Abstract: Gas turbine unit having an axis parallel to the main gas flow, the gas turbine unit comprising: a blade having a tip; a stator heat shield having an inner surface facing the blade tip; wherein the inner surface of the stator heat shield and the blade tip define a variable clearance depending on the applied thermal condition; wherein the blade tip is configured to have a cylindrical shape along the axial direction in a hot running condition starting from a conical shape along the axial direction in a cold starting condition.

Abstract: Systems and methods are provided that use a tip clearance control apparatus comprising a mechanical iris, where the tip clearance control apparatus controls a distance between a tip of a blade and a ring of abradable material positioned in an adjustable opening of the mechanical iris.

Abstract: A suction chamber for use in a surface pumping system includes a central housing that is substantially cylindrical and has a motor end and a pump end opposite the motor end. The suction chamber includes a motor-end plate bolted to motor end of the central housing and a pump-end plate bolted to the pump end of the central housing. The suction chamber also includes an inlet branch connected to the central housing. A method for assembling a non-welded suction chamber is also disclosed.

Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.

Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section plane defined by an axial direction and a radial direction of the ring, a portion forming an annular base with, in the radial direction, an inner face and an outer face from which a first and a second attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the attachment tabs of each ring sector are maintained. The turbine ring assembly includes a first and a second annular flanges removably fastened to the first radial clamp, the second annular flange including a bearing shroud protruding upstream in the axial direction and having a radial bearing in contact with the central shroud.

Abstract: A turbine ring assembly including ring sections forming a turbine ring and a ring support structure, each ring section having, along a section plane defined by an axial direction and a radial direction of the ring, a part forming an annular base with, in the radial direction, an inner face and an outer face, from which a first and a second fastening lug project, the structure including a central shroud, from which a first and a second radial clamp project, between which the fastening lugs of each ring section are maintained. It includes a first and a second annular flange detachably fixed to the first radial clamp, the second annular flange including a support shroud projecting upstream in the axial direction and having a radial support in contact with the central shroud.

Abstract: An assembly is disclosed for adjusting the radial position of one or more blade tracks radially encasing the blades of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a plurality of blade track carriers, an annular control ring, an actuator, and a plurality of blade tracks. The blade tracks have a radially inner surface that defines a flowpath boundary of the turbine stage. The blade tracks are carried by the blade track carriers, which are engaged with the annular control ring. Actuation of the actuator moves the control ring in an axial dimension and this movement is translated into an adjustment of the radial position of the blade track.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

Abstract: A gas turbine engine includes a turbine section including at least one turbine rotor having at least one blade. A blade outer air seal is positioned radially outward of a radially outer tip of the at least one turbine blade. The blade outer air seal has a forward hook and an aft hook. The forward hook is supported on a forward retainer and the aft hook is supported on an aft hook retainer. The aft hook retainer provides structure to prevent rotation of the blade outer air seal relative to the aft hook retainer. There is an interference fit between the aft hook retainer and the forward retainer. A load path is provided from a static structure through the aft hook retainer to the forward retainer.

Abstract: The invention relates to a method and apparatus for assembling nozzles 31 between buckets 41,42 of a turbine, particularly a gas turbine, in which a temporary fixing of the nozzles 31 to the buckets 41,42 during the assembly is provided.

Abstract: An adjustable blade outer air seal apparatus includes a case that extends circumferentially around an axis, a support ring non-rigidly mounted to the case on spring connections radially inwards of the case, whereby the support ring floats with respect to the case, and at least one blade outer air seal segment that is radially adjustable relative to the support ring.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver is coupled to a closed form refrigeration system having an evaporator, a compressor, a condenser, an expansion valve, and a refrigerant contained therein. The thermal driver is cooled by the refrigeration system, and the rate of cooling causes expansion and contraction of the thermal driver that is translated by linkages into axially forward and aft motion of the shroud.

Abstract: A centrifugal impeller shroud assembly has a dynamically moveable impeller shroud for encasing a rotatable centrifugal impeller and resolving misalignment between the impeller shroud and the rotatable centrifugal impeller. The assembly comprises a static casing, an impeller shroud, a shroud arm, and a thermal member. The shroud arm is coupled between the casing and the impeller shroud. The thermal member is coupled to the impeller shroud and has a coefficient of thermal expansion (CTE) lower than the CTE of the shroud. The shroud arm comprises a flexible portion configured to flex responsive to a differential pressure across the shroud arm.

Abstract: A method and apparatus according to which an output of a power generation system is controlled. In one embodiment, the power generation system includes a turbine and a feedback control system. The turbine includes a rotor to which a first portion of a power fluid is communicated, the first portion imparting torque to the rotor; a shaft to which the rotor is connected; a shroud extending circumferentially about the rotor and the shaft; and a bypass gap between the rotor and the shroud, through which a second portion of the power fluid is communicated. The feedback control system axially displaces the shroud relative to the rotor, thereby adjusting the size of the bypass gap and, consequently, the ratio of the first portion relative to the second portion.

