Abstract: An inner barrel for a nacelle for an engine is provided. The inner barrel includes a radially inner acoustic liner and a radially outer structural barrel. The structural barrel includes a flange for coupling the inner barrel to the nacelle. At least a portion of the flange is formed integrally with the structural barrel.

Abstract: A centrifugal blower comprises: an impeller (2) provided with blades (12); a casing (3) that houses the impeller (2), surrounds the impeller (2) on an outer side of the impeller (2) in a radial direction of the impeller (2) to form a spiral flow passage (C1) through which air (AR) can flow, and is provided with a nose section (30) forming a start point (S) of the spiral flow passage (C1) and an end point (E) of the spiral flow passage (C1) where one turn of the spiral flow passage (C1) from the start point (S) terminates; a drive unit (4) that rotates the impeller (2) about the center axis (O) of the impeller (2); and a vane (5) that is provided on the bottom plate (22) of the casing (3), divides the spiral flow passage (C1) in the radial direction of the impeller (2), and extends along a circumferential direction of the impeller (2). The rear edge (6) of the vane (5) is located upstream from the nose section (30) in a primary flow direction (DI) of the spiral flow passage (C1).

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Abstract: A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.

Abstract: An example seal includes, among other things, a plug body to limit flow through an axially extending interface between a first component and a second component, the plug body to flow when positioned within both a cavity of the first component and a cavity of the second component.

Abstract: The invention concerns a rotary assembly for a turbomachine, comprising: a disc (16) having an external periphery having an alternation of slots (22) and teeth (20), blades (14) extending radially from the disc (16), and the roots (24) of which are engaged axially and held radially in the slots (22) of the disc, platforms (30) extending circumferentially from the blades (14) and which are arranged circumferentially end to end, opposite each other, axial sealing means upstream and/or downstream of an annular zone extending radially from the platforms (30) as far as the disc (16). According to the invention, the sealing means comprise radially an internal annular part (64) and an external annular part (66) structurally separate from each other, and the facing radial ends of which are adapted for a relative radial movements by sliding sealingly, only an absorption of the centrifugal forces of the external part (66) being provided rotationally by the platforms (30).

Abstract: The present invention relates to a rotating blade for a turbomachine, in particular a compressor stage or a turbine stage of a gas turbine, particularly of an aircraft engine, having a blade element for deflecting the flow, with a pressure side and a suction side, these sides being joined by a leading edge and a trailing edge, wherein a stacking axis of the blade element, in the radial direction over a radius r from a root of a blade element at r=0 to a tip of a blade element at r=H, has a course x(r) in a first downstream direction perpendicular to the radial direction and parallel to a principal axis of the turbomachine and has a course y(r) in a second direction perpendicular to the radial direction and to the first direction.

Abstract: The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members mounted at one or more predetermined locations around a circumference of the fan shaft of the fan. More specifically, the predetermined location(s) has a swirl distortion exceeding a predetermined threshold. Further, the inlet assembly includes at least one airflow modifying element configured within the inlet so as to reduce swirl distortion entering the fan.

Abstract: An apparatus for the actuation of a throttle valve, in particular a throttle valve arranged in an intake system of an internal combustion engine, uses a servomotor, in which apparatus at least one device for thermal decoupling is arranged between the throttle valve and servomotor. A shaft of the servomotor is coupled to a shaft of the throttle valve via a torque-transmitting coupling element with a definedly low heat transfer capability.

Abstract: The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members, such as struts or strakes, mounted at predetermined locations around a circumference of the fan shaft of the fan at the inlet. The predetermined location(s) may be determined as a function of swirl distortion entering the inlet. As such, the structural member(s) are configured to reduce swirl distortion of the airflow entering the fan. In some embodiments, the inlet assembly may also include inlet guide vanes. In alternative embodiments, the inlet assembly may be absent of inlet guide vanes.

Abstract: The present disclosure is directed to an aerodynamic inlet guide vane assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet guide vane assembly is configured for mounting to fan shaft and a nacelle of the aft fan. The inlet guide vane assembly includes a plurality of inlet guide vanes grouped into a plurality of inlet guide vane groups. Each of the inlet guide vanes has a shape and an orientation corresponding to airflow conditions entering the fan. Further, the inlet guide vane groups are spaced circumferentially around the central axis as a function of the airflow conditions entering the fan.

