Abstract: A brush seal assembly is adapted to be operatively mounted between a stator and a rotor of a gas turbine engine. The brush seal assembly comprises a housing and a seal operatively coupled to the housing. The seal comprises at least two annular brushes each having a plurality of bristles extending away from the housing. The at least two annular brushes and the housing defines a cavity therebetween. The housing defines at least one circumferential surface within the cavity. The housing comprises at least one discontinuity defined in the at least one circumferential surface. The at least one discontinuity disrupts a continuity of annularity of the circumferential surface.

Abstract: An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.

Abstract: Method and apparatus for a flight vehicle including a wing having a high aspect ratio and first and second rotors having a high aspect ratio, with a ratio of the rotor diameter to wing length ratio is equal to or greater than about 0.25. In embodiments, the flight vehicle can include a first and second motor, each less than about one thousand HP, to drive a respective rotor and a second motor. The flight vehicle can include a cruise mode and a VTOL mode.

Abstract: A muffling device applied to a ventilating fan having a scroll casing that has a bottom plate and a top plate includes a first annular muffling panel and a second annular muffling panel. The first muffling panel includes a first wall extending from an edge of the through hole in a direction away from the bottom plate and a second wall extending inward from a top end of the first wall and extending toward the bottom plate. The second muffling panel includes a third wall extending from the top plate in a direction away from the bottom plate and a fourth wall extending from a top end of the third wall. The first muffling panel, the second muffling panel, and the top plate corporately define a first noise reduction chamber. A distance from the second muffling panel to the first muffling panel is gradually increased in a radially outward direction.

Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle.

Abstract: A guide vane retention system for a gas turbine engine. The system includes an outer diameter shroud defining an aperture. Also included is a guide vane having a radially outer end extending through the aperture, the guide vane defining a slot proximate the radially outer end and positioned radially outwardly of the outer diameter shroud in an installed condition of the guide vane. Further included is a clip disposed within the slot of the guide vane. The clip includes a looped end. The clip also includes a first leg extending away from the looped end to a first free end. The clip further includes a second leg extending away from the looped end to a second free end.

Abstract: A blower arrangement comprising an impeller, which has an axial intake opening formed by a cover plate covering impeller blades at least in sections, by an intake nozzle connected upstream of the impeller, which extends at least in sections into an overlap section in the intake opening of the impeller, wherein a circumferential nozzle gap is formed between the intake nozzle and the cover plate of the impeller, an outer nozzle, which is arranged spaced apart in the radial direction in relation to the impeller and the intake nozzle and enclosing them in the circumferential direction. A first circumferential radial gap is provided between the outer nozzle and the intake nozzle, which forms an inlet nozzle duct extending in the flow direction. A second circumferential radial gap is provided between the outer nozzle and the cover plate of the impeller, which forms a gap duct extending in the flow direction.

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

Abstract: The disclosure relates to a flow-conducting grille for arranging on the suction side of a fan, with a grille web structure which comprises radial webs spaced apart in the circumferential direction and coaxial circumferential webs spaced apart in the radial direction, wherein the radial webs of at least one quadrant of the flow-conducting grille are curved in each case over their radial extension, viewed in the circumferential direction, towards a predetermined radial plane extending from a central axis of the flow conducting grille.

Abstract: A device and method for regulating a compressor for an internal combustion engine. At least one actual variable is detected that characterizes a property of an air column, which is situated at an outlet of the compressor in an induction tract of an internal combustion engine, the actual variable being compared in a comparison with a comparison value, the comparison value characterizing a limit for the property of the air column, a setpoint variable being determined as a function of the result of the comparison in order to shift the actual variable in the direction or opposite direction of the comparison value, and an actuator for influencing the actual variable being operated as a function of the setpoint variable.

Abstract: An active tip clearance control system of a gas turbine engine and an associated method are disclosed. The system comprises a Coanda effect fluidic device configured to control a flow of clearance control fluid to a turbine section of the gas turbine engine for active tip clearance control.

Abstract: A composite material guide vane for a gas turbine engine, the composite material including fiber reinforcement densified by a matrix, the fiber reinforcement being formed as a single piece by three-dimensional weaving and including an airfoil and at least two fastener flanges extending from a radial end of the vane towards opposite side faces of the airfoil, the fastener flanges being axially offset from each other.