Abstract: A pump assembly has at least one electronics receiving space (54; 54; 54?). The electronics receiving space (54; 54; 54?) includes at least one defined ventilation opening (40; 40; 40?). The ventilation opening (40; 40; 40?), at an outer side of the electronics receiving space (54; 54; 54?), runs out into an air duct (41; 41; 46; 46; 48, 48?) which is led along at least one condensation surface (60; 60; 60?).

Abstract: A fan assembly, and associated methods are shown that may include tapering configurations in a nozzle assembly. Configurations are shown that are optimized for thrust. Examples of assemblies and methods are shown that include sound attenuating materials and jagged edges to reduce noise. Configurations are shown that provide a substantially constant or increasing air velocity. Configurations are also shown that provide a static pressure of 120 percent or less of a given dynamic pressure.

Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

Abstract: A drain pump for an appliance includes a single, self-starting, single-phase synchronous motor and a pump chamber having an inlet and first and second outlets. The first outlet is a drain outlet and the second outlet is a recirculation outlet. An impeller is disposed within the pump chamber and is selectively and bi-directionally driven by the single-phase synchronous motor. Rotation of the impeller in a first direction directs fluid from the inlet toward the drain outlet and away from the recirculation outlet. Rotation of the impeller in the second direction directs the fluid from the inlet toward the recirculation outlet and away from the drain outlet.

Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.

Abstract: A method for operating a stationary gas turbine at partial load, having at least one compressor, at least one expansion turbine and a combustion chamber provided with at least one burner, which gas turbine further includes a hydraulic gap adjuster, wherein the method has the following steps: operating the gas turbine at partial load; operating the a hydraulic gap adjuster; during the operation of the hydraulic gap adjuster, increasing the fuel supply to the burner while increasing the temperature of the combustion gases which are guided to the expansion turbine.

Abstract: A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

Abstract: A clearance control assembly for providing clearance control between a blade outer air seal and an airfoil tip of a gas turbine engine includes an outer case, a first blade outer air seal carrier, a blade outer air seal, an actuator, a load-applying member, and a lever. The first blade outer air seal carrier is positioned radially inward of the outer case. The blade outer air seal is positioned radially inward of and mounted to the blade outer air seal carrier. The load-applying member is positioned to be acted upon by the actuator during operation of the actuator. The lever is connected to the case and is operably in contact with the load-applying member and the first blade outer air seal carrier.

Abstract: A turbomachine blade clearance system can include an actuator having an anchor portion for fixation to an interior surface of a turbomachine housing and an actuating portion for actuating movement relative to the anchor portion. A turbomachine blade seal can be operatively connected to the actuating portion of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade.

Abstract: A system includes a stator assembly including at least one stator airfoil. The system also includes a rotor assembly including at least one rotor airfoil configured to rotate about an axis. The system also includes an actuator coupled to the stator assembly and configured to actuate the stator assembly in an axial direction relative to the rotor assembly, creating an axial movement such that a clearance between the at least one rotor airfoil and the stator assembly varies based on an axial position of the stator assembly.

Abstract: A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

Abstract: An active clearance control system for a gas turbine engine includes an air seal segment and a puller engageable with the air seal segment.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.

Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.

Abstract: An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position.

Abstract: Provided is a rotating fluid machine capable of holding down a decrease rate of a circumferential velocity of a leakage fluid in an interspatial flow passage and thereby controlling an unstable fluid force. A steam turbine includes: an interspatial flow passage 15 formed between an outer circumferential surface of a rotor blade cover 6 and an inner circumferential surface of a grooved section 14 in a casing 1; annular sealing fins 17A to 17D spatially arranged in a direction of a rotor axis, at a side of the rotor blade cover 6 in the interspatial flow passage 15; and a friction enhancement portion (more specifically, rough surfaces 19A to 19E) disposed over the whole circumference on the side of the rotor blade cover 6 in the interspatial flow passage 15.

Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

Abstract: A movable vane control system is disclosed for use with a gas turbine engine having a turbine axis of rotation. The system includes a plurality of rotatable turbine vanes in a gas flow path within a turbine case of the gas turbine engine. A first vane position sensor having a first distance sensor is configured to sense the distance between the first distance sensor and a surface portion of a first of said plurality of vanes or a first movable target connected to the first vane. Additionally, the first distance sensor, the first vane surface portion, the first movable target, or a combination thereof is configured to provide a variable distance between the first distance sensor and the first vane surface portion or first movable target that varies as a function of a position of the first vane.

Abstract: A blade outer air seal (BOAS) assembly is provided. The BOAS assembly may comprise an outer case, a first support arm, a second support arm, a control rod, a blade outer air seal (BOAS), and a unison ring. The unison ring may be located radially inward of the outer case and in mechanical communication with the control rod. The BOAS may be configured to expand or contract in response to a rotation of the control rod. The first support arm may be fixed to the outer case. The second support arm may be fixed to the outer case. The control rod may be coupled to the first support arm and the second support arm, wherein the control rod may be configured to rotate about a control rod axis. The BOAS may comprise a first segment and a second segment.