Abstract: A rotating component for a turbine engine includes a rotor portion protruding radially outward, at least one overweight region is located in the rotor portion, and at least one additively manufactured counterweight region is positioned relative to the at least one overweight region such that the rotating component is circumferentially balanced.

Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.

Abstract: In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic.

Abstract: A method of assembling and retaining a noise attenuation device (30) within an air inlet (16) of a compressor cover (12) includes inserting the noise attenuation device (30) into the air inlet (16) and applying a rolling compressive force to the air inlet (16) using a forming tool (40). As a result, the air inlet terminal end (17) is deformed radially inward so as to form a radially-inwardly protruding lip (17b) about the air inlet terminal end (17). The radially-inwardly protruding lip (17b) is configured to retain the noise attenuation device (30) within the air inlet (16). The forming tool (40) used to form the radially-inwardly protruding lip (17b) is also described.

Abstract: A blower apparatus includes a motor portion having a central axis extending in a vertical direction; an impeller arranged above the motor portion, joined to a rotating portion of the motor portion, and arranged to rotate to send a gas from above radially outward; an impeller cover portion including an inner surface arranged to cover an outer circumference of the impeller and an upper side of an outer edge portion of the impeller, and further including an air inlet defined in a center thereof; a body cover portion joined to the impeller cover portion, arranged to cover an outer circumference of the motor portion, and arranged to define a tubular space between the body cover portion and a housing tubular portion defining an outer surface of the motor portion and extending in the vertical direction to assume a tubular shape; and a plurality of guide vanes arranged in a circumferential direction in the tubular space, and each of which is arranged to extend in a radial direction between an inner surface of the bod

Abstract: Rotor blade for a wind turbine, including a main blade part (4) with a blade tip (8). The blade tip (8) results in a blade tip vortex downstream of the rotor blade (1) during operation. The blade tip (8) includes a vortex de-stabilizer (7) which is configured to de-stabilize the blade tip vortex during operation of the rotor blade (1). Furthermore, a wind turbine field including a plurality of wind turbines positioned in a grid. One or more wind turbines on a boundary of the predetermined grid (e.g. a front row of the grid) are provided with at least one such rotor blade (1).

Abstract: A method includes substantially eliminating surge of a compressor and reducing specific fuel consumption and exhaust emissions of an engine by adjusting exhaust flow through an exhaust gas recirculation system, by adjusting airflow through a compressor recirculation valve, by adjusting fuel injection timing, or by adjusting a combination thereof in response to variance in a plurality of parameters. The parameters include quantity of exhaust emissions, a maximum in-cylinder pressure of the engine, an area ratio of an exhaust gas recirculation mixer of the exhaust gas recirculation system, estimated or sensed compressor surge, engine load, altitude of operation, or combinations of the parameters thereof.

Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

Abstract: To provide enhanced operation of data storage devices and systems, various systems, apparatuses, and methods are provided herein. In a first example, a backflow assembly includes a backflow stopper comprising a frame configured to structurally support a fin array when coupled to a fan, the fin array comprising a plurality of flexural deformation elements and associated fin elements arrayed in a radial arrangement to establish a pathway for airflow, each of the flexural deformation elements configured to move an attached fin element responsive to airflow impacting the attached fin element. An acoustic barrier assembly is positioned adjacently to the backflow stopper and configured to attenuate acoustic waves emanating from the fan.

Abstract: A fan motor assembly capable of improving efficiency of a motor by minimizing flow loss, and a vacuum cleaner having the same includes a case, a motor installed inside the case to form a suction force, an impeller rotatably installed on a shaft of the motor, and a guide fan configured to guide air that is suctioned by the motor, wherein the guide fan includes a first guide unit configured to increase pressure of the suctioned air and a second guide unit provided at an upper side of the first guide unit to be in contact with the case.

