming the turbine casings 21 and 37.

Abstract: The present invention relates to a centrifugal pump, a shaft sleeve and a stationary seal member for a static seal used in connection with a dynamic sealing of a centrifugal pump. The invention relates to a static seal the clearance of which may be adjusted while the pump is running. Especially the invention discusses the novel structure of such a static seal.

Abstract: The invention relates to a pump turbine system comprising a turbine with a turbine impeller as well as a turbine spiral housing; and a pump with a pump impeller as well as a pump spiral housing; an electrical machine which is in drive communication with the shaft or can be brought into such communication; a hydraulic short circuit can be produced between turbine and pump.

Abstract: The present invention relates to a centrifugal pump, a shaft sleeve and a stationary seal member for a static seal used in connection with a dynamic sealing of a centrifugal pump. The invention relates to a static seal the clearance of which may be adjusted while the pump is running. Especially the invention discusses the novel structure of such a static seal.

Abstract: A turbine stage for a turbine engine includes a bladed wheel rotatable inside a sectorized ring of composite material carried by a casing. Each ring sector has a downstream circumferential rim held to bear radially against an annular tab that is engaged radially in an annular groove of the downstream circumferential rim of the ring with axial clearance, when cold, that is designed to be reduced to zero in operation when hot, and to enable the annular tab of the casing to be clamped axially in leaktight manner in the annular groove of the ring sector.

Abstract: A fan assembly for a computing device is disclosed. The device can include an impeller having a number of blades and a motor for turning the blades. The motor can turn the blades via a magnetic interaction between the impeller and the motor. A thrust bearing can be used to control a position of the impeller relative to the motor. In particular, the impeller can be configured to rotate around an axis and the thrust bearing can be used to control movement of the impeller in a direction aligned with the axis. In one embodiment, the impeller can be configured to generate aerodynamic forces, such as lift, and the parameters associated with the thrust bearing can be selected to counteract the aerodynamic forces so that the impeller remains within a desired positional range relative to the motor.

Abstract: A turbine inter-stage seal with active clearance control. The inner diameter of the stator vane includes a seal support structure with a plurality of segmented seal supports each movable by an actuator located on the vane outer diameter with a plunger or push rod extending through the hollow portion of the vanes. A segmented seal arrangement, such as segmented brush seals, are secured to the underside of the seal support segments and form a complete annular seal for the inter-stage between adjacent rotor disks. A proximity probe or microwave sensor detects the brush seal clearance, and a controller regulates the brush seal clearance.

Abstract: A gas turbine comprises forward and aft rows of rotatable blades coupled to a disc/rotor assembly, a row of stationary vanes positioned between the forward and aft rows of rotatable blades, and rotatable sealing apparatus. Each of the stationary vanes comprises an inner diameter platform having first sealing structure. The rotatable sealing apparatus comprises seal housing apparatus coupled to the disc/rotor assembly and has second sealing structure adapted to engage with the first sealing structure.

Abstract: A stacked pump arrangement for mixed-media flow includes a first, self-priming, centrifugal pump with a volute having an inlet and an outlet and a second straight centrifugal pump mounted to an upper portion of the first centrifugal pump, the second straight centrifugal pump also having a volute with an inlet and an outlet. A transition chamber is connected, at one end, to the first centrifugal pump volute outlet and is connected, at another end, to the second straight centrifugal pump volute inlet.

Abstract: A stacked pump arrangement for mixed-media flow includes a first, self-priming, centrifugal pump with a volute having an inlet and an outlet and a second straight centrifugal pump mounted to an upper portion of the first centrifugal pump, the second straight centrifugal pump also having a volute with an inlet and an outlet. A transition chamber is connected, at one end, to the first centrifugal pump volute outlet and is connected, at another end, to the second straight centrifugal pump volute inlet.

Abstract: An impeller fixing mechanism is provided in a centrifugal pump for immobilizing the impeller, relative to the pump shaft and drive shaft of the pump, while effecting repairs to the pump, thereby eliminating much of the labor-intensive need for realigning the pump shaft and drive shaft and assuring accurate positioning of the impeller relative to the pump shaft. A method for effecting repairs of centrifugal pumps employs use of the impeller fixing mechanism of the invention to immobilize the impeller relative to the pump shaft, thereby facilitating the repair.

