| Entries |
| Document | Title | Date |
|---|
| 20080206043 | Rotor for a turbomachine - The invention refers to a rotor for a turbomachine, wherein the rotor has a vibration reduction device which is formed in such a way that it damps vibrations of the rotor which emerge during operation of the turbomachine. The damping is achieved by means of a rolling body inside the vibration reduction device, wherein the rolling body is arranged with capability of movement along a track surface. | 08-28-2008 |
| 20080206044 | NOISE REDUCTION ASSEMBLY FOR AIRCRAFT TURBOJET - A noise reduction assembly located at a junction plane between an air intake structure and a fan casing of an aircraft turbojet has improved acoustic properties since the alternation of acoustic and non-acoustic zones is displaced or eliminated. In particular, the inner wall of the air intake structure includes a projecting part that extends towards the aft direction beyond the junction plane, in other words the flange of the fan casing. The projecting part may be sufficiently long so that its inner skin is continuous as far as the limit between the acoustic zone and the non-acoustic zone of the nacelle. | 08-28-2008 |
| 20080247864 | Fan and fan frame thereof - A fan includes an impeller and a fan frame. The fan frame has a main body and at least one sound absorber, wherein the main body has a passage for receiving the impeller, a plurality of flanges are disposed on a periphery of the main body, a recess is defined between the two adjacent flanges, an aperture is disposed on a wall of the main body corresponding to the recess so as to allow the recess to communicate with the passage, and the sound absorber is disposed in the recess. Also, a cover is assembled in the min body and covers the sound absorber within the recess. | 10-09-2008 |
| 20080273964 | STATOR DAMPER SHIM - A system and method for reducing vibration and wear to adjacent platform surfaces and mounting locations of a vane segment in a gas turbine engine is disclosed. The present invention seeks to improve the interaction between mating faces of adjacent gas turbine vane assemblies by increasing the surface area where contact between the adjacent vanes occurs, so as to increase the damping capability and reduce the wear to the mating surfaces. | 11-06-2008 |
| 20080286092 | Air convection warmer with noise reduction filter - To reduce the noise level of air convective warmer, the air filter of the warmer is fitted with an air intercept mechanism to disrupt the flow of air that traverses inside the interior cavity of the air filter. By thus disrupting the air flow, the noise that otherwise would have been generated due to a non-interrupted air stream flow is lowered. The air intercept mechanism may be in the form of at least one partition positioned inside the interior cavity of the air filter. Alternatively, double-ended open tubes may be used, so long as the interior cavity of the filter is sealed, with only the tubes providing the passages for air to output from the air filter. Yet a third embodiment of the air reduction filter has an air impermeable material covering at least one portion of the surface area of the filtering material to prevent the inflow air from directly entering into the interior cavity of the air filter through the covered surface area. | 11-20-2008 |
| 20080317586 | CENTRIFUGAL AIR BLOWER - A centrifugal air blower guides returning air from a fan rotated by a rotational drive source out of interference with air delivered by a fan. The centrifugal air blower includes a rotational drive source having a rotational drive shaft, a housing including a holder which holds the rotational drive source in surrounding relation thereto, and a fan coupled to the rotational drive shaft of the rotational drive source. The housing has a disk-shaped flange extending from the holder, and the flange has a plurality of air guides disposed on a surface thereof and extending toward a peripheral edge of the flange. | 12-25-2008 |
| 20090035126 | IMPELLER FOR A COOLING FAN - An impeller ( | 02-05-2009 |
| 20090060717 | SYNCHRONOUS SIGNAL GENERATOR FOR TRIM BALANCING OF JET ENGINE - A synchronous signal generator is provided for use in conjunction with an aircraft engine having a spool and an engine output shaft driven by the spool. The synchronous signal generator includes a generator housing, a generator output member rotatably mounted in the generator housing, a once-per-revolution timing mark on the generator output member, and conversion gearing disposed within the housing and configured to couple the engine output shaft to the generator output member. The conversion gearing rotates the generator output member at substantially the same rotational frequency as the spool when the conversion gearing is coupled to the engine output shaft. | 03-05-2009 |
| 20090060718 | Component with a damping filler - A component ( | 03-05-2009 |
| 20090067991 | COOLING FAN - A cooling fan ( | 03-12-2009 |
| 20090074564 | Air inlet noise attenuation assembly - An air inlet assembly comprising an entrance region configured to receive an airflow, an exit region configured to output the airflow, and an attenuation region disposed between the entrance region and the exit region. The attenuation region has a cross section aspect ratio of at least about 5-to-1, and comprises acoustic absorbing material. | 03-19-2009 |
| 20090110541 | Vibration Management for Gas Turbine Engines - Systems and methods involving vibration management of gas turbine engines are provided. In this regard, a representative method includes: detecting vibrations of a gas turbine engine; automatically adjusting rotational speed of a component of the gas turbine engine in order to attempt to reduce the vibrations to within predefined vibration limits; and automatically adjusting operating parameters of the gas turbine engine such that, if the vibrations are reduced to within the predefined vibration limits, thrust of the gas turbine engine is set to an amount of thrust corresponding to the amount of thrust provided prior to the adjusting of the rotational speed of the component. | 04-30-2009 |
| 20090185897 | PARTICLE VIBRATION DAMPER - Numerous cavities exist in a turbocharger for reasons of construction. If such cavities are filled with particles, inexpensive particle vibration dampers can be realized. Moreover, advantages with regard to additional containment security result in the case of possible bursting of the compressor wheel, and also with regard to noise suppression. | 07-23-2009 |
| 20090191047 | System for reducing compressor noise - A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies. | 07-30-2009 |
| 20090196739 | AXIAL FLOW FLUID DEVICE - An axial flow fluid device in which blade rows having radially-arranged blades are provided in a flow passage of a fluid (Y). The axial flow fluid device includes a turbulent flow eliminating device for eliminating turbulent flow components (Y | 08-06-2009 |
| 20090196740 | Multi directional augmenter and diffuser - This invention relates to increasing the use of an adjustable or flexible augmenter for the increase of power generation primarily used for utilizing wind energy. The adjustable augmenter is a wind enhancement structure with a plurality of flexible walls connected to each other with supporting horizontal elongated members. In the preferred embodiment, the invention is used with a plurality of smaller blades on a rotation connected to a tower structure with a plurality of the rotation and an inlet air flow regulation to achieve optimal power output. A preferred embodiment includes lightweight low cost structure of flexible wall to enhance an air flow into impact impellers connected to a rotation creating a swept area with a height to diameter ratio of greater than four. A preferred embodiment includes wherein said impact impellers connected to a rotation means creating a swept area with a height to diameter ratio of greater than ten. A preferred embodiment includes a furling or wind velocity control means for optimizing the power output of a wind power generating means with a flexible air velocity enhancement means. | 08-06-2009 |
| 20090202341 | TURBOMACHINE MODULE PROVIDED WITH A DEVICE TO IMPROVE RADIAL CLEARANCES - The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing ( | 08-13-2009 |
| 20090202342 | FAN UNIT HAVING A FAN - A fan unit has a fan ( | 08-13-2009 |
| 20090220334 | FAN SHROUD FOR HEAT EXCHANGE TOWER FANS - A heat exchange tower which has at least one fan having fan blades and a fan shroud, and the fan shroud has a sound absorbing portion including an outer ring structure and a sound absorbing material disposed inside the outer ring structure and outside of the circle of rotation of the fan blades. A flared inlet portion is provided leading to the sound absorbing portion. | 09-03-2009 |
| 20090252599 | RING SEALS FOR GAS SEALING AND VIBRATION DAMPING - A connection device for connecting two turbine housings ( | 10-08-2009 |
| 20090269185 | DAMPING SYSTEMS FOR USE IN ENGINES - Damping systems and engines including the damping systems are provided. In one embodiment, and by way of example only, the damping system includes a rotor, a bearing assembly mounted to the rotor, a spring cage disposed around the bearing assembly, an axially-extending housing surrounding the spring cage, a first squeeze film damper formed between the bearing assembly and the spring cage, and a second squeeze film damper formed between the spring cage and the axially-extending housing. | 10-29-2009 |
| 20090285672 | Vibration-Absorbing Device for Blower Motors - Disclosed herein is a vibration-absorbing device for blower motors, which is provided between a blower motor and a motor housing surrounding the blower motor. The vibration-absorbing device includes a vibration-absorbing body, which may be spherical, and an engaging depression. The vibration-absorbing body is provided in the blower motor. The engaging depression is formed in the inner surface of the motor housing such that a vibration-absorbing body can be contained therein. | 11-19-2009 |
| 20090317235 | Vortex Blower - In the present invention, a partition wall which partitions a discharge port and a suction port provided on a static passage, in the rotating direction, has a discharge side shape which is identical with the shape of blades, and has a positional relationship in which the partition wall does not overlap with the discharge port in view of such a fact that the pressure variation on the suction side is higher than that of the discharge side, and noise on the suction side is dominant. | 12-24-2009 |
| 20090317236 | VIBRATION DAMPING NOVEL SURFACE STRUCTURES AND METHODS OF MAKING THE SAME - A gas turbine or turbine component partially or fully coated with a damping surface layer. The damping surface layer may have a thickness between 0.1 and 2000 microns and may be capable of dissipating vibration or modifying a resonance frequency of the gas turbine or turbine component at ambient room temperatures including operational temperatures greater than 500° F., and the damping surface layer comprises at least one of (a) at least two layers comprising a first layer of at least one hard material and a second layer comprising at least one soft material, (b) a composite comprising a nickel alloy with a heat softenable chemistry, (c) a fine-grained nickel-based superalloy, or (d) a porous metallic coating, a porous metallic and ceramic coating, or a ceramic coating. | 12-24-2009 |
| 20090317237 | SYSTEM AND METHOD FOR REDUCTION OF UNSTEADY PRESSURES IN TURBOMACHINERY - A turbomachinery system is provided. The system includes a first set of blades and a second set of blades moving relative to the first set of blades, wherein the second set of blades includes a first subset of blades having multiple first geometric parameters. The second set of blades also includes at least a second subset of blades non-uniformly spaced circumferentially and axially relative to the first subset of blades such that unsteady pressures generated from the wakes of the first set of blades interacting with the second set of blades is below an acceptable level. Further, the at least second subset of blades include multiple second geometric parameters that are different or identical to the multiple first geometric parameters. | 12-24-2009 |
| 20090317238 | COMBINED ACOUSTIC ABSORBER AND HEAT EXCHANGING OUTLET GUIDE VANES - An outlet guide vane assembly for turbomachines is provided. The outlet guide vane assembly comprises one or more outlet guide vanes, wherein each of the one or more outlet guide vanes comprises a first surface and a second surface, and wherein the one or more outlet guide vanes are disposed between an inner wall and an outer wall of an engine and a surface cooler layer disposed on at least a portion of the first surface, the second surface, or both of the one or more outlet guide vanes, wherein the surface cooler layer comprises a metal foam, a carbon foam, or a combination thereof, wherein the metal foam, the carbon foam or the combination thereof is configured to augment heat transfer and enhance acoustic absorption. | 12-24-2009 |
| 20090324390 | Liner for a gas turbine engine casing - A turbofan gas turbine engine ( | 12-31-2009 |
| 20100008762 | ENGINE BLOWER - An engine blower includes a centrifugal blower, an engine, and a frame for supporting the centrifugal blower. The centrifugal blower is supported by a back support of the frame via a flexible vibration-proofing section while being connected to the back support via a belt-shaped stopper. An engaging hole is provided on at least one of the centrifugal blower and the back support, and a thick engaging section is provided on at least one end of the stopper for being engaged with the engaging hole. When the stopper is inserted into the engaging hole and the one end of the stopper is pulled, the engaging section is engaged with the engaging hole. By further pulling the one end of the stopper, the engaging section is tightly buried into the engaging hole. Thus, the stopper can be reliably attached to the centrifugal blower or the back support. | 01-14-2010 |
| 20100028133 | TURBOMACHINE COMPONENT DAMPING STRUCTURE AND METHOD OF DAMPING VIBRATION OF A TURBOMACHINE COMPONENT - A turbomachine component includes a main body having a surface, and a damping structure mounted to the surface of the main body. The damping structure is formed from a material having a temperature dependent damping characteristic. | 02-04-2010 |
| 20100028134 | QUIET FAN INCORPORATING ACTIVE NOISE CONTROL (ANC) - An active noise control (ANC) system may be implemented to both sides of a fan, such that both directions of the noise emitting are treated to reduce the overall noise. The impact on airflow is minimal, and the technique is very effective in a broad range of low frequencies. Passive sound-absorbing materials may be included for attenuation of high frequencies. The resulting quiet fan produces a low level of noise compared to any other device based on fan, which produces the same capacity of airflow. The quiet fan may be incorporated in any mechanical system which requires airflow induction such as: computers, air conditioners, machines, and more. | 02-04-2010 |
| 20100028135 | Vibration damper - A vibration damper ( | 02-04-2010 |