Abstract: Systems and methods for indirect monitoring of combustor dynamics in a gas turbine engine include collecting vibration data acquired by a vibration sensor, which is mounted proximate to an operational component positioned relative to a combustor of a gas turbine engine. The vibration data can be transformed into a frequency domain representation at periodic intervals. The relative signal strength of the vibration data can be determined over the one or more identified frequency bands. The relative signal strength can be adjusted with hysteresis at each of the one or more identified frequency bands. Occurrence of a combustor dynamics event at one or more specific resonant frequencies can be determined based at least in part on evaluation of the adjusted relative signal strength relative to one or more event detection threshold levels.

Abstract: A bi-directional blower includes a blower body for guiding for air to flow along an entire circumference scroll shape of an inner space of the blower body. The blower body divides the inner space into an upward space and a downward space to guide air flow. The blower body comprises: an upper discharge case discharging the air flow along the entire circumference scroll shape toward the upward space through an upper discharge port; and a lower discharge case discharging the air flow along the entire circumference scroll shape toward the downward space through a lower discharge port.

Abstract: A fan noise-lowering structure includes a fan frame main body and a connection section. The fan frame main body has a bottom side and a frame peripheral wall. The frame peripheral wall is perpendicularly annularly disposed on the outer rim of the bottom side. The inner rim of the frame peripheral wall defines an airflow passage. Two ends of the airflow passage respectively have an inlet and an outlet. The connection section is disposed in the frame peripheral wall. Two ends of the connection section are connected with the frame peripheral wall. The two ends of the middle passage are an inlet end and an outlet end in communication with the airflow passage. The connection section serves to guide the high-pressure air of the outlet to jet toward the inlet so as to achieve multiple noise-lowering effects.

Abstract: An electronic device having a soundproof structure is provided. The electronic device includes a housing including an internal space, an inlet and an outlet formed on one side of the housing, a cooling fan disposed in the internal space, and configured to create an air-flow introduced from the inlet which is discharged to the outlet, and a sound absorbing member disposed to surround, at least in part, a peripheral area of the cooling fan in a direction to not obstruct the air-flow.

Abstract: Collar support assemblies are provided. For example, a collar support assembly for an airfoil comprises a collar that includes a first surface shaped complementary to a fillet of the airfoil and a planar second surface. The first surface is disposed adjacent the fillet of the airfoil. The collar support assembly further comprises a shim material disposed between the second surface and an airfoil support structure and a filler material inserted between the first surface and the fillet of the airfoil to provide a tight fit between the collar and the airfoil. In other embodiments, the collar support assembly comprises a pair of collars and supports an airfoil doublet. The airfoil doublets may be part of an outlet guide vane assembly of a gas turbine engine, and methods for assembling outlet guide vane assemblies also are provided.

Abstract: A diagonal or radial fan comprises a rotating motor fan wheel and an upright guide device that in terms of flow is connected downstream of the motor fan wheel, wherein the motor fan wheel comprises a motor and an impeller with blades that is rotary driven by the motor, said blades being arranged between an impeller cover plate and an impeller base disk, wherein the guide device comprises at least one guide device cover plate and one guide device base disk, and wherein the guide device cover plate and the guide device base disk are in continuous elongation to the impeller cover plate and the impeller base disk.

Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.

Abstract: A gas turbine engine has a stator vane assembly. The stator vane assembly includes an inner diameter shroud, an outer diameter shroud located radially outward from the inner diameter shroud, a vane extending radially outward from the first inner diameter shroud to the outer diameter shroud. The wedge clip is positioned horizontally through the vane to prevent the vane from being dislodged from the stator vane assembly.

Abstract: Spatial power-combining devices, and in particular, antenna structures for spatial power-combining devices are disclosed. A spatial power-combining device includes a plurality of amplifier assemblies, and each amplifier assembly includes an input antenna structure, an amplifier, and an output antenna structure. At least one of the input antenna structure and the output antenna structure may have a profile that includes tuning features, such as steps or other shapes, configured to tune or match with a desired operating frequency range. The tuning features may be configured with one or both of a signal conductor and a ground conductor of at least one of the input and output antenna structures. The tuning features may be non-symmetric across a particular signal conductor or a ground conductor, and the tuning features of a signal conductor may be non-symmetric with the tuning features of a ground conductor.