Abstract: Apparatus and method of operating a centrifugal compressor and active control system includes a centrifugal compressor with compressor blades mounted on an impeller, an annular cavity bounded in part by a shroud adjacent to the blades, and an active control system for controlling a clearance between the shroud and the blades by controlling a cavity pressure in the cavity. An electronic controller for controlling a control pressure valve for pressurizing using a source of compressor discharge pressure air and depressurizing the cavity respectively may open and close the valves using pulse width modulation. Pressure and clearance sensors positioned for measuring the cavity pressure the blade tip clearance respectively in signal supply communication with the electronic controller may be used. The shroud may be supported by radially spaced apart annular radially outer and inner supports connected to a casing by a bolted joint bounding the cavity.

Abstract: The present application provides a variable steam seal system for use with a steam turbine. The variable steam seal system may include a seal steam header, a first pressure section, a first pressure seal positioned about the first pressure section, and a flow path through the first pressure seal and extending to the seal steam header. The first pressure seal may include a moveable seal packing ring for varying the flow path through the first pressure seal to the seal steam header.

Abstract: Apparatus and method of operating a centrifugal compressor and active control system includes a centrifugal compressor with compressor blades mounted on an impeller, an annular cavity bounded in part by a shroud adjacent to the blades, and an active control system for controlling a clearance between the shroud and the blades by controlling a cavity pressure in the cavity. An electronic controller for controlling a control pressure valve for pressurizing using a source of compressor discharge pressure air and depressurizing the cavity respectively may open and close the valves using pulse width modulation. Pressure and clearance sensors positioned for measuring the cavity pressure the blade tip clearance respectively in signal supply communication with the electronic controller may be used. The shroud may be supported by radially spaced apart annular radially outer and inner supports connected to a casing by a bolted joint bounding the cavity.

Abstract: A centrifugal pump or compressor with a labyrinth seal that produces an axial thrust balance when the impeller shifts in the axial direction due to fluid pressure forces acting on the impeller, and a process for reducing the axial thrust imbalance by regulating the fluid leakage from a front pressure cavity of the pump. The impeller includes a front face that forms part of a front pressure cavity in which fluid pressure acts that produces a thrust imbalance on the impeller. A labyrinth seal with a plurality of teeth is formed between the housing and the front face of the impeller near the impeller inlet. The teeth form gaps with lands formed on the impeller face, where the lands are slanted and stepped such that axial displacement of the impeller changes the gap space to regulate the fluid pressure acting in the front cavity. A self regulating fluid pressure is developed within the front cavity to produce a balancing force against the impeller.

Abstract: A method and seal assembly for sealing a rotary machine including a rotary component and a stationary component is provided. The method includes providing a plurality of flexible leaf plates in an opening defined between a pair of spaced walls that include an adjustable front wall and an adjustable back wall that is opposed to the front wall. The method also includes adjusting a width of the opening by axially adjusting at least one of the front and back walls with respect to a central rotational axis of the rotary component.

Abstract: A seal for restricting leakage of a fluid through a gap disposed between rotating and stationary components concentrically aligned within a gas turbine engine comprises a sealing member and a land. The sealing member is positioned on either the rotating or stationary component of the gas turbine engine and closes a gap between the rotating member and the stationary member. The land is positioned opposite the sealing member on either the rotating or stationary component of the gas turbine engine such that a clearance height is provided between the sealing member and the land. In one embodiment, the land is geometrically shaped according to expected changes in the gap and relative axial position of the sealing member and land during operation of the gas turbine engine. The sealing member and the land are positioned with respect to each other so that the clearance height is maintained approximately constant during operation of the gas turbine engine.

Abstract: An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.

Abstract: An actuation pressure control system effects actuation of adjustable seal segments between stationary and rotating turbomachinery members. At least one actuator is coupled with each of the adjustable seal segments and controls a position of the seal segments, respectively. A pressure system is disposed within the turbomachinery that measures or estimates ambient pressure representing an actuator back pressure acting against the actuator. A pressure regulator via a controller pressurizes the actuator to a level sufficient for a desired seal operation and controls actuator pressure based on the actuator back pressure.