Abstract: A gas turbine engine includes a fan, a compressor section having at least two sequential compressors, a combustor section fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. The turbine section includes at least a first turbine, a second turbine and a third turbine. One of the first turbine, the second turbine and the third turbine is a fan-drive turbine. An environmental control system air supply includes at least a first compressor bleed and a second compressor bleed. Each of the first compressor bleed and the second compressor bleed are positioned upstream of a highest pressure compressor of the at least two compressors.

Abstract: A multi-blade fan includes a support body rotatable about a rotary shaft, and a plurality of blades secured to the support body such that an inter-blade pitch angle relative to the rotary shaft assumes a prescribed arrangement. The blades extend along an axial direction of the rotary shaft. The plurality of blades are disposed such that, with respect to amplitude values of periodic functions at individual orders when the prescribed arrangement is expanded in a periodic Fourier series, a maximum amplitude value is less than 200% of a second-largest amplitude value.

Abstract: The present application relates to a rotor of a compressor or axial turbomachine comprising a vibration-damping system equipped with piezoelectric transducers distributed circularly and connected to dissipative resonant electric circuits. The circuits are closed and are equipped with a resistor and a coil. The piezoelectric transducers are divided into two sets of alternated transducers, each set being connected to a passive RLC circuit. In order to ensure a pooling of capacitances and currents thereof, the piezoelectric transducers are connected in parallel. During operation, the rotor is subjected to a turning excitation and is likely to vibrate and to deform in accordance with a modal shape with diameters with orthogonal deformation waves. The number of transducers is equal to the quadruple of the number of diameters of the mode, so as to be able to utilize the symmetrical character of this mode with diameters.

Abstract: A multi-stage fuel pump includes a casing having a fuel intake formed on one side thereof and a fuel discharge port formed on the other side thereof, and a plurality of impellers provided within the casing, having a plurality of blades disposed on a circumferential surface in an outward direction of the circumferential surface and having blade chambers formed between the blades and penetrating through upper and lower surfaces of the impellers to allow fuel to be discharged and introduced to and from upper and lower sides of the blades, and formed in multiple stages, wherein fuel intaken through the fuel intake according to rotation of the impellers is discharged to the fuel discharge port through the blade chambers of the impellers, and the numbers of the blades of each of the impellers are different, thereby reducing blade passage frequency (BPF) noise generated according to rotation of the impellers.

Abstract: The present invention relates to a blade row group arrangeable in a main flow path of a fluid-flow machine and including N adjacent member blade rows firmly arranged relative to one another in both the meridional direction (m) and the circumferential direction (u), with the number N of the member blade rows being greater than/equal to 2 and (i) designating the running index with values between 1 and N. Here, a front member blade row with front blades (i) having a leading edge and a trailing edge as well as a rear member blade row with rear blades (i+1) having a leading edge and a trailing edge are provided.

Abstract: Stirrer (M) that includes at least two blades and is able to be fixed to a rotary shaft, wherein each blade has a leading edge facing the fluid to be stirred and a trailing edge facing away from the leading edge, and wherein each blade is obtained by bending a flat metal sheet, each blade having two longitudinal bends, the length of each bend being greater than 60% of the maximum radius of the blade.

Abstract: A method for designing a turbine having a plurality of stages disposed axially one behind the other in the direction of flow through the turbine, each stage being formed of a stationary row of a plurality of stator vanes and a rotating row of a plurality of rotor blades. The row of rotor blades of at least one of these stages has a plurality of rotor blade clusters each formed of at least two rotor blades (A1, B1; A2, B2) having different airfoil profiles and/or different distances (?A, ?B) from adjacent rotor blades following in the direction of rotation. A vane-to-blade-cluster ratio (V/(B/P)) parameter indicates the ratio of the number of stator vanes (V) to the quotient (B/P) of the number of rotor blades (B) of the stage divided by the number of rotor blades per rotor blade cluster (P).

Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.