| 20100040456 | CENTRIFUGAL FAN - A centrifugal fan includes a plurality of blades, a casing and a tongue. The casing includes a base plate perpendicular to a rotation axis of the blades and a sidewall extending upwardly from the base plate. The base plate and the sidewall cooperatively define a space for receiving the blades therein. The sidewall defines an opening in one side for functioning as an air outlet. An air channel is defined between outmost ends of the blades and the sidewall. The tongue is detachably mounted to one end of the sidewall adjacent to the air outlet. The tongue includes a guiding surface protruding towards the outmost ends of the blades. The tongues is provided for lowering a noise level of the centrifugal fan during operation. | 02-18-2010 |
| 20100054917 | Blade arrangement - Blade arrangements | 03-04-2010 |
| 20100054918 | METHOD FOR REDUCING THE VIBRATION LEVELS OF A PROPELLER OF A TURBINE ENGINE - The present invention relates to a method for reducing the vibration levels capable of occurring, in a turbine engine comprising at least one propeller and one coupling structure of the turbine engine, because of the turbulence of aerodynamic origin generated by the coupling structure on the propeller. The method comprises the following steps during the design of the aerodynamic profiles of the propeller and of the coupling structure: an initial configuration of the aerodynamic profiles is defined, the synchronous forced response on the propeller is calculated as a function of the force of harmonic excitation generated by the coupling structure expressed in the form of a linear function of the generalized aerodynamic force for the mode in question; for stacked sections of one of the propeller or of the coupling structure, a tangential geometric offset value θ of the individual aerodynamic profiles is determined in order to reduce the term corresponding to the generalized aerodynamic force. The combination of the sections with the tangential offsets therefore defines a new configuration of the aerodynamic profiles that is applied to the aerodynamic profiles of the propeller or of the coupling structure. | 03-04-2010 |
| 20100068036 | AUXILIARY POWER UNIT INLET DUCT WITH ACOUSTIC SILENCING - An inlet duct for an auxiliary power unit comprises an inlet end, and extends to an outlet end. At least one splitter is positioned within the duct and between the inlet and the outlet end to sub-divide an interior of the duct into plural flow paths. | 03-18-2010 |
| 20100074728 | FAN WITH SOUND-MUFFLING BOX | 03-25-2010 |
| 20100080689 | GAS TURBINE ENGINE ROTOR AND BALANCE WEIGHT THEREFOR - A balance weight for a rotor includes: (a) an arcuate body including a front wall and a rear wall interconnected by an end wall, the front, rear, and end walls collectively defining a generally U-shaped cross-sectional shape; and (b) a projection extending outwardly from the rear wall, the projection being adapted to engage an aperture extending through a flange of the rotor. | 04-01-2010 |
| 20100104421 | COOLING FAN - A cooling fan includes a housing, a cover on the housing and an impeller received in a space between the housing and the cover. The housing includes a bottom wall and a sidewall projecting upwardly from an outer periphery of the bottom wall. The sidewall defines an air outlet therein. The impeller includes a hub and a plurality of blades extending radially out from the hub. A porous layer extends into the space between the housing and the cover from the sidewall at a location adjacent to the air outlet. | 04-29-2010 |
| 20100111675 | FAN CASE FOR TURBOFAN ENGINE - A gas turbine engine rotor containment structure comprises an inner structurally supporting case having an inner surface positioned adjacent to a gas turbine engine rotor component to be contained. A layer of acoustic material is wrapped around and bounded to a radially outer surface of the inner case. A thin walled outer ring is bounded to a radially outer surface the layer of acoustic material. A layer of fibrous containment material surrounds a radially outer surface of the outer ring. | 05-06-2010 |
| 20100129203 | Control of shockwave-boundarylayer-interaction using MEMS plasma devices - A micro-electromechanical system (MEMS) dielectric barrier discharge (DBD) based aerodynamic actuator is configured to modify a shockwave boundary layer interaction and limit incident boundary layer growth caused by a reflected shockwave. | 05-27-2010 |
| 20100135774 | BALANCING FLYWEIGHT, ROTOR DISK EQUIPPED THEREWITH, ROTOR AND AIRCRAFT ENGINE COMPRISING THEM - The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts together. The two apexes are aligned on a longitudinal axis. The two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis. | 06-03-2010 |
| 20100143097 | AEROFOILS FOR GAS TURBINE ENGINES - An aerofoil | 06-10-2010 |
| 20100158671 | FAN DEVICE WITH A VIBRATION ATTENUATING STRUCTURE - A fan device with a vibration attenuating structure is disclosed. The fan device with a vibration attenuating structure comprises a fan and a frame covering the fan. The frame entirely covers the fan, and two opposing sides of the frame have an opening thereon. The openings are corresponding to blades of the fan to form the flowing path of the air. As above-mentioned, the frame performs as a buffering member for attenuating the vibration of the fan so as to prevent the noise generated by the vibration. | 06-24-2010 |
| 20100172740 | HEAT DISSIPATING DEVICE - A heat dissipating device includes a receiving bracket adapted to be mounted in an electronic device enclosure and a fan module accommodated in the receiving bracket. The fan module includes a fan and a mounting bracket connected to the fan. The fan is secured to the mounting bracket via a plurality of fasteners. Each fastener has a securing head. A plurality of vibration absorbers is disposed between the fan and the fastener. Each vibration absorber includes two isolating walls. One of the isolating walls is sandwiched by the fan and the mounting bracket, and the other isolating wall is sandwiched by the mounting bracket and the fastener securing head, so as to isolate the mounting bracket, the fan, and the fastener. | 07-08-2010 |
| 20100172741 | COMPRESSOR DEVICE - There is provided a compressor device in which resonance in a circulating channel is reduced so that an increase in noise generated from the compressor device is prevented. The compressor device includes: a plurality of blades rotated about a rotation axis; an air inlet extending along the rotation axis and introducing air to the blades; a circulating channel disposed on a circumference centered on the rotation axis and communicating between the air inlet and the shroud of the blades; and a strut extending radially centered on the rotation axis and dividing the circulating channel. Resonance frequencies determined from circumferential lengths in the circulating channels divided by the strut are higher than a noise frequency determined from the rotational speed of the blades and the number of blades. | 07-08-2010 |
| 20100172742 | Stator assembly for a rotary machine - A stator assembly having a windage cover for structure adjacent to a cavity bounded by rotating elements in a rotary machine is disclosed. Various construction details are developed for damping vibrations in the windage cover as the windage cover bounds a cavity having swirling high velocity gases that are capable of transmitting acoustic energy and kinetic energy to adjacent structure. In one detailed embodiment, the windage cover in the uninstalled condition has diverging arms that are resiliently compressed during installation to exert a frictional force on the adjacent structure. | 07-08-2010 |
| 20100189546 | FLUID EXPANSION DEVICE AND METHOD WITH NOISE ATTENUATION - A device or system through which fluid is adapted to flow, such as, for example, a fluid-carrying conduit, flow control valve, or fluid expansion device including, for example, a steam turbine or fluid expander, according to which acoustic energy is generated by, or present within, the device or system and the acoustic energy is attenuated. | 07-29-2010 |
| 20100189547 | Centrifugal Fan - A centrifugal fan used as a ventilating fan is provided which can increase a range of frequencies of noises in which noises can be suppressed and can adjust frequencies of noises at which noises can be suppressed. The centrifugal fan includes, in an outer casing, a motor that couples an impeller, a casing that surrounds a periphery of the impeller and has a bell-mouthed suction port on one side, and a bell-mouthed orifice that has an opening that is concentric with the suction port and has a diameter equal to or smaller than that of the suction port, wherein a member closing a clearance portion between an end of the orifice and the casing is a noise absorbing structural material, and a space formed by the orifice is a rear air layer, thereby forming a resonance type noise absorbing structure. | 07-29-2010 |
| 20100209230 | AIR CONDITIONING DEVICE FOR VEHICLE SEATS - The present invention concerns a fastening mechanism ( | 08-19-2010 |
| 20100215479 | GAS TURBINE ENGINE INLET WITH NOISE REDUCTION FEATURES - A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft. | 08-26-2010 |
| 20100226758 | FAN ASSEMBLY - A fan assembly for creating an air current includes a nozzle mounted on a base. The base includes an outer casing, a silencing member housed within the outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller about an axis to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly. The silencing member is located beneath the air inlet of the impeller housing and is spaced from the air inlet along said axis by a distance in the range from 5 to 60 mm. | 09-09-2010 |
| 20100232932 | AIR INLET SHROUD STRUCTURE - The present invention relates to a nacelle for a turbojet, comprising an air inlet structure capable of channelling a flow of air to a turbojet fan and a middle structure ( | 09-16-2010 |
| 20100232933 | AIR FAN DAMPING STRUCTURE - An air fan damping structure is installed on an air fan which has a fan frame. The fan frame has an air inlet, an air outlet and a housing space between them to hold a fan blade assembly. The damping structure includes a first buffer and a holding member located on the fan frame. The first buffer is hollow and has a through hole, and a first anchor portion to form an anchor relationship with a second anchor portion formed on the fan frame. The holding member has an inserting portion to run through the through hole and a depressing portion connecting to the inserting portion to receive a force to allow the inserting portion to run through the through hole. The inserting portion and the through hole have respectively a first retaining portion and a second retaining portion to form a retaining relationship. | 09-16-2010 |
| 20100254803 | Turbofan engine noise suppression using fan flow deflector - An embodiment of the invention is a technique to suppress noise in a jet engine. A substantially annular fan nozzle of a separate-flow turbofan engine includes a flow boundary surface and an outlet to discharge fan air into atmosphere. At least one vane extends substantially radially from the flow boundary surface to vector at least a portion of the fan air toward a direction where noise suppression is desired. The-vane is situated in proximity of the outlet and has a span substantially greater than a thickness of a local boundary layer of the fan air. | 10-07-2010 |
| 20100254804 | STATOR VANE ASSEMBLY - A stator vane assembly comprising: an inner vane support ( | 10-07-2010 |
| 20100260594 | VACUUM LINE - A vacuum line ( | 10-14-2010 |
| 20100266388 | FAN MOTOR APPARATUS FOR VACUUM CLEANER - A fan motor apparatus for a vacuum cleaner is provided. The fan motor apparatus may include a fan motor, an outer casing surrounding at least a part of the fan motor, wherein the outer casing includes a discharge portion having a discharge port; and, a noise-absorbent member is supported by the discharge port such that the port is closed, wherein the noise-absorbent member changes its shape to form a leakage space when internal exhaust pressure of the fan motor exceeds a predetermined degree. | 10-21-2010 |
| 20100278632 | Radial compressor of asymmetric cyclic sector with coupled blades tuned at anti-nodes - A gas turbine engine includes a radial compressor having first and second blades. The first blade has a tuned leading edge that prevents either blade from exciting at a natural frequency at speeds within an expected operating speed range. | 11-04-2010 |
| 20100278633 | Radial compressor with blades decoupled and tuned at anti-nodes - A gas turbine engine includes a radial compressor with first and second blades. The first and second blades have tuned leading edges that prevent natural frequencies from exciting at speeds within an expected operating speed range. | 11-04-2010 |
| 20100278634 | ROTARY MACHINE BALANCE WEIGHTS - In a one embodiment, a balance weight includes a base, a rotational axis extending from the base, and a circumference having opposite cam surfaces about the rotational axis. The opposite cam surfaces are at least partially angled toward one another in a direction away from the base along the rotational axis. The balance weight is designed to mount in a groove of a rotary component of a turbine engine. | 11-04-2010 |
| 20100278635 | Noise attenuation device for a centrifugal compressor discharge or suction nozzle - A centrifugal compressor discharge or suction nozzle is provided. The centrifugal compressor discharge or suction nozzle includes a side resonator integrally formed in the centrifugal compressor discharge or suction nozzle. Further, a centrifugal compressor discharge or suction nozzle formed as a pipe section piece adapted to be mounted on a centrifugal compressor, includes a side resonator integrated into the pipe section piece. Furthermore, a centrifugal compressor includes the centrifugal compressor discharge or suction nozzle and/or the pipe section piece. Additionally, a centrifugal compressor arrangement includes the centrifugal compressor. | 11-04-2010 |
| 20100278636 | MAGNETIC DEVICE FOR DAMPING BLADE VIBRATIONS IN TURBOMACHINES - An arrangement for damping blade vibrations in a turbomachine is provided. The blade vibrations are due to an arrangement made of magnets and multiple induction plates and the undesired vibrations of the blade are damped by creating turbulent flows, wherein the induction plates are directed parallel to the rotation axis, and the magnetic field caused by the magnets is formed homogenously in the circumferential direction. | 11-04-2010 |
| 20100284786 | Instability Mitigation System Using Rotor Plasma Actuators - An instability mitigation system is disclosed, comprising a rotor having a row of blades arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on a blade that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed. | 11-11-2010 |
| 20100284787 | INDIVIDUAL BLADE NOISE MEASUREMENT SYSTEM AND METHOD FOR WIND TURBINES - A method for configuring blades of a wind turbine for low noise generation. The method includes providing at least one noise measuring device. The noise measuring device is arranged and disposed in a position to measure noise of the blades during rotation. The wind turbine is configured to include a rotational trigger, the rotational trigger being arranged to provide a signal at a predetermined rotational position of the wind turbine blades. One or more of the blades is configured with an aerodynamic modifying device. Noise level is measured with the noise measuring device during wind turbine operation. The noise produced by each of the blades is determined. The blades are configured in response to the noise determined for each of the blades. A method for measuring the noise level generated by an individual blade and a wind turbine configured for desired noise level are also disclosed. | 11-11-2010 |
