Abstract: A shield system for a gas turbine engine extends between an inner case structure and a vane pack.

Abstract: A fan for generating an air current includes a body having an air inlet, and a nozzle connected to the body. The nozzle includes an interior passage for receiving an air flow from the body and an air outlet from which the air flow is emitted from the fan. The interior passage extends about an opening or bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The body includes a duct having an air inlet and an air outlet, an impeller located within the duct for drawing the air flow through the duct, and a motor for driving the impeller. An annular guide member extends about the duct for guiding air from the air inlet of the body to the air inlet of the duct. The guide member defines with the duct an annular noise suppression cavity.

Abstract: A terminal box cover for a ram air fan assembly includes a body defining a top wall having an outer surface. The body extends between a forward end and a rearward end. An opening is formed in a forward wall at the forward end. The opening allows electric supply feeders to move into an internal space defined by the cover when mounted on a terminal box base. The outer surface extends from the forward end to the rearward end such that the forward wall is thicker than a rear wall at the rearward end. The thickness is defined as a distance extending away from the top wall. A separator wall is defined extending from the inner surface. The separator wall extends from the front wall toward the rear wall, but is spaced from the rear wall. The separating wall has a curved inner lip at a rearwardmost end. In addition, a ram air fan assembly, a system including a heat exchanger, and a method of replacing a box cover are also described.

Abstract: A fan casing includes an impeller housing, a mixed-flow impeller located within the impeller housing, and a motor for driving the impeller. The impeller includes a hub connected to the motor, and a plurality of blades connected to the hub, each blade comprising a leading edge located adjacent the air inlet of the impeller housing, an inner side edge connected to and extending partially about the outer surface of the hub, an outer side edge located opposite to the inner side edge, and a blade tip located at the intersection of the leading edge and the outer side edge. The leading edge comprises an inner portion located adjacent the hub, and an outer portion located adjacent the blade tip, and wherein the inner portion is swept rearwardly from the hub to the outer portion, and the outer portion is swept forwardly from the inner portion to the blade tip.

Abstract: A fan with a sound deadening box has in its body a double inlet centrifugal fan and an inlet-port sound absorber formed between the fan and a body air inlet. The fan further includes a casing-inlet-port-side air passage and triangular prism shaped first inlet-port-sound-absorber air passage. With this structure, the fan has a low pressure loss, a low input, high static pressure, and a low level of airflow collision noise.

Abstract: A method of repairing a turbine component having an array of partitions is provided and includes machining one or more partitions of the array to remove trailing edge sections thereof, fabricating one or more replacement inserts, respectively locating the one or more replacement inserts in the one or more machined partitions and substantially simultaneously brazing the one or more replacement inserts to the one or more machined partitions.

Abstract: A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: A liquid pump has a rotor in a pump housing which has a pump chamber, a pump base, a pump-chamber wall and a cover. The rotor rotates just above the pump base, the pump-chamber wall being provided around the outside of and slightly spaced apart from the rotor and having a heating means thereon. An inlet to the rotor is provided centrally in the axial direction towards the rotor and an outlet from the pump housing is provided externally at the periphery of the pump-chamber wall. Blade-like guiding elements which are integrally injection-moulded thereon are arranged on the pump base, radially outside the impeller.

Abstract: A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided.

Abstract: A combustor includes an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface. A shroud circumferentially surrounds at least a portion of the end cap, wherein the shroud at least partially defines a fuel plenum between the upstream surface and the downstream surface. A combustion chamber downstream from the end cap defines a longitudinal axis. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap to the combustion chamber. A transition duct circumferentially surrounds at least a portion of the combustion chamber downstream from the end cap and curves tangentially from the longitudinal axis.

Abstract: A guide vane attachment structure including a first fitting portion formed in a vane joint surface of a guide vane, a support member whose constituent material is a metal is integrally connected to a fan frame, and a second fitting portion to be fitted to the first fitting portion formed in a support joint surface of the support member.

Abstract: A gas turbomachine inlet system includes a duct member having an inlet portion fluidically coupled to an outlet portion through an intermediate portion. The inlet portion, outlet portion, and intermediate portion define a fluid flow zone. A throttling system is arranged in the duct member at one of the inlet portion, outlet portion and intermediate portion. The throttling system is configured and disposed to selectively establish a pressure drop through the fluid flow zone. A method of controlling inlet pressure drop through an inlet system for a gas turbomachine is also described herein.

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.

Abstract: An assembly for use with a power-producing unit includes an annular case, a hub positioned radially inward of the case, a fluidic flow path defined between the case and the hub, a plurality of support tubes each extending between the case and the hub, and a flow modifying structure positioned on an exterior surface of at least a first one of the support tubes and configured to reduce vortex shedding of a passing fluid.