Abstract: There is provided a centrifugal air blower capable of effectively suppressing noise caused by the shapes of a tongue part and a bell mouth formed in a scroll casing, and including: a fan 3 composed of a bottom plate 6 fixed to a rotating shaft, multiple blades 8, and an annular rim 9 provided concentrically with the bottom plate; a scroll casing 4 for housing the fan; a spiral flow passage 19 formed around the fan; and a tongue part 16 for suppressing an inflow of air from the end of winding to the beginning of winding of the spiral flow passage. A portion of the tongue part on the other end side in the axial direction of the rotating shaft is inclined to increase a dimension of overhanging in a counter-rotating direction of the fan toward the other end side in the axial direction of the rotating shaft.

Abstract: A method for reducing the noise level generated by a fan of a turbomachine including a plurality of vanes, said method further including, when the turbomachine is operating and under given flight conditions, the following steps measuring an operational pitch angle for each of the vanes, calculating an offset between the operational pitch angle of each of the vanes and a predetermined reference pitch angle for the given flight conditions so as to produce a controlled noise level at multiple rotation frequencies of the fan, correcting the orientation of the vanes so as to compensate their operational pitch angles depending on the offsets thus calculated.

Abstract: A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.

Abstract: The invention relates to a fan unit (1) for mobile use for ventilating an area in which it is deployed, in particular for circulating fresh air in areas contaminated by smoke or gases, which comprises a main frame (2), having a lifting frame (4) mounted thereon and an axial fan (3). A first pivot arrangement (8) for the lifting frame (4) is disposed on the one hand in the region of a frame part (7) extending up from a base frame (6) and on the other hand in a first end region (14) of the lifting frame (4) facing the frame part (7). The lifting frame (4) can be adjusted in terms of its vertical distance from the base frame (6) from a non-operating position lying closer thereto into a raised deployment position. A second pivot arrangement (17) is disposed on the lifting frame (4) about which a support frame (19) is mounted so as to be pivotable in terms of its relative position with respect to the base frame (6).

Abstract: An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The air intake may comprise a scroll portion and a strutted portion configured to receive the flow of air from the intake duct and channel the flow of air toward the intake outlet. The strutted portion may comprise one or more vanes for interacting with the flow of air. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

Abstract: A gas compressor assembly configured to pressurize an airflow received from the ambient for delivery to an internal combustion engine having a cylinder includes a compressor housing. A compressor wheel is disposed inside the compressor housing and configured to pressurize the airflow. A compressor bypass is configured to direct the pressurized airflow away from the cylinder. A pressure relief valve is configured to selectively open and close the compressor bypass to thereby limit pressure of the pressurized airflow and minimize surge of the compressor wheel. A baffle arranged inside the compressor bypass is configured to dissipate energy of a sound wave generated by the pressurized airflow upon an initial opening of the pressure relief valve. An internal combustion engine employing such a turbocharger is also disclosed.

Abstract: A method for designing a turbine of a gas turbine, in particular of an aircraft engine, which has a last stage having a rotating last rotor grid, having a plurality of rotating blades, and an adjacent, downstream, stationary exit guide grid, having a plurality of guide vanes; with the last stage being characterized by a vane-to-blade ratio characteristic quantity, which indicates the ratio of the number of guide vanes to the number of rotating blades.

Abstract: A fan module and an electronic device using the fan module are provided. The fan module includes a housing, a fan blade assembly, and a fan hub. The housing has a first surface on which plural wind guiding structures are arranged. The fan blade assembly is pivoted to the housing through the fan hub and adapted to rotate along a rotation direction. The wind guiding structures are arranged along a circumferential direction of the fan hub to guide a wind flow into the housing while the fan blade assembly is being rotated.

Abstract: In a vibration damper of a turbomolecular vacuum pump, a vacuum tightness function and a vibration damping function are both performed by one ore more toroidal rings made of an elastic material. The elastic rings assume a resting configuration while the vacuum pump is not operating and the damper is at atmospheric pressure, and they assume a compressed configuration while the vacuum pump is operating and the damper is under vacuum conditions. In the compressed configuration, the elastic rings are deformed due to a compression force. This deformation of the elastic rings prevents metal-to-metal contact between the vacuum pump and a vacuum chamber to which the pump is connected through the damper.