| 20100284788 | DUCT WALL FOR A FAN OF A GAS TURBINE ENGINE - A duct wall of a fan casing of a gas turbine engine comprises an intake section and a containment casing, which are interconnected by bolts at flanges. An acoustic flutter damper is provided between the flanges to reduce or eliminate flutter arising in blades of the fan at certain important operating conditions. The damper provides flexibility at the connection between the intake section and the containment casing so that, in the event of detachment of a blade or a bladed fragment, the resulting deflection wave in the containment casing can be accommodated by displacement and/or deformation of the acoustic flutter damper, reducing the risk that the bolts will shear to allow the intake section and the containment casing to become detached from each other. The acoustic flutter damper may comprise a circumferential array of separate segments. | 11-11-2010 |
| 20100284789 | DAMPING ASSEMBLY - Fan flutter is a significant problem with regard to gas turbine engines and can lead to premature failure and unacceptability with respect to engine operation. Traditional acoustic liners for noise abatement are formed to reduce environment noise. Fan flutter frequencies are typically much lower than community noise targeted by traditional acoustic liners, and therefore require different approaches with respect to attenuation. By altering the acoustic propensities of the intake duct, it is possible to increase the safe operating envelope of the engine. The flutter attenuators according to this invention are optimised so that they occupy the minimum area of the intake duct, and so can be accommodated more easily (without significantly compromising the area available for liners targeting community noise, for example). In such circumstances resonators for flutter frequencies are typically associated with existing acoustic liner and take the form of chambers incorporating labyrinthine cores for absorption of acoustic frequency waves or utilise Helmholtz chambers with appropriate volumes and inlet pipe aperture configurations for tuning to desired flutter frequencies to be attenuated. | 11-11-2010 |
| 20100284790 | DUCT WALL FOR A FAN OF A GAS TURBINE ENGINE - A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section. | 11-11-2010 |
| 20100290892 | INTAKE DUCT LINER FOR A TURBOFAN GAS TURBINE ENGINE - A turbofan gas turbine engine comprises a fan and an intake duct upstream of the fan. The fan comprises a fan rotor having a plurality of fan blades. The intake duct has a liner, the liner comprising an acoustic liner positioned upstream of the fan and a buzz-saw tone noise liner positioned upstream of the acoustic liner. The buzz-saw tone noise liner is positioned substantially at, or near, an upstream end of the intake duct. The intake duct has a lip and the buzz-saw tone noise liner is positioned at, or near, the lip. | 11-18-2010 |
| 20100290893 | AIRFOILS WITH VIBRATION DAMPING SYSTEM - The disclosure relates to adjacently mounted circumferentially distributed turbo machine airfoils with a vibration damping system. Each adjacent pair of airfoils includes a fixing and receiving portion, extending between the paired adjacent airfoils, each with a face that are proximal (e.g., in contact with) each other. Vibration can be suppressed by the fixing and receiving portions each having a received magnet fixingly installed therein and a non-magnetic conducting plate therebetween. Each magnet has a pole that faces the pole of the other magnet in between which the non-magnetic conducting plate is located and in which eddy currents can be induced by the relative movement of the magnets due to vibration. | 11-18-2010 |
| 20100329850 | EXTERNAL EXTRACTOR FAN FOR EXHAUST HOOD - An external fan for an extractor device, wherein the external fan includes a fan housing; a ventilator housing that is arranged in the fan housing and that has an air discharge; and a sound absorbing member that is arranged in the fan housing and that is opposite the air discharge of the ventilator housing. | 12-30-2010 |
| 20110002775 | CENTRIFUGAL FAN AND NOISE REDUCTION METHOD IN CENTRIFUGAL FAN - A centrifugal fan having a sound reduction effect for noises in a wide frequency range is provided. The centrifugal fan comprises a motor to which an impeller is connected, a casing which surrounds the impeller and which has a bell-mouth-like suction port, and a bell-mouth-like orifice which has a suction port being concentric with the suction port of the casing and having a diameter as large as that of the suction port of the casing, in an outer shell, providing a plurality of protrusions in a resonant space surrounded by the orifice, the casing, and the outer shell, and providing depressions which are formed so as to be interposed between the protrusions. | 01-06-2011 |
| 20110014031 | SEAL MEMBER, STEAM TURBINE, AND METHOD OF AVOIDING RESONANCE - A first seal member | 01-20-2011 |
| 20110027070 | SYSTEMS AND METHODS FOR REDUCING NOISE FROM JET ENGINE EXHAUST - An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis. | 02-03-2011 |
| 20110076135 | HIGH PRESSURE TURBINE OF A TURBOMACHINE WITH IMPROVED ASSEMBLY OF THE MOBILE BLADE RADIAL CLEARANCE CONTROL BOX - A high pressure turbine of a turbomachine such as a turbojet, in which a control box of radial clearances of rotating blades are provided. An annular element including a determined flexibility has one end fixed to an annular support and the other end supported by a simple axial bearing with a given pressure on the upstream side of the control box. Thus, disturbing vibration loads are prevented at the attachment points of the control box with the external casing of turbines, thereby also eliminating the risk of cracks occurring. | 03-31-2011 |
| 20110081231 | PUMP BEARING ARRANGEMENT - A pump bearing arrangement, suitable particularly for rapidly rotating pumps such as turbomolecular pumps, comprises a pump rotor ( | 04-07-2011 |
| 20110085889 | MECHANISM FOR ATTENUATING TORQUE PULSATIONS BETWEEN AN ENGINE AND A ROTORCRAFT ROTOR DRIVEN BY THE ENGINE - The invention provides a mechanism for attenuating torque pulsations between an engine ( | 04-14-2011 |
| 20110091313 | FAN ASSEMBLY WITH VIBRATION ABSORBING MEMBER - A fan assembly includes a chassis and a fan bracket secured in the chassis. The chassis has a bottom wall. The fan bracket includes a first sidewall and a second sidewall perpendicular to the bottom wall, and it is configured for securing the fans. A securing flange extends from an edge of the first sidewall, and is secured to the bottom wall of the chassis. A plurality of securing slots is defined in the securing flange. A plurality of first members engages in the securing slots and isolates the bottom wall of the chassis from the securing flange. | 04-21-2011 |
| 20110097193 | DEVICE FOR REDUCING VIBRATION GENERATED BY ROTORCRAFT ROTOR, AND ROTORCRAFT PROVIDED WITH SUCH DEVICE | 04-28-2011 |
| 20110097194 | Radial Compressor - A radial compressor for a turbo charger has a housing with an inflow passage and a spiral passage. A compressor wheel is supported rotatably in the housing. The housing has at least two housing parts between which a cavity is formed. At least one opening is provided in the inflow passage, wherein the at least one opening fluidically connects the cavity with the inflow passage. | 04-28-2011 |
| 20110103935 | AIRCRAFT ENGINE NACELLE AIR INTAKE ASSEMBLY - This aircraft engine nacelle air intake assembly comprises an air intake structure comprising an air intake lip ( | 05-05-2011 |
| 20110110762 | Damping Element for Reducing the Vibration of an Airfoil - An airfoil ( | 05-12-2011 |
| 20110110763 | Exhaust Ring and Method to Reduce Turbine Acoustic Signature - Embodiments of the disclosure provide a turbine, an exhaust ring, and a method of reducing the acoustic signature of a turbomachine. In an embodiment, the turbine includes an exhaust ring disposed downstream from at least one stage of rotor blades and upstream from at least one fluid flow obstruction. An embodiment of the exhaust ring includes exhaust guide vanes having camber angles that are varied in a predetermined manner that cause a fluid flow to be diverted around a downstream obstruction in a manner that suppresses formation of a bow wave at the obstruction. An embodiment of the method includes adjusting a camber angle of a portion of a plurality of vanes, the camber angle directing a fluid flow around at least one fluid flow obstruction in a manner that suppresses formation of a bow wave at the fluid flow obstruction. | 05-12-2011 |
| 20110135448 | FAN MODULE WITH VIBRATION-RESISTENT MOUNTING - A fan module includes a cooling fan, a support rack, and four fasteners fixing the cooling fan to the support rack. The fasteners are vibration-resistant material, and are disposed between the support rack and the cooling fan, and below the cooling fan. | 06-09-2011 |
| 20110150631 | TORSIONAL DYNAMIC DAMPER FOR A WIND TURBINE AND METHOD OF USING SAME - A wind turbine includes a tower, a nacelle located adjacent a top of the tower, a rotor coupled to the nacelle, and a dynamic vibration damper coupled to the tower and configured to dampen vibrations induced in the tower in a torsional direction while negligibly effecting vibrations induced in the tower in bending directions. The dynamic vibration damper may be tuned to a resonant frequency of the wind turbine in the torsional direction. A method of retrofitting a wind turbine with a vibration damper is also disclosed. | 06-23-2011 |
| 20110158791 | FAN ASSEMBLY WITH VIBRATION ABSORBING MEMBER - A fan assembly includes a chassis and a fan bracket secured in the chassis. The chassis has a bottom wall. The fan bracket comprises a strengthening fan bracket plate, a first fan bracket plate mounted to the strengthening fan bracket plate, and a second fan bracket plate parallel to the first fan bracket plate. The first fan bracket plate and the second fan bracket plate are configured for securing the fans. Each fan comprises a first sidewall. A plurality of vibration absorbing members are secured to the fan. Each vibration absorbing member comprises a head and a blocking portion, and the head is located between the strengthening fan bracket plate and the first fan bracket plate. The blocking portion is located between the first sidewall and the first fan bracket plate. | 06-30-2011 |
| 20110171006 | TURBINE ENGINE BYPASS FAN-BLEED NOISE REDUCTION - Apparatuses are provided for reducing noise generation from a dead ended conduit in a gas turbine engine. In particular A scooped bellmouth is provided that comprises a bellmouth within a surface having an outer perimeter an inner perimeter and a ramp diverging from the surface at a first end, the ramp extending radially through the outer perimeter of the bellmouth at a second end. The ramp diverts an airflow away from the bellmouth thereby preventing the development of a low pressure area at the bellmouth without affecting the efficiency of the gas turbine engine. | 07-14-2011 |
| 20110188995 | AXIAL LOAD DAMPING SYSTEM FOR ROTOR SHAFT - A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall. | 08-04-2011 |
| 20110200426 | NOISE REDUCTION DEVICES FOR BLOWERS - A noise reduction device for a blower includes a noise reduction member. The noise reduction member has a noise reduction chamber and a noise reduction opening defined therein, so that a part of air flowing into, through or out of the blower can enter the noise reduction chamber via the noise reduction opening. | 08-18-2011 |
| 20110223007 | RADIAL FAN WHEEL ARRANGEMENT - A radial fan wheel arrangement includes a circular bottom plate ( | 09-15-2011 |
| 20110223008 | TURBINE ENGINE FAN COMPRISING A BALANCING SYSTEM WITH BLIND HOLES FOR ACCOMMODATING MASSES - A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone. | 09-15-2011 |
| 20110243712 | Bearing Vibration Measuring Device for a Turbomachine - A bearing vibration measuring device for a turbo machine in which an outer housing and an inner housing are held concentrically at a distance from one another by way of at least one strut is provided. A bearing housing is disposed which is accessible from the outer housing through a radially extending access hole in the strut, the device includes a rod with an inner longitudinal end and an outer longitudinal end facing away from the inner longitudinal end, the rod being housed in access hole and being fastened at the inner longitudinal end to the bearing housing and including at least one vibration sensor on the outer longitudinal end. | 10-06-2011 |
| 20110255957 | FAN WITH REDUCED NOISE - Four tapered portions are formed on an end portion of an inner wall surface of an air channel at four locations corresponding to four corners of the profile of a surface of a housing where a suction port is formed. The four tapered portions are each inclined outwardly in a radial direction of a rotary shaft from a discharge port side toward the suction port side and extending in a rotational direction of an impeller. The tapered portions each include a main portion which is shaped such that an angle formed between the main portion and an axis of the rotary shaft gradually becomes smaller from one end of the main portion located rearward as viewed in the rotational direction of the impeller toward the other end of the main portion located forward as viewed in the rotational direction of the impeller. | 10-20-2011 |
| 20110268557 | SYSTEM AND METHOD FOR ATTENUATING THE NOISE OF AIRFOILS - A system and method for reducing the noise of an airfoil is provided. The airfoil includes a main portion including a leading edge and a trailing edge. The airfoil further comprises a noise attenuator coupled to the main portion and disposed proximate to at least a portion of the trailing edge. The noise attenuator has a chord length in the range of about 0.5 to about 5 times a trailing edge thickness and is fixed relative to the trailing edge. The airfoil can be a rotating blade deployed on a wind turbine. The airfoil can also be deployed on an aircraft as a fixed wing. | 11-03-2011 |
| 20110268558 | NOISE REDUCER FOR ROTOR BLADE IN WIND TURBINE - A rotor blade assembly for a wind turbine is disclosed. 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 tip and a root. The rotor blade assembly further includes a noise reducer mounted to a surface of the rotor blade, the noise reducer comprising a plurality of noise reduction features. The rotor blade assembly further includes a bond layer disposed between the noise reducer and the rotor blade for bonding the noise reducer to the rotor blade, the bond layer having a shear modulus approximately equal to or less than 500 megapascals. | 11-03-2011 |
| 20110318166 | Pulsation Damper Element for a Fluid Pump and Associated Fluid Pump - A pulsation damper element for a fluid pump with an elastic diaphragm and a fluid pump having such a pulsation damper element is disclosed. A pot-shaped diaphragm carrier with an elastic region is provided, the elastic diaphragm being introduced, fluid-tight, into the diaphragm carrier such that latitude of movement of the elastic diaphragm in the pressure direction is limited by the movable region of the diaphragm carrier. | 12-29-2011 |