Abstract: A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed angled passages in communication with an inlet space. Each vane includes a bleed port defined in a suction surface thereof, in proximity of the leading edge. The diffuser case includes a passive fluid communication defined at least partially through each one of the vanes between each bleed port and the inlet space upstream of the leading edge, such that air bled through the bleed ports is recirculated upstream of the leading edges to the inlet space to increase a surge margin of the diffuser.

Abstract: A ring airfoil with a voluminous leading edge region, an intermediate region, a trailing edge region including a flap. The ringed structural leading edge region combined with a rigid trailing edge region having intermediate discrete support portions extending therebetween provides sufficient rigidity to support the flap on the trailing edge region while using a membrane intermediate surface to form a portion of the intermediate region of the airfoil.

Abstract: A turbine shroud assembly includes an inner shroud portion comprising a body portion having a first circumferential edge, and a discourager extending circumferentially past the first circumferential edge of the body portion, wherein the discourager is integrally formed with the inner shroud portion.

Abstract: The present disclosure relates to fluid turbines having a turbine shroud assembly formed with mixing elements (e.g., both inwardly and outwardly curving elements) having airfoil cross sections. These airfoils form ringed airfoil shapes that provide a means of controlling the flow of fluid over the rotor assembly or over portions of the rotor assembly. The fluid dynamic performance of the ringed airfoils directly affects the performance of the turbine rotor assembly. The mass and surface area of the shrouds result in load forces on support structures. By delaying or eliminating the separation of the boundary layer over the ringed airfoils, boundary layer energizing members (e.g., vortex generators, flow control ports) on the ringed airfoils increase the power output of the fluid turbine system and allow for relatively shorter chord-length airfoil cross sections and therefore reduced mass and surface area of the shroud assemblies.

Abstract: A compressor guide-vane stage for a turbine engine, the stage comprising two coaxial shrouds, respectively an inner shroud (120) and an outer shroud, with vanes (124) extending between them, the radially inner ends of the vanes being engaged with clearance (125) in orifices in the inner shroud and being secured to the inner shroud by means of a polymerizable sealing resin (126), the guide-vane stage being characterized in that a gasket (140) is mounted on the radially inner end of each vane, the gasket including a slit through which the vane passes and bearing against the radially inside surface of the shroud or in the proximity of said surface, in order to limit the passage of resin through the above-mentioned clearance while the resin is being applied to the inside surface of the shroud.

Abstract: A casing treatment 4 including a recirculation passage 41 and a mixing piping 6 are provided. The recirculation passage 41 has a first recirculation opening 42 and a second recirculation opening 43 that are in communication with each other, the first recirculation opening 42 being formed inside a compressor housing 11 of an exhaust gas turbocharger and opening to an air passage 15 upstream of a compressor impeller 3, the second recirculation opening 43 being formed at the outer circumferential section of the compressor impeller 3. The mixing pipe 6 opens to the recirculation passage 41 and has a return opening 14 for introducing EGR gas and blow-by gas to the recirculation passage 41.

Abstract: A regenerative blower is disclosed with a rotating impeller that includes a hub that includes a main body and a tapered outer periphery or volute that extends around the main body of the hub. The volute has a wide base that extends to a tapered volute tip. A plurality of vanes are spaced apart along the main body of the hub and intersect the volute. Each vane has a base coupled to or integral with the main body of the hub and a distal end extending radially away from the hub. Each vane has a downstream side and an upstream side. The downstream sides are concave and the upstream sides are convex. Each vane may also include a pair of side edges that are beveled inwardly towards the volute as the side edges extend from the downstream side of the vane to the upstream side of the vane.

Abstract: An insulator for a stator assembly includes at least a first insulator adapted to be mounted to the stator core and structured to insulate the stator core from the coils. The at least one insulator includes structure to perform at least one additional function. For example, the structure may include a support member to support and/or locate the PCBA on the stator core, a wire guide to guide cross-over wires that form a connection between coils, and/or positioning structure to precisely position the PCBA with respect to the coils.

Abstract: A system includes a solid feed pump. The solid feed pump includes a housing, a rotor disposed in the housing, a curved passage disposed between the rotor and the housing, a solid feed inlet coupled to the curved passage, a solid feed outlet coupled to the curved passage, and a rotatable sleeve configured to rotate to actively draw solid feed into the solid feed inlet or out of the solid feed outlet.

Abstract: A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.