Abstract: A flange joint assembly includes a first structure including a first flange and a second structure including a second flange coupled to the first flange to form a joint therebetween. The second flange includes a radially outer surface. The flange joint assembly also includes a compression ring coupled to at least the radially outer surface and configured to apply a compressive force to the radially outer surface to reduce an amount of tension stress within said second flange.

Abstract: An engine for mounting in or to an aircraft includes a stage of compression airfoils rotatable about a central axis; a casing surrounding the stage of compression airfoils and defining an inlet; and a low-distortion inlet assembly mounted within the inlet. The inlet assembly includes one or more structural members mounted at predetermined locations around a circumference of the central axis within the inlet, the predetermined locations defining an airflow distortion exceeding a predetermined threshold; and at least one airflow modifying element configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils.

Abstract: A fan wheel has a hub cup and a plurality of blades which are arranged on the hub cup and extend radially outward from an outer wall of the hub cup which is in particular at least substantially cylindrical. Each blade has a leading edge and a trailing edge, wherein for at least one blade, an axial unit depth z*(t) of the blade has an aperiodically wave-like shape. A radiator fan module has a fan wheel of the type described above, and the fan wheel can be used in a motor vehicle.

Abstract: A gas turbine engine including a support structure including a conduit coupled to a static support. The conduit defines an end wall between which a fluid is contained within a volume defined by the conduit. An effort variable provided to the support structure modulates a stiffness of the support structure.

Abstract: A gas turbine engine includes a fan section having a single-stage fan, a core turbine engine, and a nacelle at least partially surrounding the fan of the fan section and the core turbine engine. The gas turbine engine also includes an outlet guide vane extending between a casing of the core turbine engine and the nacelle. The gas turbine engine is configured to define an acoustic ratio greater than or equal to 2.3, with the acoustic ratio being a ratio of an axial spacing between the trailing edge of the fan blade and the leading edge of the outlet guide vane at a radial location seventy-five percent (75%) along the span of the fan blade to the axial width of the fan blade also at the radial location seventy-five percent (75%) along the span of the fan blade.

Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.

Abstract: A blade for a turbomachine bladed wheel having N blades. At one end, the blade presents a platform that is formed integrally with an airfoil of the blade. Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil. Each of these segments forms an angle of 90°-180°/N relative to the radial direction on either side of the airfoil.

Abstract: A method for determining the vibration of turbomachine rotor blades, including steps of measuring, via one or more sensors, the variation in the minimum distance between each sensor and the top of each blade along a radial axis of the rotor, between successive rotations of each blade in front of each sensor, a minimum distance value being obtained on each passage of each blade in front of each sensor, in order to deduce therefrom a variation in the lengths of the blades along the radial axis; and, using directly, as such, the variation in the length of the blades along the radial axis in a model of the deformation of the blades, in order to deduce therefrom characteristics of one or more vibrational modes of the rotating blades. A turbomachine can be equipped with a device implementing this method.

Abstract: A turbine engine that includes an engine casing including a shell and an angel wing member. The angel wing member includes a base defined at the shell and a tip positioned distal from the base. The turbine engine also includes a backsheet extending over the angel wing member such that an angled region is defined in the backsheet at an interface with the tip. The tip has a predetermined contour capable of mitigating stress concentrations in the angled region induced from said tip.

Abstract: A scroll casing forms a scroll flow passage of a centrifugal compressor, and, provided that, in a cross section of the scroll flow passage, Eo is an outer end of the scroll flow passage in a radial direction of the centrifugal compressor, Ef is a front end of the scroll flow passage in an axial direction of the centrifugal compressor, and Mw is a middle point of a maximum flow-passage width Wmax of the scroll flow passage in the radial direction, a flow passage height H of the scroll flow passage in the axial direction gradually increases from a position of the outer end Eo to a position of the front end Ef with respect to the radial direction, and the scroll flow passage has a recirculation flow suppressing cross section in which the front end Ef is disposed on an inner side, in the radial direction, of the middle point Mw, in a section disposed at least partially in a region closer to a scroll start than a connection position of the scroll start and a scroll end.