| 20120020770 | ENERGY ABSORBING APPARATUS IN A GAS TURBINE ENGINE - A gas turbine includes a casing, a first diaphragm assembly, a second diaphragm assembly, and first energy absorbing apparatus. The casing has a radially outer surface and a radially inner surface including an annular slot extending circumferentially therein. The first diaphragm assembly includes a first inner structure, a first outer structure and a plurality of airfoils extending between the first inner and outer structures. The second diaphragm assembly includes a second inner structure, a second outer structure and a plurality of airfoils extending between the second inner and outer structures. The first energy absorbing apparatus engages a first end portion of the first outer structure so as to absorb at least portions of unsteady aerodynamic loads and steady rotational loads generated by the first diaphragm assembly. | 01-26-2012 |
| 20120027571 | Fan and vibration-absorbing boss thereof - A fan including a hub part, a blade part and a vibration-absorbing boss, all constituent elements of which are injection molded, thereby reducing production costs. The fan has a minimized contact area between the vibration-absorbing boss and the hub part to prevent the vibration-absorbing boss from being deformed by high-temperature heat during insert injection molding of the hub part and the blade part while assuring sufficient strength of the hub part. | 02-02-2012 |
| 20120057962 | FAN ARRAY FAN SECTION IN AIR-HANDLING SYSTEMS - A fan array fan section in an air handling system includes a plurality of fan units arranged in a fan array and positioned within an air handling compartment. One preferred embodiment may include an array controller program to operate the plurality of the fan units at peak efficiency. The plurality of fan units may be arranged in a true array configuration, a space pattern array configuration, a checker board array configuration, rows slightly offset configuration, columns slightly offset configuration, or a staggered array configuration. | 03-08-2012 |
| 20120057963 | COMPRESSOR OF AN EXHAUST-GAS TURBOCHARGER - The present invention relates to a compressor ( | 03-08-2012 |
| 20120057964 | IMPELLER TYPE WATER-HAMMER PROOF AND SILENT CHECK VALVE - An impeller type water-hammer proof and silent check valve includes a shell ( | 03-08-2012 |
| 20120063886 | Anti-Vibration Fan - The fan of the invention includes a frame and a vibration absorber. The frame has a fixing recess at a corner thereof. The vibration absorber has an elastic body fastened in the fixing recess and a pin with a circular trough. A portion of the elastic body protrudes from the frame. The pin is fixed at the portion of the elastic body for fastening the frame on a panel. | 03-15-2012 |
| 20120070270 | DAMPED ASSEMBLY - A damped assembly | 03-22-2012 |
| 20120099962 | Rotor For Turbomachines - A rotor for turbomachines having a plurality of blades, and wherein a damping member, housed inside a respective chamber arranged between the two blades of each pair of adjacent blades of said rotor, is pushed, in use, by the centrifugal force against two surfaces, each of which is carried by a respective blade, which limit the respective chamber in a radially outward direction; the damping member being cup-shaped and being provided with a base wall facing the two surfaces of the relative chamber and having three support bosses on both of said surfaces. | 04-26-2012 |
| 20120107095 | GAS TURBINE ENGINE TRIM BALANCE - A trim balance for a gas turbine engine having a hollow rotatable rotor shaft includes an elongate support rod adapted for longitudinal accommodation within and mounting on an interior surface of the rotor shaft and one or more apertured balance weights supported on the support rod which extends through the weight apertures and a weight retainer for retaining the weights on the support rod. | 05-03-2012 |
| 20120107096 | AIR EXCHANGE FAN AND CIRCUIT BOARD BOX THEREFOR - An air exchange fan comprises: a frame with an opening, a helicoid housing with an air suction inlet disposed in the frame, an air blower disposed in the housing, and, an elongated circuit board box mounted at the air suction inlet side of the housing; a silencing plate is mounted above the outer peripheral of the inlet, and has a streamlining structure formed by outwardly expanding from the inlet in an axial direction of a rotation axis of the air blower, the rotation axis of which being served as the center, within a range that is from a tongue of the housing to a location with a 90 degrees angled from the tongue in a direction opposing to the rotation direction, and has a curved chamfered shape which mates with the peripheral shape of the inlet. A circuit board box for such air exchange fan is also disclosed. | 05-03-2012 |
| 20120114461 | FAN MODULE AND VIBRATION-DAMPING MOUNTING THEREFOR - A fan module with vibration-damping mounting includes a cooling fan, a support frame and a clip detachably fixing the cooling fan to the support frame. The clip includes a mounting portion fixed to the support frame, fixing portions supporting the cooling fan, and vibration reducing portions. Each of the vibration reducing portions is connected between a corresponding fixing portion and the mounting portion. The fixing portions are spaced from the support frame, to prevent a vibration of the cooling fan from being transferred to the support frame. | 05-10-2012 |
| 20120121384 | ROTOR AND METHOD FOR MANUFACTURING A ROTOR FOR A TURBO MACHINE - The invention relates to a rotor for a turbo machine, having rotating blades ( | 05-17-2012 |
| 20120148384 | PUMP HAVING AN AXIAL BALANCING DEVICE - The pump comprises a stator ( | 06-14-2012 |
| 20120156006 | ACOUSTIC LINER - An acoustic liner for a gas turbine engine comprises a folded cavity with an opening and a resistive facing sheet covering the opening, characterised in that the folded cavity further comprises a resistive septum that increases attenuation at high frequencies. The presence of the septum permits the attenuation of noise over a much wider range of frequencies than in known liners. By suitable choice of the resistance and reactance of the septum and of its position in the cavity, the liner can provide low frequency attenuation comparable with known liners while also providing improved attenuation at higher frequencies. | 06-21-2012 |
| 20120189429 | BEARING SYSTEM FOR GAS TURBINE ENGINE - A bearing system for a gas turbine engine includes a spring defined about an axis of rotation. The spring has a multiple of beams which extend between a flange structure and an attachment structure. A damper defined about the axis of rotation and mounted to the spring to at least partially axially overlap the multiple of beams. | 07-26-2012 |
| 20120195738 | SHOCKPROOF FAN APPARATUS - A fan apparatus includes a fan, a shockproof unit, and a case. The fan includes two plates, and a through hole is defined on each plate. The shockproof unit includes a pole penetrating the two though holes, and at least a flange is defined on the pole; at least an elastic element is restricted between one of the plates and the flange. Two ends of the pole protrude from the through holes and abut on the case when the fan is received in the case. A concave groove is defined on each end of the pole; the concave groove protrudes one of the through holes and received in a sleeve abutting on the case; a containing hole is defined in the sleeve to receive the end of the pole. | 08-02-2012 |
| 20120195739 | ATTENUATION OF OPEN ROTOR NOISE - An aeronautical propulsor has a core engine, one or more open rotors driven by the engine, and a nacelle which encloses the core engine and provides an aerodynamic external surface. At least a portion of the external surface of the nacelle is acoustically treated to attenuate noise produced by the open rotors. | 08-02-2012 |
| 20120275901 | FAN ASSEMBLY FOR VEHICLES - A fan assembly comprising, a shroud having a through opening, around which the shroud defines an air conveying ring, a motor-fan assembly which includes an axial fan rotatable with respect to the support about an axis of rotation, and a noise-reducing annular structure, having a plurality of projections which are arranged in succession in a circumferential direction and extend radially towards the axis of rotation of the fan, each projection having a face which is directed towards the axis of rotation and is substantially parallel thereto, and a plurality of portions radially recessed towards the air conveying ring. Each of the recessed portions has a face which is directed towards the axis of rotation of the fan and the profile of which in the axial direction is generally curvilinear and not parallel to the axis of rotation. | 11-01-2012 |
| 20120275902 | MODULAR FAN HOUSING WITH MULTIPLE MODULAR UNITS HAVING SOUND ATTENUATION FOR A FAN ARRAY FOR AN AIR-HANDLING SYSTEM - A modular fan housing configured to hold an array of motors and fans is provided. The modular fan housing is configured for use in an air-handling system that delivers air to a ventilation system for at least a portion of a building. The fan housing comprises a plurality of modular units configured to be stacked adjacent to one another in at least one row or column to form an array. The modular units each include an interior surface and have a front end and a back end that define a chamber. The chambers are configured to receive the motors and fans. Sound attenuation layers extend along at least a portion of the interior surface of the corresponding chambers. The sound attenuation layers are positioned between at least some of the adjacent chambers. | 11-01-2012 |
| 20120282082 | Gas-turbine balancing device - The present invention relates to a gas-turbine balancing device with at least one annular groove provided on the outer circumference of at least one intermediate or high-pressure rotor of an intermediate or high-pressure compressor, with at least one balancing element being arranged in the annular groove, and with the balancing element being moveable in the circumferential direction along the annular groove and provided with a fixing device. | 11-08-2012 |
| 20120301277 | FAN - A fan includes a housing, an impeller and at least one position-limiting mechanism. The housing has an accommodating space for receiving the impeller. The impeller has a hub and a plurality of blades surrounding the hub. The position-limiting mechanism is located between the top of the blade and the inner side of the housing, and disposed on the top of the blade or the inner side of the housing. | 11-29-2012 |
| 20120308361 | CENTRIFUGAL ELECTRIC PUMP FOR SUCTION OF AERIFORM FLUIDS WITH SILENCING DEVICE - A centrifugal electric pump for suction of aeriform fluids includes an electric motor equipped with a shaft; a cylindrical suction box provided with an inlet for the aeriform fluid, one or more outlet openings arranged on the lateral wall thereof and with a closing cover; at least one fan driven in movement by the motor, arranged for sucking a flow of air from the inlet, centrifuge it and discharge it outside the suction box through the one or more outlet openings, a silencing device arranged inside the suction box. The silencing device includes an annular deflector, placed in front of the outlet openings, so as to interrupt the direct path of the flow of centrifuged air between the at least one fan and the outlet openings, and arranged for creating a shaped annular damping chamber for the flow of centrifuged air, open towards the suction inlet. | 12-06-2012 |
| 20120321443 | TIP TREATMENT FOR A ROTOR CASING - A tip treatment bar and associated rotor casing structure, wherein the tip treatment bar includes a solid composite structure having a plurality of layers arranged therein so as to provide the bar with a directional stiffness characteristic. Such a layered composite arrangement can be used to tailor the vibration characteristics of the bar. The tip treatment bar and casing structure may be suited for mounting relative to a fan or compressor in a gas turbine engine. | 12-20-2012 |
| 20120328415 | VIBRATION DAMPER COMPRISING A PEG BETWEEN OUTER PLATFORMS OF ADJACENT COMPOSITE-MATERIAL BLADES OF A TURBINE ENGINE ROTOR WHEEL - A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts. | 12-27-2012 |
| 20130011239 | TUBULAR INLINE EXHAUST FAN ASSEMBLY - An improved exhaust fan housing, and exhaust fan assembly so characterized, is generally provided. The exhaust fan housing includes a first cylindrical or conical element, a second cylindrical element interior of the first cylindrical element, and a plurality of hollow vanes traversing an annular fluid passage chamber delimited thereby and uniting the first and second cylindrical elements. A central drive chamber, delimited by the second cylindrical element, is in fluid communication with ambient air exterior of the first cylindrical element via the hollow vanes. Each hollow vane is characterized by spaced apart wall segments which unitingly terminate so as to delimit a leading edge for each hollow vane, each of the spaced apart wall segments having a free end or a closed end delimiting first and second trailing edges for the hollow vanes. | 01-10-2013 |
| 20130028709 | FAN MODULE - A fan module includes a cooling fan, a supporting rack, and a number of fasteners sandwiched between the cooling fan and the supporting rack. The fasteners are made of vibration-resistant material. The supporting rack includes two opposite supporting walls. An installing portion protrudes out from a top of each supporting plate. Each fastener is sandwiched between the cooling fan and the corresponding installing portion. An extension portion extends from each fastener to resist against an outside surface of the cooling fan. | 01-31-2013 |
| 20130028710 | COMPACT LOW NOISE EFFICIENT BLOWER FOR CPAP DEVICES - A blower includes an electric motor having a shaft, a housing having an inlet and outlet between which is defined a gas flow path, the outlet structured to direct gas exiting the blower in an axial first direction, a first impeller attached to the shaft and adapted to accelerate air tangentially and direct it radially outward, a stationary portion, and a shield. The stationary portion includes a first stator vane structure defining a plurality of stator vane leading edges and a stator vane outer radial edge. The first stator vane structure is arranged to direct gas flow along a curved path that directs flow at an inner end thereof in a radially inward direction. The shield has an outer edge extending radially beyond the outer radial edge of the first stator vane structure and is adapted to isolate the stator vane leading edges from an impeller blade pressure pulse. | 01-31-2013 |
| 20130045084 | LOW-NOISE BLADELESS FAN - A low-noise bladeless fan includes a base, a nozzle at the top of the base and noise-reduction components located within the base. The noise-reduction components include a first noise-reduction component, a second noise-reduction component and a third noise-reduction component. The first noise-reduction component is located at an interface between air outlets and an internal passage for airflow reduces noise by isolating, obstructing and separating noise created inside the outer casing. The second noise-reduction component is disposed within an impeller fixture reduces noise by absorbing noise created inside the outer casing. Through-holes are disposed in the bottom of the outer casing act as the third noise-reduction component and also reduce noise. The arrangement of noise-reduction components can reduce noise created in the fan, thereby cooling users with natural and soft wind. | 02-21-2013 |