Abstract: A vane segment according to the present invention includes: an outer connection member connecting a plurality of vanes; positioning jigs for positioning end vanes located at both ends, of the plurality of vanes; and radial restriction sections which restrict the outer connection member so as to be relatively immovable to an outer side in a radial direction of a vane ring, wherein: each of the plurality of vanes has a vane main body and an outer shroud; grooves are formed in the outer shrouds; openings into each of which the positioning jig is inserted are formed in portions of the outer connection member; holes into each of which the positioning jig inserted in the opening is inserted are formed in bottoms of the grooves of the two end vanes; and at least one of the positioning jigs is an eccentric positioning jig.

Abstract: A connector assembly for variable inlet guide vanes in a compressor case of a gas turbine engine comprises an annular case insert having a plurality of circumferentially distributed open-ended receptacles. The annular case insert is sized so as to be received inside a compressor case, with the plurality of circumferentially distributed open-ended receptacles being in register with holes in the compressor case. Bushings have an outer diameter sized to be received in a respective one of the receptacles of the annular case insert, and an inner diameter adapted to receive a connector portion of a vane. Sets of the bushing and the connector portion of a vane in one of the receptacles forming a rotational joint. A method for installing vanes in a compressor case is also provided.

Abstract: A vane assembly for a gas turbine engine includes an annular shroud having openings therein and a plurality of vanes extending radially from the shroud and each having an extremity received within one of the openings. A grommet is positioned within each opening for shielding the vane extremity from the annular shroud. The grommet includes an annular protrusion for providing sealing between the opening and the vane extremity, and an annular restraint element adjacent the protrusion for retaining the vane in place relative to the shroud.

Abstract: A turbojet casing adapted to receive a plurality of vanes, the casing including attachment means (21, 30) for attaching one end of each vane to the casing, the casing being characterized in that the attachment means extend on a face of the casing facing away from the vanes, the casing including orifices (26) for passing the ends of the vanes so that they can co-operate with the attachment means of the casing. A turbojet including such a casing.

Abstract: A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.

Abstract: A compressor inlet manifold for directing air from a radial airflow inlet into an axial compressor inlet of a compressor of a gas turbine engine is disclosed. The compressor inlet manifold provides air flow to the compressor with reduced distortion to the compressor which enables the required design surge margin to be reduced, thereby increasing gas turbine engine efficiency. The improved air flow has reduced distortion, turbulence and unsteadiness. The compressor inlet manifold body may have at least one annular opening extending axially downstream from an upstream wall. Air flow into the compressor inlet manifold may be conditioned with one or more of a flow improvement projection extending radially inward relative to other aspects of a compressor inlet outer wall, a conically shaped inner sidewall, and a baffle positioned at an acute angle relative to an axis aligned with a radially inward air flow.

Abstract: The invention includes vane members that have a space formed therein and a plate spring member that is disposed inside the space of the vane members and elastically contacts inner surfaces of the vane members. The plate spring member includes a positioning portion, an elastic contact portion, and a connection portion. The elastic contact portion is divided into plural numbers in the length direction of the vane members. As a result, in the invention, the elastic contact portion elastically contacts the inner surfaces of the vane members without any partial contact throughout the entire surface thereof. Accordingly, the elastic contact area between the elastic contact portion and the inner surfaces of the vane members is widened, so that self-excited vibration generated in a turbine vane may be reliably suppressed.

Abstract: An exemplary centrifugal fan includes a casing defining an air outlet, and an impeller in the casing. An air channel is defined in the casing between a sidewall of the casing and outermost free ends of the impeller. The sidewall includes a first curved section adjoining a second curved section. The first curved section is located at a more upstream portion of the sidewall than the second curved section along a rotation direction of the impeller. The first curved section extends along a part of an Archimedes spiral or a part of a logarithmic spiral. The second curved section is located farther away from the impeller than an imaginary extension line of the first curved section along the Archimedes spiral or the logarithmic spiral. An air guide plate is formed in the casing and extends from the air outlet to an inner region of the air channel.

Abstract: Disclosed herein are apparatuses and systems for directing the flow of hot gas exiting a transition piece. In an embodiment, an aft frame an aft frame has an exit face that has an airfoil shape. In an embodiment, a transition piece aft exit has an airfoil shape.

Abstract: A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component.

Abstract: A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).

Abstract: A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).

Abstract: A turbomachine includes a housing that defines a flow path, and a stage arranged within the housing. The stage includes a plurality of rotating airfoil members and a first plurality of stationary airfoil members. A second plurality of stationary airfoil members is arranged directly adjacent to the first plurality of stationary airfoil members. A flow improvement system is associated with each of the first and second pluralities of stationary airfoil members. The flow improvement system establishes a predetermined clocking of each of the first plurality of stationary airfoil members relative to each of the second plurality of stationary airfoil members to improve flow characteristics along the flow path.