Abstract: A system and method for extending seal life and for reducing leakage flow in a turbine engine is directed to an interface defined between a stationary component and a rotating component. A seal, which can be a flexible seal such as a brush seal, can be operatively attached to the stationary component. The rotating component has a first region at a first radius relative to the axis of rotation that transitions into a second region at a second, larger radius relative to the axis of rotation. In one embodiment, the rotating component can be selectively axially moved between a first position and a second position. In the first position, the seal is disposed over the first region so as to define a clearance. In the second position, the seal is disposed over the second region so as to decrease the size of the clearance.

Abstract: The present invention relates to a centrifugal pump, a shaft sleeve and a stationary seal member for a static seal used in connection with a dynamic sealing of a centrifugal pump. The invention relates to a static seal the clearance of which may be adjusted while the pump is running. Especially the invention discusses the novel structure of such a static seal.

Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.

Abstract: Disclosed herein is a rotor assembly for a steam turbine including a stacked rotor section having rotor plates. The rotor plates include a main body portion having a plate shape and a first axial face and a second axial face opposite to the first axial face. The rotor plates also include an airfoil base surface at an outer radial edge of the main body portion. The rotor plates further include buckets which extend radially outward from the airfoil base surface. And the rotor plates yet further include a seal disposed to prevent steam exposure to the first and second axial faces.

Abstract: A recentering device for a rotor shaft for recentering a rotor shaft relative to an axis X of a stator structure in the event of decoupling caused by excessive imbalance. The shaft, in normal operating conditions, lies on the axis X and is radially supported by a bearing support disposed in a bore of the axis X in the stator structure. The bearing support has an outside diameter smaller than the diameter of the bore, to enable the bearing support to orbit about the axis X in the event of decoupling. The bearing support is connected to the stator structure by radially fusible elements. The recentering device recenters the bearing support after decoupling.

Abstract: A turbine engine stator assembly in juxtaposition across a radial gap with a rotary blading assembly includes a radially movable shroud and a gap control member made of at least one shape memory alloy (SMA). The SMA is selected and preconditioned to deform pre-selected amounts to change the radial length of the gap during engine operation responsive to temperature about the SMA. A fluid flow means delivers fluid to the SMA at pre-selected temperatures during engine operation.

Abstract: A turbomachine comprising at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the shaft, one of the bearings being capable of giving way when an unbalance occurs in the rotary assembly, at least one segment of the shaft being covered in a covering which comprises at least one piece of fabric impregnated with resin and which is for coming into contact with a surrounding portion of the turbomachine when the unbalance occurs in order to protect the first shaft and ensure that there is no risk of the first shaft rupturing. The turbomachine is intended to be used mainly in the field of aviation, and more particularly as an airplane turbojet.

Abstract: A turbomachine including at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the first shaft, one of the bearings being capable of giving way when an unbalance occurs in the first rotary assembly. The turbomachine further comprising brake arrangement for braking the first shaft when the unbalance occurs, and bond arrangement acting at the end of braking to bond a portion of the first shaft to a surrounding portion of the turbomachine. The turbomachine is intended to be used mainly in the field of aviation, and more particularly as an airplane turbojet.

Abstract: A method of assembling sectored elements of an annular stator of a high-pressure turbine of a turbomachine about a longitudinal axis of said turbine, in which method an angular distribution pattern is defined for distributing elements of the stator over a predetermined angular sector, said pattern being defined so as to prevent inter-sector zones of stator elements being in radial alignment, said zones being defined between two adjacent sectors of the same stator element, and so as to repeat said distribution pattern around the entire circumference of the stator.

Abstract: A cooling fan comprising a fan housing and a plurality of blades rotatably disposed within a conduit through the fan housing. Each of the plurality of blades extends radially outward from a hub to a tip. The radial gap between the tips of the blades and the conduit defines a tip clearance. The cooling fan further comprises an tip clearance reduction system operable to control the tip clearance.