Abstract: A centrifugal fan includes an impeller. The impeller includes a hub, a plurality of connecting structures, an annular structure and a plurality of blades. The hub includes a circumferential surface. The connecting structures are disposed on the circumferential surface of the hub at intervals. Any adjacent two of the connecting structures define a first minimum distance on the circumferential surface. At least two first minimum distances are not equal. The annular structure is connected to the connecting structures. The blades are disposed on the annular structure at intervals.

Abstract: An airfoil assembly for a turbine engine, comprising at least one airfoil having a leading edge and a trailing edge, a band having an inner side and an outer side and rigidly coupled to the at least one airfoil along a portion of an interface between the band and the at least one airfoil for providing at least a portion of support for the at least one airfoil, a relief located in the band at the leading edge or the trailing edge of the at least one airfoil and defining a stress relief gap between the band and the leading edge or trailing edge and a closure preventing airflow through the relief.

Abstract: A hand dryer for drying a user's hands by means of an airflow discharged through an air outlet on the hand dryer. The airflow is generated by a motor-driven fan unit. The fan unit is supported by resilient support member in contact with the fan unit, the support member having a vertex, which vertex makes said contact with the fan unit.

Abstract: A fan assembly includes a body and an air outlet connected to the body. The body includes an air inlet comprising a plurality of apertures formed in an outer casing of the body, an impeller and a motor for driving the impeller to generate an air flow which passes along an air flow path extending from the air inlet to the impeller, a drive circuit for actuating the motor, the drive circuit being connected to the outer casing, and a panel for shielding the drive circuit from the air flow passing along the air flow path. The drive circuit includes a connector for connecting the drive circuit to a power cable, the connector being located within the outer casing. The outer casing includes an aperture through which the power cable is inserted to connect the cable to the connector, The panel includes a drain located beneath the connector.

Abstract: A fan assembly and a fan frame thereof are disclosed. The fan assembly includes a fan frame and an impeller disposed in the fan frame. The fan frame has an air inlet end and an air outlet end, and includes a sidewall, a top portion and a bottom portion. The top portion is disposed close to the air inlet end and connected to one end of the sidewall. The bottom portion is disposed close to the air outlet end and connected to the other end of the sidewall. The bottom portion has at least one silencing structure.

Abstract: A centrifugal fan includes a housing and an impeller. The housing includes a first surface and a flow channel wall. The first surface has a surrounding section and an air inlet section. The surrounding section encircles the air inlet section. The flow channel wall defines a flow chamber and an air outlet, and at least a sidewall of the flow channel wall has a tongue portion close to the air outlet. The impeller is rotatably connected within the flow chamber. The surrounding section plus the air inlet section is an area on the first surface, on which the impeller is projected, and the surrounding section has a convex structure.

Abstract: A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.

Abstract: A method for the manufacture of a double-row blade wheel for a fluid-flow machine that includes a first grid row with a plurality of first blades and a second grid row with a plurality of second blades is provided. The method includes the following steps: manufacturing a first grid row or segments of the first grid row; manufacturing a second grid row or segments of the second grid row, independently of the first row; and after the respective manufacture, connecting the first grid row to the second grid row or connecting segments of the first grid row and/or of the second grid row to one another or to one of the grid rows.

Abstract: A method for designing a stage for an axial turbomachine having a guide blade ring and a rotor blade ring arranged downstream of the guide blade ring is provided. The method includes: profiling a guide blade ring having guide blades arranged regularly over the circumference of the guide blade ring in accordance with basic aerodynamic and mechanical conditions; moving at least one profile section of at least one of the guide blades in the circumferential direction in such a way that the pitch angle for the at least one guide blade and a guide blade arranged adjacent thereto varies over the blade height in such a way that during operation of the axial turbomachine the departing flow formed downstream of the guide blade ring is irregularly formed over the circumference of the axial turbomachine, such that the vibration excitation of the rotor blades of the rotor blade ring is low.

Abstract: A blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another, on which first element arrangements that are identical to one another and have at least one first element are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements, which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element are movably mounted, wherein first and second element arrangements are different from each other.

Abstract: An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through the inlet duct.

Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.