Abstract: A side channel blower includes a housing comprising a substantially tangential outlet. A housing cover comprises an axial inlet. At least one conveying duct is configured so that the axial inlet fluidly communicates with the outlet. An impeller is driven by a drive unit. The impeller is rotatably supported in the housing and comprises conveying blades which cooperate with the at least one conveying duct. An interruption region is arranged between the outlet and the axial inlet. The interruption region comprises a radially limiting wall and interrupts the at least one conveying duct in a circumferential direction. A first recess is arranged in the radially limiting wall of the interruption region downstream of the outlet. Further recesses are arranged in the interruption region before the axial inlet and after the outlet. A smallest distance between the further recesses is 0.5 to 3 times a distance between two conveying blades.

Abstract: Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one sealing member having an uncompressed cross-section that is substantially circular. The sealing member(s) are disposed between and in contact with the end portion of the vane and the vane-receiving portion of the shroud.

Abstract: An attachment arrangement at a middle of a cover having an elastically deformable portion. The cover includes a concave shell including an inner surface spaced apart from the compressor including an impeller including blades by an attachment. The attachment includes one connection end at the middle of the shell, another end attached to a casing of the turbine engine, and an axisymmetric diaphragm having a generally frusto-conical configuration having an arm profile coupled to the end for attachment to the casing by a double-elbow joint having right and obtuse angles when in a rest position. The distance between the inner surface of the shell and upper edges of the blades can be held constant during operation with minimum clearance adjustment. The cover can be moved such that clearance between the cover and blades of the compressor impeller remains substantially constant and as low as possible.

Abstract: A gas turbine system including a compressor section, a combustor section and a turbine section, wherein the compressor section includes a first wheel and a second wheel having a center bore extending axially therethrough, and wherein the first wheel and the second wheel are relatively adjacent each other. Also included is a gap disposed between the first wheel and the second wheel, wherein airflow is directed radially inward within the gap toward the center bore of the second wheel with or without the help of impellers extending radially. The compressor section further includes an airflow manipulation device disposed within the gap, comprising of at least one or multiple vanes which may start in radial direction but extend at least partially into the center bore.

Abstract: Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of turbine nozzle flow paths therethrough, positioning braze preforms in the plurality of turbine nozzle flow paths and against a surface of the turbine nozzle component, and bonding the braze preforms to the turbine nozzle component to achieve a controlled reduction in the flow area of the turbine nozzle flow paths.

Abstract: An electric blower includes a stator, a rotor, a bracket, rotary fan, air guide, a fan case covering air guide and rotary fan. Air guide includes a partition plate, a diffuser, a partition slope, and a guide vane. Diffuser vanes configure closed passages. Passage lengths of closed passages include a first passage length and a second passage length that is different from the first passage length.

Abstract: One embodiment includes an air pump assembly (10) with an impeller (12), a housing (16), and a diverter (18). The impeller (12) has an axis of rotation (R). The housing (16) surrounds the impeller (12) and has an inlet passage (42) with a longitudinal axis (L1) arranged generally orthogonal to the axis of rotation (R) of the impeller (12). The diverter (18) helps reduce turbulent fluid-flow in the inlet passage (42).

Abstract: A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing.

Abstract: A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.

Abstract: One embodiment includes an air pump assembly (10) with an impeller (12), a housing (16), and a diverter (18). The housing (16) surrounds the impeller (12) and has an inlet passage (40) with a longitudinal axis (L) arranged generally non-orthogonally with respect to an axis of rotation of the impeller (12). The diverter (18) helps reduce turbulent flow in the inlet passage (40).

Abstract: A pollutant collecting pump for water surface comprises a power device (1) and a pollutant collecting barrel (6). The power device (1) is connected to the pollutant collecting barrel (6). A pollutant inlet (4) is provided on the upper portion of the pollutant collecting barrel (6), and a pollutant outlet (5) is provided on the lower portion of the pollutant collecting barrel (6). A blade (2) is provided outside the pollutant collecting barrel (6), and an axis of the pollutant collecting barrel (6) is perpendicular to a rotating surface of the blade (2). The pollutant inlet (4) is positioned above the blade (2). The pollutant collecting pump for water surface is adapted to collect pollutants distributed on water surface with low density and small thickness, and has the advantages in simple structure, low manufacturing cost, convenient operation and thorough collection.

Abstract: A turbomachine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly.

Abstract: A turbine exhaust diffuser system includes a plurality of manways. The plurality of manways each extend between an outer wall of the turbine exhaust diffuser system and an interior access tunnel of the turbine exhaust diffuser system. The plurality of manways extend between the outer wall and the access tunnel at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.