| 20130045085 | Motor suspension for fans, preferably axial-flow fans, as well as method for manufacturing an air grille of such a motor suspension - A motor suspension for fans has an air grille with radially extending braces and grille rings that are positioned coaxially to each other and are connected to each other by the radially extending braces. For adapting the motor suspension to a vibration behavior of a fan, at least one of a feature selected from a number of the braces and a diameter of the braces is varied to effect a reduction of acoustic noises and/or natural resonances of the motor suspension. The number of the braces that are preferably made of metal is preferably unequal to the number of vanes of the fan. | 02-21-2013 |
| 20130051981 | GAS TURBINE ENGINES INCLUDING BROADBAND DAMPING SYSTEMS AND METHODS FOR PRODUCING THE SAME - Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine. | 02-28-2013 |
| 20130051982 | ANNULAR BEARING SUPPORT DAMPERS, GAS TURBINE ENGINES INCLUDING THE SAME, AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a gas turbine engine are provided, as are embodiments of an annular bearing support damper and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine includes engine housing and a rotor assembly disposed within the engine housing. A rotor bearing supports the rotor assembly within the engine housing, and an annular bearing support damper is positioned between the rotor bearing and the engine housing. The support damper includes an annular housing assembly having a damping fluid annulus. An array of circumferentially-spaced damper pistons is movably coupled to the annular housing assembly and fluidly communicates with the damping fluid annulus. The damper pistons are fixedly coupled to the rotor bearing and moves in conjunction therewith to force the flow of damping fluid around the annulus during engine operation to reduce the transmissions of vibrations to the engine housing. | 02-28-2013 |
| 20130071231 | WALL STRUCTURE WITH NOISE DAMPING INSULATION PROPERTIES AND GAS TURBINE WITH SUCH A WALL STRUCTURE - A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided. | 03-21-2013 |
| 20130094941 | VARIABLE-CAPACITY COMPRESSOR - Variable displacement compressor is provided with a displacement control valve ( | 04-18-2013 |
| 20130101395 | TURBINE BLADE RAIL DAMPER - A device for damping of vibratory energy in the blades of rotor assemblies during operation where the blades have a shroud attached thereto with at least one sealing rail extending radially outward from the shroud to an outer diameter surface. A damper element is attached to the turbine blade sealing rail extending radially inward from the rail outer diameter surface along rail sides to maintain the damper element out of the flow of gas and positioned at a radial location on the blade for damping. | 04-25-2013 |
| 20130101396 | FAN ASSEMBLY - A fan assembly includes a fan and a casing receiving the fan. The casing is formed by one-step injection molding and includes a base portion, a cover portion, a connection portion, and a plurality of anti-vibration members. The connection portion is formed by thermal-pressing and rotatably connects the cover portion and the base portion. The anti-vibration members are attached to the cover portion and the base portion and located between the fan and the cover portion and the base portion when the cover portion and the base portion are locked together to absorb vibration and prevent the transmission of the vibration to the casing. | 04-25-2013 |
| 20130115051 | GAS TURBINE EXHAUST CASE WITH ACOUSTIC PANELS - A turbine exhaust case for a gas turbine engine has an outer shroud and an inner shroud concentrically defining therebetween an annular gaspath for channelling hot gases. A plurality of circumferentially spaced-apart turbine exhaust struts extends radially across the hot gaspath. The inner shroud may be provided in the form of an acoustic panel. The acoustic panel has a radially outwardly facing surface defining the radially inner flow boundary surface of the gaspath. The acoustic panel is mechanically fastened to the radially inner end of the struts. | 05-09-2013 |
| 20130115052 | DIFFUSER BLOCK AND DIFFUSER COMPRISING SAID DIFFUSER BLOCKS COMBINED WITH ONE ANOTHER - Provided is a diffuser block used to form a diffuser with a plurality of the diffuser blocks, the diffuser block including: a body having a tube shape including an inner space provided inside the body, an inlet through which a fluid flows into the inner space and an outlet through which the fluid flows out of the inner space; and a first vane portion which protrudes toward the inner space from one side of the body. | 05-09-2013 |
| 20130129483 | CRACK AND DELAMINATION STOPPERS FOR AIRCRAFT PROPULSION SYSTEM COMPONENTS - An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin. | 05-23-2013 |
| 20130142624 | MULTI-LAYER ACOUSTIC TREATMENT PANEL - A multilayer acoustic treatment panel including a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; and a second cellular-structure core sandwiched between the intermediate skin and a continuous skin. The perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with the two ends of a soundwave flow channel arranged in the second cellular-structure core. | 06-06-2013 |
| 20130149108 | BLADE - A blade having a root portion and an aerofoil portion, wherein the aerofoil portion has a tip remote from the root portion, and a leading edge and a trailing edge, and wherein the tip of the aerofoil portion has a set-back portion extending from the leading edge or the trailing edge of the aerofoil portion part way towards the respective other edge and set back from the remainder of the tip of the aerofoil portion towards the root portion. | 06-13-2013 |
| 20130149109 | METHOD OF DAMPING AEROFOIL STRUCTURE VIBRATIONS - The method described herein includes providing an aerofoil structure having a root portion and an aerofoil portion, wherein the aerofoil portion has a tip remote from the root portion. In certain aspects, the tip of the aerofoil structure can be substantially surrounded by a casing with a clearance gap between the tip and the casing. In certain aspects, the method described herein includes disposing the aerofoil structure relative to the casing such that an oscillation of the aerofoil structure from an unperturbed position in a first direction reduces the clearance gap and that an oscillation from the unperturbed position in a second direction increases the clearance gap. In certain aspects, the method further includes disposing the aerofoil structure such that the frequency of the clearance gap variation is equivalent to the frequency of the aerofoil structure vibration and permits a flow through the clearance gap in which the flow tends to dampen the aerofoil structure vibrations. | 06-13-2013 |
| 20130177400 | STATOR VANE INTEGRATED ATTACHMENT LINER AND SPRING DAMPER - A stator subassembly includes an array of circumferentially arranged stator vanes. An attachment liner secures the stator vanes to one another to provide the subassembly. A damper spring is integral with the attachment liner and is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case. | 07-11-2013 |
| 20130177401 | STATOR VANE SPRING DAMPER - A stator subassembly includes an array of circumferentially arranged stator vanes. A damper spring is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case. | 07-11-2013 |
| 20130183141 | AIR MOVING DEVICES - Disclosed herein is an air moving device which includes a housing and a motor. The air moving device may include at least one shock absorber which is configured to reduce vibrations and/or noise. The air moving device may also be configured to cancel out noises generated when operating the device. | 07-18-2013 |
| 20130195622 | ANTI-VIBRATION SERIAL FAN STRUCTURE - An anti-vibration serial fan structure includes a first frame having a first assembling side and a second frame having a second assembling for connecting to the first assembling side. The first assembling side is provided with at least one mounting post or mounting hole and at least one male or female connector. The second assembling side is correspondingly provided with at least one mounting hole or mounting post and at least one female or male connector. The male connector has a certain degree of elasticity, so that the engaged male and female connectors provide a vibration-absorbing effect to save additional cushioning elements, enabling the serial fan structure to have lowered assembling cost and minimized defects in assembling. | 08-01-2013 |
| 20130223988 | ARRANGEMENT TO REDUCE NOISE ORIGINATED BY A WIND TURBINE BLADE - An arrangement for reducing noise which is generated by a wind turbine blade is provided. The wind turbine blade has a first panel and a second panel. The first and the second panel are arranged at a trailing edge of the wind turbine blade, wherein the first panel is adjacent to the second panel. The first panel includes a first transition zone and the second panel includes a second transition zone. The first transition zone and the second transition zone are engaged in a way that whistle tones produced by a gap of the wind turbine blade, the gap being located between the first panel and the second panel, is reduced or even avoided. | 08-29-2013 |
| 20130223989 | ACOUSTIC DAMPER, COMBUSTOR AND GAS TURBINE - An acoustic damper of the present invention is objected to obtain a sound absorption effect of a combustor in an extensive range of frequency band. The acoustic damper includes an acoustic pipe body attached to a combustor so as to communicate with an inside of the combustor, and the acoustic pipe body is provided with a plurality of passages whose extension lengths are different from each other inside the acoustic pipe body. | 08-29-2013 |
| 20130223990 | ANGULAR SECTOR OF A STATOR FOR A TURBINE ENGINE COMPRESSOR, A TURBINE ENGINE STATOR, AND A TURBINE ENGINE INCLUDING SUCH A SECTOR - A stator angular sector for a turbine engine compressor including: an outer shroud and an inner shroud, and at least one vane extending radially between the shrouds. The outer shroud includes first and second mounting mechanisms for mounting the stator angular sector on a casing of the engine, which mechanisms are oriented parallel to the axis in opposite directions and connected together by an intermediate portion. The outer shroud includes at least one axial end portion extending from the intermediate portion with which at least one damper-forming insert is configured to come into contact, such that beyond a given value for amplitude of vibration of the end portion, the damper insert and the end portion are configured to move relative to each other to vary total moving mass moving with the end portion, thereby modifying vibratory behavior of the end portion. | 08-29-2013 |
| 20130236292 | BALANCE CORRECTION WEIGHT PROVIDING CONSTANT MASS - A system is provided for balancing a movable turbine part of a turbine or of a compressor. The system includes a balancing weight element with a first hole and a second hole and a fixing element. The first hole and the second hole are formed in such a manner that the fixing element is detachably insertable in either the first hole or the second hole. The first hole is formed in such a manner that the inserted fixing element in the first hole detachably couples the balancing weight element to the movable turbine part in a spatially fixed position. The second hole is formed in such a manner that the fixing element is receivable in the second hole. | 09-12-2013 |
| 20130251510 | SPF/DB STRUCTURE FOR ATTENUATION OF NOISE FROM AIR FLOW - A propulsion system comprises a turbine engine, and an engine nacelle including an SPF/DB inner wall having a hot side face sheet against the engine and a cold side face sheet that has noise attenuation openings. | 09-26-2013 |
| 20130280045 | AIRFOIL INCLUDING DAMPER MEMBER - 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 sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location. | 10-24-2013 |
| 20130280046 | BYPASS TURBOJET - A bypass turbojet including a fan wheel carrying blades and surrounded by an annular casing, the casing including an air suction mechanism sucking air from an annular clearance formed between the casing and radially outer ends of the blades of the fan wheel. The air suction mechanism includes an inlet including at least one inlet slot formed in an inside wall of the casing and connected to a suction channel extending downstream. The inlet slot of the suction mechanism is situated axially in register solely with upstream portions of chords of the blades of the fan wheel at their radially outer ends. | 10-24-2013 |
| 20130294891 | METHOD FOR THE GENERATIVE PRODUCTION OF A COMPONENT WITH AN INTEGRATED DAMPING ELEMENT FOR A TURBOMACHINE, AND A COMPONENT PRODUCED IN A GENERATIVE MANNER WITH AN INTEGRATED DAMPING ELEMENT FOR A TURBOMACHINE - The invention provides a method for the generative manufacture of a component ( | 11-07-2013 |
| 20130309064 | FAN WITH INTEGRATED VIBRATION ABSORBING STRUCTURE - A fan with integrated vibration absorbing structure includes a fan frame, a hub-blade assembly, and at least one vibration absorber. The fan frame includes a base and at least one side wall formed around the base, and the hub-blade assembly is arranged in the fan frame. The at least one vibration absorber is provided on the at least one side wall to project therefrom for absorbing vibration produced by the fan during the operation thereof. Therefore, with the vibration absorbers integrated into the fan frame, it is no longer necessary to provide any additional vibration-absorbing member while upgraded vibration-absorbing effect can be achieved. Meanwhile, the fan can be more conveniently mounted at reduced mounting cost. | 11-21-2013 |
| 20130309065 | FAN - 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. A noise suppression cavity is located beneath the air inlet of the duct. The cavity has an inlet which is located beneath, and is preferably concentric with, the air inlet of the duct. | 11-21-2013 |
| 20130309066 | FAN - 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 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 a first end defining an air inlet of the duct and a second end located opposite to the first end and defining an air outlet of the duct, an impeller located within the duct for drawing the air flow through the duct, and a motor for driving the impeller. The second end of the duct protrudes from the body into the interior passage of the nozzle. | 11-21-2013 |
| 20130343876 | SPHERICAL-LINK END DAMPER SYSTEM WITH NEAR CONSTANT ENGAGEMENT - A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis. | 12-26-2013 |
| 20140010636 | Motor Base - A motor base includes a bottom plate and at least one vibration reduction unit. The bottom plate has opposite top and bottom surfaces. A shaft-coupling portion is arranged on the top surface. The at least one vibration reduction unit encloses the shaft-coupling portion. Each of the at least one vibration reduction unit includes at least one protrusion and at least one groove. The at least one protrusion is arranged on one of the top and bottom surfaces. The at least one groove is correspondingly arranged on the other one of the top and bottom surfaces. | 01-09-2014 |
| 20140050566 | BALANCE WEIGHT INSTALLATION SYSTEM AND RELATED METHOD - Systems, methods, and devices, adapted to ease installation of balance weights about a turbine are disclosed. In one embodiment, a device includes: a base including a hollow feature and an operative tip configured to connect to a balance weight; and an inner component disposed within the hollow feature of the base, the inner component including an inner tip at a first end, the inner tip configured to manipulate a set screw connected to the balance weight. | 02-20-2014 |