Abstract: An apparatus for extending the operational flow rate range of a turbine is described herein. Two or more removable sleeves may be used to change the cross-sectional area of a turbine. Each removable sleeve may define or eliminate the stator gap between a stator blade tip and an inner wall of the removable sleeve and a rotor gap between a rotor blade tip and an inner wall of the removable sleeve. A movable sleeve may be disposed in the turbine and may move between a first position and a second position in response to changes in the pressure differential across the turbine. The movable sleeve may define or eliminate a stator gap between a stator blade tip and the inner conical surface of the sleeve or a hub of the turbine and a rotor gap between a rotor blade tip and the inner conical surface of the sleeve.

Abstract: Systems and devices configured to reduce thermal design clearances (e.g., between stationary nozzles connected to the inner casing and rotor buckets connected to the rotor) in turbines by actively controlling casing movements and/or locations during turbine operation are disclosed. In one embodiment, a clearance management system includes: a first inner casing support arm shaped to connect to an inner casing of a turbine and extend through an outer casing of the turbine; a seal system disposed about the first inner casing support arm and configured to connect to the outer casing; and a set of actuators disposed on a turbine foundation of the turbine and connected to the first inner casing support arm, the set of actuators located external to the outer casing and configured to adjust a position of the inner casing relative to the outer casing via manipulation of the first inner casing support arm.

Abstract: A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

Abstract: An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint. The flow discourager is connected to the first module and extends to be received in a notch in the second module. The flow discourager acts to direct an ingestion gas flow away from the joint between the first module and the second module.

Abstract: A method controlling a clearance between tips of blades of a turbine rotor of a gas turbine aircraft engine and a ring-shaped turbine shroud of a housing surrounding the blades, the method including: controlling flow and/or temperature of air directed toward the housing according to an estimate of the clearance, the estimate of the clearance is determined upon start-up of the aircraft engine, according to a temperature measured by a temperature sensor including a sensitive element positioned in a free space of the aircraft engine.

Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.

Abstract: A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.

Abstract: A method and system adapted for removing one or more shells from an assembly of multiple annular shells, for example, turbine shells of a gas turbine engine. The method includes removing an upper shell positioned in an upper position relative to a lower shell of the assembly of multiple annular shells, and then positioning and securing a counterweight in the upper position and securing the counterweight to the lower shell as a replacement for the upper shell in the upper position. The counterweight and the lower shell are then rotated in unison until the lower shell is in the upper position and the counterweight is in a lower position previously occupied by the lower shell. Thereafter, the lower shell can be removed from the assembly.

Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first vane segments that extend radially between an inner rotor platform and an outer rotor platform, and a plurality of first flow apertures that extend axially through the duct blocker rotor. Each first flow aperture also extends circumferentially between respective adjacent first vane segments. The duct blocker stator includes a plurality of second vane segments that extend radially between an inner stator platform and an outer stator platform, and a plurality of second flow apertures that extend axially through the duct blocker stator. Each second flow aperture also extends circumferentially between respective adjacent second vane segments. The first vane segments move circumferentially relative to the second vane segments to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: A turbine for a supercharging device of an internal combustion engine may include a turbine wheel which is rotatably arranged about an axis of rotation in a turbine housing. A radial inflow channel may be arranged coaxially to the turbine wheel, which leads to a radial inlet region of the turbine wheel. The inflow channel may be axially bounded on one side by a blade carrier and axially bounded on the other side by a cover disc. A plurality of guide blades may be pivotably arranged on the blade carrier, and a plurality of spacer elements may axially project from the blade carrier. An axial outflow channel may be arranged coaxially to the turbine wheel, which leads from the inlet region to an axial outlet region of the turbine wheel, which may be radially bounded by an inner contour formed complementary to an outer contour of the rotating turbine wheel.

Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: An example blade outer air seal assembly includes a blade outer air seal that is biased toward a second part. The blade outer air seal and the second part move together radially during operation. Radial inward movement of the blade outer air seal is limited exclusively by the second part during operation.

Abstract: A fan cooling system has individual fan modules which are connected together in an end-to-end configuration, where one of the fan modules is connected to a mechanism which rotates the linear array of fan modules. The fan modules are substantially identical, which allows prefabrication of the fan modules prior to on-site installation of the system. Each fan module may contain water injection piping and nozzles, which allows the fan cooling system to dispense fog. The linear array of fan modules may be rotated along a longitudinal axis, such that the axial flow direction of the fans may be changed with respect to a vertical plane. A suggested use of the fan cooling system is for the cooling of livestock in large livestock structures.

Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behavior of the elements.

Abstract: An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end.