Abstract: The present invention relates to a balance structure of a fan rotor, which comprises a fan wheel and a balancing part. The fan wheel has a hub and a plurality of blades disposed on the circumferential side of the hub. The hub has a top wall connected to a sidewall. An unbalanced portion is selectively disposed on the top wall or on the sidewall. The unbalanced portion is disposed on one side of a symmetrical axis of the hub. The balancing part is disposed at the unbalanced portion such that the fan rotor is balanced.

Abstract: A fan for cooling an electronic device is described, wherein the fan can include an enclosure and a motor secured within the enclosure. The fan can also include an impeller to be turned by the motor, the impeller having a plurality of blades, wherein an angular spacing of the blades results in an audio spread-spectrum within a range of audio frequencies. In some examples, an arrangement of the blades has a center of mass below a threshold, and the angular spacing of the blades and a blade pass frequency (BPF) results in sound that is distributed in the range of audio frequencies.

Abstract: A soft wall containment system having a casing, a liner system, a containment blanket, and a barrel including multiple features is provided. The soft wall containment system may selectively be installable in a gas turbine engine having a turbine with multiple airfoils. The barrel features may be disposed outboard of the airfoils. The casing barrel may have a first thickness, the casing barrel features may have a second thickness, and the first thickness may be greater than the second thickness. Additionally, the features may be slots that extend through the thickness of the barrel.

Abstract: Provided is a propeller fan including a boss, and a blade fixed at an outer peripheral surface of the boss, wherein the blade has a second protrusion that protrudes toward a positive pressure surface side, at a trailing edge with respect to a rotation direction, the second protrusion is provided in a range on a radially outer side of a center of a radial distance from an inner peripheral end to an outer peripheral end of the blade, and has a protrusion tip end with a maximum protrusion height, a first base at a starting part of protrusion on a radially inner side of the protrusion tip end, and a second base at a starting part of protrusion on a radially outer side of the protrusion tip end, and the protrusion tip end is positioned nearer to the second base than to the first base in the radial direction.

Abstract: Disclosed is a flutter damper, including an acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber, and a piezoelectric element disposed within a first surface of the chamber, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and wherein the piezoelectric element is operatively connected to an electronic engine control.

Abstract: The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a rotating component disposed adjacent to a stationary component.

Abstract: A total air temperature sensor includes a probe head, a strut, and a turbulence inducing surface. The probe head has an airflow inlet and an airflow outlet. The strut defines a leading edge and an opposed trailing edge extending along a longitudinal axis, and connects between the probe head and an opposed probe mount. The turbulence inducing surface is defined in the strut aft the leading edge. The turbulence inducing surface is configured to trip a fluid boundary layer passing over the strut to transition from laminar to turbulent for moving flow separation toward the trailing edge to reduce acoustic noise emission from the total air temperature sensor.

Abstract: An axial fan includes a rotatable fan blade assembly including a plurality of fan blades, and a plurality of permanent magnets affixed to the plurality of fan blades. A stationary guide channel is located radially outboard of the fan blade assembly. A plurality of field coils are located at the guide channel and are configured to drive rotation of the fan blade assembly via magnetic interaction with the plurality of permanent magnets when the plurality of field coils are sequentially energized. A method of operating an axial fan includes energizing a plurality of field coils, urging a fan blade assembly out of contact with the guide channel via magnetic interaction between the plurality of field coils and a plurality of permanent magnets located at the fan blade assembly, and sequentially pulsing the plurality of field coils thereby urging rotation of the fan blade assembly about an axis of rotation.

Abstract: The present disclosure is directed to a rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. Further, the rotor blade assembly includes a flexible extension having a first end and a second end. More specifically, the first end is mounted to a surface of the rotor blade and the second end is free. As such, during operation of the wind turbine, the flexible extension passively adjusts with a changing angle of attack of the rotor blade, thereby reducing variations in blade loading.