| 20140056693 | FAN AND FAN FRAME THEREOF - A fan includes a fan frame and a fan wheel . The fan frame includes a frame body and at least two vibration-proof members. The frame body has at least two positioning ribs, wherein the at least two positioning ribs protrude from a side wall of the frame body and are distributed symmetrically. Each of the vibration-proof members has a positioning groove. The positioning rib of the frame body is capable of being embedded in the positioning groove of the vibration-proof member so as to position the vibration-proof member on the side wall of the frame body. The fan wheel is rotatably disposed in the fan frame. | 02-27-2014 |
| 20140056694 | FAN ASSEMBLY - A fan assembly includes a first fan module and a second fan module arranged in parallel, and a shock absorber mounted between the first and second fan modules. A cavity is defined in a middle of the shock absorber, for counteracting and absorbing vibrations created by the first and second fan modules. | 02-27-2014 |
| 20140064927 | INLET SECTION OF AN AIRCRAFT ENGINE NACELLE - A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange. | 03-06-2014 |
| 20140064928 | Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region - The present invention relates to an engine casing of an aircraft gas turbine having a radially inner honeycomb-structured layer arranged on the engine casing in the flow direction upstream of a fan in the area of an inflow-side air inlet, characterized in that sound-absorbing elements are arranged radially outside at least one axial section of the honeycomb-structured layer, said elements extending in the axial direction and being arranged annularly next to one another in the circumferential direction. | 03-06-2014 |
| 20140072406 | FAN STRUCTURE WITH EASY ASSEMBLY - A fan structure includes at least one installation standoff, a fan and a fixing frame. An end of the at least one installation standoff is installed on a substrate, and a positioning slot is formed on the other end of the at least one installation standoff. The fixing frame is installed on the fan and includes at least one positioning hook for engaging with the positioning slot of the at least one installation standoff, so as to fix the fixing frame on the substrate. A guiding slot is formed on at least one side of the fixing frame for guiding the at least one installation standoff to move on the fixing frame. The fixing frame further includes at least one resilient portion connected to the at least one positioning hook for driving the at least one positioning hook to separate from the at least one positioning slot. | 03-13-2014 |
| 20140072407 | FILLED STATIC STRUCTURE FOR AXIAL-FLOW MACHINE - A stator assembly for a rotary machine having a rotor arranged to rotate about an axis in use. The stator assembly has a circumferential support member or casing arranged about said axis and a plurality of elements extending in a substantially radial direction from the support. The elements have a platform at an end thereof for engagement within the support, wherein the elements each comprise a hollow internal cavity having an opening through the platform at the end of the element, wherein said internal cavity is filled with a vibration damping material. The elements may be filled vanes in a gas turbine engine compressor. The platforms may also be filled with the vibration damping material. | 03-13-2014 |
| 20140079537 | Balance Ring for Gas Turbine Engine - A ring has a ring body with a central portion surrounding an axis and extending to first and second opposing ends separated by a split. The central portion has a first axial thickness. At least one retaining feature is formed on the ring body, the at least one retaining feature having a second axial thickness greater than the first axial thickness. An assembly and a gas turbine engine are also disclosed. | 03-20-2014 |
| 20140086728 | Fan Diffuser Having a Circular Inlet and a Rotationally Asymmetrical Outlet - A diffuser ( | 03-27-2014 |
| 20140086729 | METHOD AND APPARATUS FOR INDEPENDENTLY VARYING AIRFLOW AND NOISE GENERATION OF A FAN - A fan design method and fan structure is described, enabling independent control of the volume of airflow and the amount of noise produced. The noise produced is a close approximation to a pleasing red noise spectrum, and is generated solely by the interaction of the rotating fan blades with a petal assembly or a fan enclosure in several embodiments. A petal assembly may be positioned at varying spacings behind the rotating fan blades to control the level of noise production with minimal effect on the volume of airflow. Various aspects of the fan blade configuration, such as the blade pitch, camber, span, chord, etc., may be manipulated to control the ratio of airflow volume to the amount of noise produced. | 03-27-2014 |
| 20140112760 | REDUCTION OF EQUALLY SPACED TURBINE NOZZLE VANE EXCITATION - 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. | 04-24-2014 |
| 20140112761 | FAN ASSEMBLY - A fan assembly includes a hollow support rack, a fan, and a shockproof member. The shockproof member is made of vibration-resistant material. The shockproof member defines a through hole. The fan is inserted into the through hole and deforms an inner wall bounding the through hole out. The shockproof member wraps the fan. A combination of the shockproof member and the cooling fan is retained in the support rack. | 04-24-2014 |
| 20140119890 | TURBO-COMPRESSOR - A turbo-compressor | 05-01-2014 |
| 20140126997 | SOUND ATTENUATING CHIMNEY ELEMENT FOR A TURBOMACHINE SYSTEM - A sound attenuating chimney element for a turbomachine system includes a high density outer body having an external surface and an internal surface, and one or more acoustic attenuation layers provided on the external surface of the outer body. The one or more acoustic attenuation layers include an outer surface portion and an inner surface portion. A structural layer is provided on the outer surface portion of the one or more acoustic attenuation layers. The structural layer includes an external surface that defines a duct configured and disposed to pass gases from the turbomachine system. | 05-08-2014 |
| 20140133964 | ACOUSTIC STRUCTURE WITH INTERNAL THERMAL REGULATORS - Thermally insulating septums are located internally within the cells of an acoustic honeycomb to regulate heat flow into the acoustic structure. The internally located insulating septums protect the honeycomb and acoustic septums located within the honeycomb cells from heat damage that might otherwise be caused by a heat source, such as the hot section of a jet engine. The internal thermal regulators are useful in combination with heat blankets or other thermal insulating structures to provide a reduction in size and/or weight of the insulating structure while still providing the same overall degree of thermal insulation for the acoustic honeycomb. | 05-15-2014 |
| 20140140816 | FAN MODULE - A fan module includes a casing, a fan, and two vibration absorption assemblies. The casing has an accommodating space. The fan is located in the accommodating space and keeps a distance from the casing. Each of the two vibration absorption assemblies includes two first vibration absorption components and a second vibration absorption component. The two first vibration absorption components are respectively in contact with the fan and separated from the casing, respectively. The second vibration absorption component is connected with two first vibration absorption components and the casing, respectively. The first vibration absorption components and the second vibration absorption components are adapted for absorbing the vibration waves having different frequency ranges. | 05-22-2014 |
| 20140147251 | INSERT ELEMENT FOR CLOSING AN OPENING INSIDE A WALL OF A HOT GAS PATH COMPONENT OF A GAS TURBINE AND METHOD FOR ENHANCING OPERATIONAL BEHAVIOUR OF A GAS TURBINE - The invention refers an insert element for closing an opening inside a wall of a hot gas path component of a gas turbine. The insert includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S). | 05-29-2014 |
| 20140147252 | POWER TOOL - A power tool having a built-in fan, the fan including a plurality of blades at uneven pitches. The fan includes a centrifugal fan which blows out air in all radial directions. The fan is provided with means for correcting unstable outflow which may be caused by the uneven pitches between the blades. The blades have unevenly configured inducers for correcting unstable outflow. | 05-29-2014 |
| 20140205437 | FAN VIBRATION ABSORPTION STRUCTURE - A fan vibration absorption structure applied to a fan set having a first side and a second side respectively having multiple first and second fixing holes. The fan vibration absorption structure includes: a housing for receiving the fan set; a first frame body having multiple first through holes on the first side without contacting therewith, a first gap being defined between the first frame body and the first side, the first frame body having multiple first locating sections each having a first perforation, a second gap being defined between the first locating section and the housing; multiple first assembling member each having a first engagement section clamped between the first frame body and the first side to form the first gap; and multiple second assembling members each having a second engagement section clamped between the first locating section and the housing to form the second gap. | 07-24-2014 |
| 20140212272 | FLUID PUMP - A fluid pump includes an inlet for introducing fluid into the fluid pump and an outlet for discharging fluid from the fluid pump. The fluid pump also includes a motor having a shaft that rotates about an axis. An impeller includes an array of blades radially surrounding the axis. The impeller is rotatable by the shaft of the motor such that rotation of the impeller pumps fluid from the inlet to the outlet. A vibration isolation member applies a force on the shaft such that the force has a component that is perpendicular to the axis. | 07-31-2014 |
| 20140212273 | TURBINE ENGINE FAN CASING AND AN ASSEMBLY FORMED BY SUCH A CASING AND ACOUSTIC PANELS - A turbine engine fan casing of composite material including fiber reinforcement densified by a matrix is made as a single part with ribs that project from an inside face and/or from the outside face of the casing, each rib including a fiber reinforcement portion connected to the fiber reinforcement of a remainder of the casing by weaving or by stitching. On the inside, the ribs serve to mount acoustic panels to the inside face of the casing to form an assembly including a casing and acoustic panels. On the outside, the ribs enable equipment to be mounted on the casing. | 07-31-2014 |
| 20140219781 | AIR INLET SILENCER FOR TURBOMACHINES - An air inlet silencer for turbomachines is provided. In one embodiment, the air inlet silencer includes a body, and a plurality of concentric baffles coupled to and axially surrounding the body. In another embodiment, an air inlet system for a turbomachine includes the air inlet silencer, as discussed herein, positioned within a silencer housing. The air inlet system may also include a deflector positioned within the silencer housing adjacent the air inlet silencer. In a further embodiment, a turbomachine includes a turbine coupled to a compressor, and an air inlet system, as described herein, coupled to the compressor. | 08-07-2014 |
| 20140219782 | MODULAR FAN HOUSING WITH MULTIPLE MODULAR UNITS HAVING SOUND ATTENUATION FOR A FAN ARRAY FOR AN AIR-HANDLING SYSTEM - A modular fan housing configured to hold an array of motors and fans is provided. The modular fan housing is configured for use in an air-handling system that delivers air to a ventilation system for at least a portion of a building. The fan housing comprises a plurality of modular units configured to be stacked adjacent to one another in at least one row or column to form an array. The modular units each include an interior surface and have a front end and a back end that define a chamber. The chambers are configured to receive the motors and fans. Sound attenuation layers extend along at least a portion of the interior surface of the corresponding chambers. The sound attenuation layers are positioned between at least some of the adjacent chambers. | 08-07-2014 |
| 20140219783 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section, a turbine section coupled to the fan section through a geared architecture, a first member supporting the geared architecture, and a second member supporting the first member relative to an engine static structure. The first member and the second members are spaced apart from one another at a location. A damper includes opposing ends and extending between the first member and the second member at the location for limiting relative movement between the first member and the second member. A fan drive gear system and a method are also disclosed. | 08-07-2014 |
| 20140271132 | NOISE SUPPRESSION SYSTEM - A noise suppression system for an air-cooled internal combustion engine is disclosed. The system may include an acoustically designed shroud forming a cavity and configured for attenuating noise produced by a cooling air fan associated with the engine. In one system, the shroud is mountable on a housing of the air fan. A pair of air inlet passages may be provided which are operable to draw ambient cooling air into the shroud to the fan. The air inlet passages are acoustically configured and tuned to attenuate noise generated by the fan. In one system, the air inlet passages may each be formed in a rear quadrant of the shroud. Various configurations of the shroud may include quarter wave resonators and/or micro-perforated panels to further attenuate fan noise. | 09-18-2014 |
| 20140271133 | CENTRIFUGAL BLOWER ASSEMBLY AND METHOD FOR ASSEMBLING THE SAME - A centrifugal blower assembly comprises a scroll wall and a pair of opposing sidewalls. The scroll wall is positioned between the pair of opposing sidewalls such that the scroll wall and opposing sidewalls together define a blower chamber and a blower outlet. A baffle element is positioned within the blower chamber and adjacent the blower outlet such that the baffle element is configured to facilitate uniform distribution of airflow downstream of the blower assembly. An air stream splitter is coupled to the scroll wall. The air stream splitter includes a spline member extending a varying distance from the scroll wall. The air stream splitter is positioned within the blower chamber to facilitate uniform airflow distribution within the blower assembly. | 09-18-2014 |
| 20140271134 | NOISE SUPPRESSION SYSTEMS - An apparatus or system includes a component that generates or transfers noise having a frequency within a noise frequency range. The component may include a boundary. The apparatus or system may be an engine in some examples. The engine may additionally include a micro-perforated sheet positioned a distance from the boundary. The micro-perforated sheet may include a plurality of micro-perforated holes, and may be configured to absorb sound within an absorption frequency range based on parameters of the micro-perforated sheet. The parameters may include the distance from the boundary and dimensions of the micro-perforated holes, and may be set such that the absorption frequency range overlaps the noise frequency range. | 09-18-2014 |
| 20140286752 | IMPELLER AND FAN USING THE SAME - An impeller which is applied to a fan includes a hub, a plurality of first centrifugal blade and a plurality of second centrifugal blades. The hub is disposed in an accommodating space of the fan. The first centrifugal blades and the second centrifugal blades are connected to the hub. The first centrifugal blades have first ends away from the hub. The second centrifugal blades have second ends away from the hub. A distance between the second end and a center of the hub is larger than that between the first end and the hub center, and the first centrifugal blades and the second centrifugal blades are arranged periodically. Thus, an airflow noise in a constant frequency generated by the impeller can be avoided, and noises in inconstant frequency would not accumulate or generate annoying noise peak. | 09-25-2014 |
| 20140328670 | VIBRATION ISOLATION MOUNT - A vibration isolation mount for a compressor that is formed of an elastomeric material and includes a sleeve, tapered studs or axial ribs spaced around the sleeve, and a lip seal extending around the sleeve. The mount is intended to be located between a compressor and a housing. The studs or ribs then deform to isolate the housing from radial vibration of the compressor, and the lip seal creates an annular seal between the housing and the compressor. | 11-06-2014 |
| 20140334917 | BLOWER DEVICE - A blower device includes an axial flow fan having blades to blow air, and a fan shroud that includes a cylindrical portion surrounding an outer circumference of the fan at a distance from the outer circumference, and an air guiding portion guiding air drawn by the fan. The fan shroud includes a short end part shorter in distance to the outer circumference of the fan than another part in an outer end portion of the fan shroud, and a protruding end part provided at a position advanced in a rotational direction from the short end part, protruding upstream in a flow of the drawn air more than the fan and protruding outward of the air guiding portion. Accordingly, the blower device which includes the fan shroud capable of reducing rotational noise can be provided. | 11-13-2014 |
| 20140341712 | LOW-NOISE FUME EXTRACTOR HOOD - A fume extractor hood is disclosed, comprising a box with a motor-fan assembly and a muffler module comprising a bearing frame defining an air extraction conduit with axis (A), an active noise suppression system comprising at least one electro-acoustic transducer and at least two microphones, a passive noise suppression system comprising a sound absorbent material. Said muffler module comprises at least two electro-acoustic transducers connected to the walls of said bearing frame, in opposite positions, in such manner to leave the central part of said conduit free. The sound beams coming from said at least two electro-acoustic transducers are mutually combined, obtaining a resulting sound beam that can be directed towards a preferred direction by means of beam forming algorithms. | 11-20-2014 |
| 20140341713 | LOW PRESSURE TURBINE PROVIDED WITH SPLITTERS AT THE LAST STATOR ARRAY, IN PARTICULAR FOR A GAS TURBINE ENGINE - A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit. | 11-20-2014 |
| 20140348639 | TURBOMACHINE BLADE | 11-27-2014 |
| 20140356134 | DAMPERS FOR FAN SPINNERS OF AIRCRAFT ENGINES - Dampers for fan spinners of aircraft engines are disclosed. An example fan module for a gas turbine engine may include a fan disk; fan blades mounted to the fan disk and extending radially therefrom; a fan spinner operatively coupled to the fan disk at an axially upstream position; and/or one or more elastic vibration dampers operatively interposing the fan spinner and the fan disk. The elastic vibration dampers may be disposed circumferentially around an interface between the fan spinner and the fan disk and may be compressed axially and/or radially. | 12-04-2014 |
| 20140369814 | DIFFUSER PIPE FOR A GAS TURBINE ENGINE AND METHOD FOR MANUFACTURING SAME - A diffuser pipe for a gas turbine engine comprises a hollow pipe body including a first end, a second end fluidly connected to the first end, and at least one flattened area proximate to the second end. A ring is connected to the second end. The ring is an outlet of the diffuser pipe. At least one stiffener is disposed on the at least one flattened area. The ring and the at least one stiffener reduce vibratory stresses at the second end of the pipe body. A method of manufacturing a diffuser pipe of a gas turbine engine is also presented. | 12-18-2014 |
| 20140369815 | CONTROL OF LOW VOLUMETRIC FLOW INSTABILITES IN STEAM TURBINES - Configuration of the last stage of a steam turbine where rotor blades rotate encircled by a vane carrier, such that a plurality of passages are located in the vane carrier, such that a fluid is blown through these passages forming a flow that impinges onto the rotor blades, the number of passages, the location of the passages in the vane carrier and the velocity of the flow impinging onto the rotor blades, being calculated in such a way that rotating flow instabilities in the rotor blades when the steam turbine operates at low volumetric flow conditions are avoided. | 12-18-2014 |
| 20140369816 | FLUID DISCHARGE VIBRATION DAMPING STRIPS FOR ACOUSTIC PROTECTION OF AIRCRAFT TURBOMACHINE FAN CASING - An acoustic protection device for a fan casing of an aircraft turbomachine, including an acoustic protection panel forming a ferrule sector centered on a center axis, and one or more vibration damping strips pressed on a first side to an external surface of the panel and on a second side to an internal surface of the casing, each damping strip including two opposite edges each including an upstream end and a downstream end spaced from each other along a direction of the center axis. At least one of both opposite edges of at least one of the damping strips is shaped such that liquid present on this edge can flow by gravity towards either or both of its upstream and downstream ends. | 12-18-2014 |
| 20150010387 | EXHAUST GAS TURBOCHARGER - An exhaust gas turbocharger may include a rotor mounted in a bearing housing via a rolling bearing. The rolling bearing may include an outer shell, an inner shell and rolling bodies running therebetween. At least one annular and vibrational noise absorbing diaphragm spring element may be arranged between the outer shell of the rolling bearing and the bearing housing. The diaphragm spring element may mount the rotor in radial direction and axial direction in a vibration-insulating manner with respect to the bearing housing. | 01-08-2015 |
| 20150010388 | DAMPER FOR DAMPING PRESSURE WAVES - The invention relates to a damping device for damping a pressure wave generated by a propeller. The damping device comprises a surface structure, which delimits a closed space, which contains gas. The damping device further comprises a flexible structure, which is arranged in the closed space delimited by the surface structure, and which flexible structure forms channels, through which the gas can flow. The invention also relates to a propeller-driven vessel and a propulsion device. | 01-08-2015 |
| 20150016962 | TANK DAMPENING DEVICE - A compressor assembly that has a compressed air tank having a vibration absorption member. The vibration absorption member can exert a pressure on a portion of the compressed air tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which applies a force against the compressed gas tank. Controlling the sound level of the compressed gas tank is accomplished by absorbing vibration from the compressed gas tank by which exerting a pressure on a portion of the compressed gas tank. | 01-15-2015 |
| 20150023779 | Low Vibration Fan - A low vibration fan including a housing, a driving member and a fan wheel is provided. The housing has an outer frame and a base, wherein the outer frame has two openings, a positioning rim, and a guiding channel linking the two openings, wherein the base couples with the positioning rim, and wherein a radial buffer gap is formed between an outer periphery of the base and an inner periphery of the positioning rim. The driving member is mounted on the base. The fan wheel couples with the driving member rotatably. Accordingly, the radial buffer gap can largely reduce the vibration transmitted from the base to the outer frame. | 01-22-2015 |
| 20150023780 | LINER ATTACHING SCHEME - A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner. | 01-22-2015 |
| 20150023781 | STARTING DEVICE - A starting device includes a pump impeller, a turbine runner for rotating together with the pump impeller, a damper mechanism having an input element receiving power from an internal combustion engine, an output element coupled to a speed change device, an intermediate element between the input and output elements, and a dynamic damper for damping vibration at a predetermined frequency among vibration transferred to the speed change device. The starting device includes a first dynamic damper having an elastic member and a first mass body coupled the first elastic member, and coupled to the intermediate element; and a second dynamic damper having an elastic member and a second mass body connected to the second elastic member, and coupled to the intermediate element. The first mass body of the first dynamic damper or the second mass body of the second dynamic damper includes at least the turbine runner. | 01-22-2015 |
| 20150023782 | FLOW GENERATOR - A flow generator includes a housing, a blower structured to generate a flow of pressurized breathable air, and a suspension device to support the blower within the housing and provide a pressure seal between low and high pressure sides of the blower. The suspension device includes a bellows-like portion provided along the perimeter of the blower to absorb shock applied at least radially to the blower and one or more cones provided along upper and/or lower sides of the blower to absorb shock applied at least axially to the blower. | 01-22-2015 |
| 20150030434 | DAMPING DEVICE FOR BEING SITUATED BETWEEN A HOUSING WALL AND A CASING RING OF A HOUSING OF A THERMAL GAS TURBINE - A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided. | 01-29-2015 |
| 20150037141 | COMPRESSOR HOUSING ASSEMBLY FOR A TURBOCHARGER - A compressor housing assembly for a turbocharger can include a compressor housing shell that includes an axis for alignment with a rotational axis of a compressor wheel, a wall that includes features defined in part by radii with respect to the axis, and an edge that defines in part an inlet opening of a shroud port; and an insert that includes a shroud section and a noise suppressor section that define a recirculation port where the insert is axially located by the wall of the compressor housing shell, where an internal recirculation passage is defined in part by the insert and the wall, and where an edge of the shroud section (e.g., a lowermost edge) defines in part the inlet opening of the shroud port. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 02-05-2015 |
| 20150037142 | CASING FOR TURBOMACHINE BLISH AND TURBOMACHINE EQUIPPED WITH SAID CASING - A casing for a blisk of a turbomachine including an internal coating made of an abradable material, and a plurality of circumferential slots arranged in the coating of abradable material, the casing further including a circumferential cavity formed in the coating of abradable material, into which cavity the slots open, the slots opening into the cavity and extending between the cavity and an internal surface of the casing. A turbomachine can include such a casing and a blisk. | 02-05-2015 |
| 20150056065 | TURBOCHARGER - There is provided a turbocharger which can reduce whirl vibration. | 02-26-2015 |
| 20150063984 | INTAKE BOX WITH SOUND-DAMPING PROPERTIES FOR AN AIR SUPPLY SYSTEM IN A COMPRESSION ARRANGEMENT - An intake box of an air supply system in a compressor arrangement, having an intake grill and an air intake pipe arranged on the compressor side, wherein the intake grill and the air intake pipe are arranged between a lower lid and an upper lid, wherein, in addition, a sound damping box for minimizing noise emissions is arranged between the intake grill and the air intake pipe, wherein the longitudinal dimension and width dimension of the sound damping box are each at least three times as large as the depth dimension of the sound damping box. | 03-05-2015 |
| 20150063985 | GUIDE BLADE RING FOR AN AXIAL TURBOMACHINE AND METHOD FOR DESIGNING THE GUIDE BLADE RING - 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. | 03-05-2015 |
| 20150063986 | APPARATUS FOR ENERGY ABSORPTION, A TURBO-MACHINE AND A METHOD FOR ENERGY ABSORPTION - An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed. | 03-05-2015 |
| 20150086335 | ELEMENT FOR SOUND ABSORPTION MOUNTED ON AIRCRAFT COMPONENTS - An element ( | 03-26-2015 |
| 20150098801 | HOVER AIRCRAFT ROTOR COMPRISING A VIBRATION DAMPING DEVICE - A hover aircraft rotor having a hub which rotates about an axis and has a number of blades; a drive shaft connectable to a drive member of the aircraft and connected functionally to the hub to rotate the hub about the axis; and damping means for damping vibration transmitted to the shaft, and which include a mass designed to oscillate, in use, to oppose transmission to the shaft of vibration generated by rotation of the blades; the mass being free to oscillate parallel to the axis, to oppose transmission to the shaft of vibration having main components along the axis. | 04-09-2015 |
| 20150104294 | Fan Inlet Air Handling Apparatus and Methods - Particular embodiments of the inventive technology may be described as an air handling shroud for establishment at the inlet area of a fan, the shroud adapted to realign and/or redistribute fan inlet flow so as to reduce fan-generated noise without unacceptably impairing fan efficiency and/or performance. Certain embodiments present a lattice arrangement of cells through which air flows; the shroud may protrude up from an inlet face lying in a plane defined by the fan (e.g., by the fan housing or an inlet cone). It may have a hemispherical shape and a lower resistance-per-area sector at the pole (or polar region) thereof. Optional componentry includes but is not limited to a flow obstructer established at a fan proximal portion of the shroud, and acoustic material established on surfaces of the cells of the shroud. | 04-16-2015 |
| 20150104295 | Piezoelectric Damper System for an Axial Turbomachine Rotor - 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. The grouping of the piezoelectric transducers that deform in the same way makes it possible to damp the piezoelectric transducers with identical means thus pooled. | 04-16-2015 |
| 20150110603 | ACOUSTIC STRUCTURAL PANEL WITH SLANTED CORE - A nacelle may comprise a noise suppressing structure. The noise suppressing structure may comprise a plurality of noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The plurality of noise suppressing cells may contact the perforated layer of material and the non-perforated layer of material at an acute angle (e.g., between twenty and seventy-five degrees) such that the plurality of noise suppressing cells are non-orthogonal to the perforated layer of material and the non-perforated layer of material. Further, each of the plurality of noise suppressing cells may comprise a hexagonal cross-sectional profile. Further still, the noise suppressing structure may comprise a support structure comprising a plurality of support members, wherein the plurality of noise suppressing cells are situated within the support structure. | 04-23-2015 |