Abstract: A fan has an impeller (20) that is equipped with blades (26, 28, 30, 32, 34; 58). The blades are configured so that the blade loading of individual blades differs during operation. As a result of this variable blade loading, the frequencies associated with the blade-passing noise (BPF) of the fan can be distributed over a broader frequency spectrum, and thus have a less obtrusive effect.

Abstract: A diffuser, an airflow generating apparatus, and an electrical device are provided. The airflow generating apparatus includes a motor; an impeller including blades with air passages formed therebetween; and a diffuser including diffusing vanes with diffusing channels formed therebetween. In a flow region defined between a terminating end of one diffusing vane and a starting end of another adjacent diffusing vane, an intersection line between a bottom of the diffusing channel between the two diffusing vanes and its circumferential section includes a front arcuate line segment and a subsequent straight line segment, the arcuate line segment extends curvedly, outwardly and downwardly from or from adjacent an inlet end of the diffusing channel, the straight line segment connects to the arcuate line segment and extends to an outlet end of the diffusing channel. The diffusing channel is designed to improve the operating efficiency of the airflow generating apparatus.

Abstract: Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.

Abstract: A rotor of a turbomachine includes a plurality of rotor blades, which each have a blade leading edge and a tip, the rotor blades forming a first group and at least one further group of rotor blades of different construction. It is provided that the rotor blades of the first group are nominal rotor blades, the rotor blades of the at least one further group each have a material cutout in the transition from the blade leading edge to the tip, the material cutout not being present in the case of the rotor blades of the first group, and the rotor blades of the first group and of the at least one further group form a non-periodic sequence in a circumferential direction.

Abstract: Provided are a vacuum pump and a method for the vacuum pump in which, when contact between a rotating body and a stator is sensed, the cause of the contact can be analyzed. Contact determination is made using a threshold for rotating body contact determination for a displacement signal and a threshold for rotating body contact determination for an acceleration signal. The amount of unbalance of a rotating body is determined using a threshold for amount-of-unbalance increase determination for the displacement signal and a threshold for amount-of-unbalance increase determination for the acceleration signal. When, in one of the displacement signal and the acceleration signal, the threshold for amount-of-unbalance increase determination or the threshold for amount-of-unbalance increase determination is exceeded within a predetermined time before determination of an estimated time point of contact, the contact is determined not to be caused by an increase in accumulation of products.

Abstract: The vacuum suctioning unit of the present invention includes: a cover provided with an air entrance; an impeller for circulating air that enters the air entrance; a motor provided with a shaft connected to the impeller; a guide device for guiding the flow of air that exits an exit of the impeller; and a motor housing that houses the motor and is provided with an air exit. The guide device includes: a guide body disposed below the impeller; a first guide vane formed on a side surface of the guide body and guiding air discharged from the impeller; and a second guide vane formed on the bottom surface of the guide body and connected to the first guide vane to guide air that is moved by the first guide vane. The entrance angle of the first guide vane is within the range of 10 to 27 degrees.

Abstract: A tubeaxial fan housing has a planar support vane that is fixed at sides thereof to opposing interior sides of the tubular housing, toward an inlet of the housing. The support vane receives a shaft on an underside thereof, upon which a propeller is mounted near an outlet end of the housing. The support vane has a curved edge facing the propeller to change a pattern of eddies generated downstream of the support plate and thereby reduce the noise generated by the fan. The curve is an S-shape and may be a sine wave whose period is ? the propeller diameter. The propeller is positioned a relatively large distance from the curved edge of the support vane to reduce further the generation of eddies. That is, the closest point of the curved edge to the propeller is one chord length, which chord is at a tip of a propeller blade. A rounded inlet bell on the housing includes a rounded surface to reduce further turbulence across the propeller and support vane to further reduce sound.

Abstract: Described is an adjustable guide vane ring of a turbomachine having an inner ring which is split radially and mounted axially together, on which a brush seal is configured, an inner ring for a guide vane ring of this kind, as well as a turbomachine.

Abstract: Disclosed is a flutter damper, including an acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber, and a piezoelectric element disposed within a first surface of the chamber, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and wherein the piezoelectric element is operatively connected to an electronic engine control.