| 20150110604 | AEROFOIL ARRAY FOR A GAS TURBINE WITH ANTI FLUTTERING MEANS - An aerofoil array for a gas turbine system has an inner annular platform and an outer annular platform, which extend about a longitudinal axis and radially delimit an annular channel for a gas flow; the annular channel houses a plurality of aerofoils, arranged at a substantially constant angular pitch and comprising respective central portions and respective ends connected to the platforms; the aerofoils are formed by two series of aerofoils having a different geometrical feature in order to intentionally vary the eigenfrequencies and arranged about the longitudinal axis with a sequence that is regularly repeated all along the annular channel; even though the external geometry of the aerofoils is varied, the cross-sections remain unchanged in the central portions, at any given radius with respect to the longitudinal axis. | 04-23-2015 |
| 20150118023 | ACOUSTIC STRUCTURE FOR A GAS TURBINE ENGINE - An acoustic structure for a gas turbine engine comprising an noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and an noise reduction adjacent to the inner wall. The fire protector layer includes a non-perforated outer wall adapted to be in contact with a second fluidic environment having potentially a fire, a fire protector adjacent to the outer wall, and a pressure resisting wall disposed between the fire protector and the noise reduction. The second fluidic environment is under a pressure lower than a pressure of the first fluidic environment. The inner and outer walls are load-bearing walls of the acoustic structure | 04-30-2015 |
| 20150125268 | PROPELLER SOUND FIELD MODIFICATION SYSTEMS AND METHODS - A propeller system for an aircraft includes an assembly for modifying a sound field of the propeller system. The propeller system includes a rotor supported for rotation about a rotor axis. The rotor has a central hub and a plurality of blades each extending outwardly from the hub to a tip. The rotor and blades are operable to propel an aircraft to travel in a direction. The rotor blades define a rotor plane perpendicular to the rotor axis. The blade tips define a circumferential rotational path as the blades are rotated by the rotor. The propeller system includes an acoustic resonator or multiple resonators having openings disposed within a distance to the propeller blade tip that is small compared to the wavelength of the propeller's fundamental blade tone and proximate to the rotor plane. The resonators are excited by tip flow of the blade as it passes the opening. The acoustic resonators are configured and positioned so as to direct acoustic energy to modify the sound field of the propeller system at blade pass or higher harmonic frequency tones in a desired direction relative to the aircraft. | 05-07-2015 |
| 20150132109 | VACUUM PUMP - A vibration control mechanism | 05-14-2015 |
| 20150292407 | REMOVABLE ACOUSTIC PANELS FOR TURBOJET ENGINE CASING - An acoustic panel intended to be fixed internally to a fan casing of a turbojet engine, including an exterior face and an interior face which are curved about an axis, and two axially opposed transverse faces, the exterior curved face having at least one first recess on the side of a first transverse face and at least one second recess on the side of the opposite transverse face, said recesses each an attachment, in which said recesses do not open onto the interior curved face of the panel. Also covered are the turbojet engine including these panels and the method of mounting them. | 10-15-2015 |
| 20150292415 | TORSION SPRING INTERNAL DAMPER - A spring assembly has a spring end for engagement with a component to bias the component in a first direction. The spring end is connected to a plurality of coils, which have an inner peripheral surface, and are mounted about a pivot pin. A damper is positioned between an outer peripheral surface on the pivot pin and the inner peripheral surface of the spring coils. The damper is engaged by the spring coils, if the spring end is driven in a direction opposed to the first direction. A one-way drive assembly and a gas turbine engine are also disclosed. | 10-15-2015 |
| 20150308290 | FAN CONTAINMENT CASE - A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine. | 10-29-2015 |
| 20150308346 | INTAKE LINER - A gas turbine engine comprising a fan and an intake liner | 10-29-2015 |
| 20150308448 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 10-29-2015 |
| 20150314882 | AIRCRAFT ENGINE NACELLE BULKHEADS AND METHODS OF ASSEMBLING THE SAME - An engine nacelle includes an exterior wall and an interior wall. A forward bulkhead is coupled between the interior wall and the exterior wall, wherein the forward bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall. The engine nacelle also includes an aft bulkhead coupled between the interior wall and the exterior wall, wherein the aft bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall. | 11-05-2015 |
| 20150315972 | METHODS AND APPARATUS FOR NOISE ATTENUATION IN AN ENGINE NACELLE - An acoustic liner includes a first core that has a plurality of first core cells defined by a corresponding plurality of first core cell walls. The first core has a first core thickness. The acoustic liner also includes a second core that has a plurality of second core cells defined by a corresponding plurality of second core cell walls. The second core has a second core thickness, and the first core thickness and the second core thickness are unequal. The acoustic liner further includes a second fabric sheet coupled between the first core and the second core. Each of the plurality of second core cell walls generally is not coplanar with any of the plurality of first core cell walls. | 11-05-2015 |
| 20150337862 | STRUCTURE FOR REDUCING NOISE OF VENTILATING FAN - Disclosed is a structure for reducing noise of a ventilating fan. The structure includes an orifice plate fixed on a scroll casing and is shaped to be an annular and semi-surrounding hollow structure in order to match with the shape of an air inlet of the scroll casing, and to cover only the air inlet of the scroll casing. The noise generated by an air blower of the ventilating fan can be directed along a bell mouth of the scroll casing of the ventilating fan after being emitted from the air inlet of the scroll casing, and then can be smoothly sucked by the orifice plate. The sucked-in noise can repeatedly collide with the orifice plate and be diffused, thereby the energy being gradually weakened and the sound pressure thereof being decreased. | 11-26-2015 |
| 20150345514 | ACOUSTIC TREATMENT FOR AN INDOOR HVAC COMPONENT - An acoustic treatment for an indoor HVAC component is provided having an inner liner and at least one aperture formed through the inner liner. An acoustic absorber is positioned adjacent the inner liner. A gap, including a width dimension, is formed between the inner liner and the acoustic absorber. | 12-03-2015 |
| 20150361802 | TURBINE ROTOR BLADE - In a turbine rotor blade of a radial turbine, especially in a variable-geometry turbine with variable nozzles, an object is to restrict high-order resonance of the turbine rotor blade without increasing the size of a device with a simplified structure. A plurality of turbine rotor blades for a radial turbine is disposed on a hub surface. Each turbine rotor blade includes blade-thickness changing portions, at which at least a blade thickness of a cross-sectional shape at a middle portion of a blade height increases rapidly with respect to a blade thickness of a leading-edge side, at a predetermined position from a leading edge along a blade length which follows a gas flow from the leading edge to a trailing edge. The blade thickness increases to a blade thickness via the blade-thickness changing portions. | 12-17-2015 |
| 20150361823 | METHODS AND APPARATUS FOR PASSIVE THRUST VECTORING AND PLUME DEFLECTION - A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow. | 12-17-2015 |
| 20150361825 | Turbine Engine Component with Vibration Damping - 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. | 12-17-2015 |
| 20150361826 | GAS TURBINE ENGINE AIRFOIL CURVATURE - A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch. | 12-17-2015 |
| 20150367921 | Propulsion Unit for Maritime Vessel Including a Nozzle Exhibiting an Exchangable Leading Edge on the Inlet of the Nozzle - Propulsion unit for propulsion and maneuvering of a maritime vessel, including a nozzle provided with a sectioned leading edge on inlet of the nozzle, which leading edge is formed by sections of a low-weight non-metallic material, and a front ring, which front ring is arranged between main part of the nozzle and the sectioned leading edge and is arranged for providing a fastening point for the sections of the leading edge. | 12-24-2015 |
| 20150369080 | ROTATING MACHINE COMPRISING A DAMPING COLLAR - A rotary machine including a stationary portion and a rotary portion; at least one bearing provided with a stationary ring and a rotary ring, the bearing being mounted between the stationary portion and the rotary portion in order to guide the rotary portion in rotation; and a damper collar interposed between the stationary ring of the bearing and the stationary portion. The damper collar includes a flexible strip having tongues cut out therein, and the flexible strip is shaped into a ring around the stationary ring of the bearing, the shaping of the strip into a ring causing the tongues to move outwards from the collar so that the free edges of the tongues come into contact with the stationary portion. | 12-24-2015 |
| 20150369127 | ACOUSTIC LINER WITH VARIED PROPERTIES - 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. | 12-24-2015 |
| 20150377128 | NACELLE FOR AIRCRAFT, PROVIDED WITH A BUILT-IN SYSTEM FOR ANTI-ICING PROTECTION AND ACOUSTIC ABSORPTION - A nacelle (N) has a built-in system ( | 12-31-2015 |
| 20150377253 | POWER-OPERATED AIR BLOWING WORK APPARATUS - A power-operated air blowing work apparatus comprises: a volute casing including a centrifugal fan installed therein and having a front wall formed with an air intake aperture for sucking air from an atmosphere into the volute casing by the centrifugal fan; an engine mounted to the volute casing in a rear side of the volute casing and connected to the centrifugal fan for rotating the centrifugal fan; an engine casing covering the engine from behind the engine in the rear side of the volute casing, and an air suction passage communicating from inside the engine casing toward inside the front wall of the volute casing for drawing air in the engine casing toward inside the front wall of the volute casing. | 12-31-2015 |
| 20160003105 | Integrated Flex Support and Front Center Body - A gas turbine engine is provided. The gas turbine engine may include a geared architecture, a central body support and a bearing package. The geared architecture may interconnect a spool and a fan rotatable about an axis. The central body support may provide an annular wall for a core flow path and an integral flex support inwardly extending therefrom. The integral flex support may couple the geared architecture to the central body support. The bearing package may include a bearing support removably coupled to the integral flex support. | 01-07-2016 |
| 20160017741 | Box Rim Cavity for a Gas Turbine Engine - A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions. | 01-21-2016 |
| 20160017895 | FAN ASSEMBLY AND FAN FRAME - 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. | 01-21-2016 |
| 20160024963 | NOISE ATTENUATING LIPSKIN ASSEMBLY AND METHODS OF ASSEMBLING THE SAME - An acoustic assembly includes a backsheet including a plurality of perforations defined therethrough and an acoustic core coupled to the backsheet. The acoustic core includes a plurality of channels defined therethrough that are configured to be in flow communication with the plurality of perforations. The acoustic assembly also includes a linear facesheet coupled to the acoustic core, wherein the linear facesheet includes a plurality of apertures configured to be in flow communication with the plurality of channels. A lipskin is coupled to the linear facesheet, wherein the lipskin includes a plurality of openings configured to be in flow communication with the plurality of apertures. | 01-28-2016 |
| 20160025109 | BLOWER DEVICE - A blower includes: centrifugal impeller ( | 01-28-2016 |
| 20160032832 | GAS TURBINE ENGINE NOISE REDUCING NOSE CONE - A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature. | 02-04-2016 |
| 20160032833 | THERMALLY CONFORMING ACOUSTIC LINER CARTRIDGE FOR A GAS TURBINE ENGINE - A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section. | 02-04-2016 |
| 20160032834 | TURBINE ENGINE, SUCH AS AN AIRPLANE TURBOFAN OR TURBOPROP ENGINE - The invention relates to a turbine engine, such as an aircraft turbofan or a turboprop engine, including a fan casing ( | 02-04-2016 |
| 20160039528 | NACELLE FOR AN AIRCRAFT TURBOJET ENGINE WITH AN EXTENDED FRONT LIP - A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange | 02-11-2016 |
| 20160047270 | SPLIT RING SPRING DAMPERS FOR GAS TURBINE ROTOR ASSEMBLIES - A spring damper includes a split ring body. The split ring body defines a center and a circular gap separating opposed first and second end portions of the split ring body. The first and second end portions are connected by a split ring body segment that is evenly spaced from the center. At least one of the first and second end portions is unevenly spaced from the center in relation to the segment that is evenly spaced with respect to the center. | 02-18-2016 |
| 20160053637 | SILENCING AND COOLING ASSEMBLY WITH FIBROUS MEDIUM - Embodiments of the present disclosure provide an assembly including a fibrous medium having a plurality of substantially corrugated channels therein, the plurality of substantially corrugated channels being permeable to a flow of fluid therethrough; a distributor in contact with the fibrous medium, and including an aperture therein for transmitting a liquid coolant through the distributor; and at least two acoustic shields coupled to the fibrous medium and proximal to opposing sides of the distributor. | 02-25-2016 |
| 20160053684 | LOW NOISE AEROENGINE INLET SYSTEM - An aeroengine is provided with a splitter apparatus disposed in a section of ain inlet duct. The splitter apparatus can be actuated from a stowed position to a deployed position to allow splitter(s) to selectively move from out of the inlet flow to a position extending into the inlet duct to divide the inlet flow into multiple passages. | 02-25-2016 |
| 20160053685 | LOW NOISE AEROENGINE INLET SYSTEM - 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 he inlet duct. | 02-25-2016 |
| 20160053686 | LOW NOISE AEROENGINE INLET SYSTEM - An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor. | 02-25-2016 |
| 20160076396 | Turbine Exhaust Cylinder / Turbine Exhaust Manifold Bolted Stiffening Ribs - Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response. | 03-17-2016 |
| 20160076397 | DAMPING DESIGN TO REDUCE VIBRATORY RESPONSE IN THE TURBINE EXHAUST MANIFOLD CENTERBODY - Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer clamped by a plurality of studs. | 03-17-2016 |
| 20160076398 | TURBINE EXHAUST CYLINDER/ TURBINE EXHAUST MANIFOLD BOLTED PART SPAN TURBINE EXHAUST FLAPS - A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut. | 03-17-2016 |
| 20160076400 | NOISE SUPPRESSION APPARATUS AND METHODS OF MANUFACTURING THE SAME - A noise suppression apparatus includes a body portion including a plurality of nested channels, each channel of the plurality of nested channels including a first end opening and a second end opening, and a surface portion including each first end opening and each second end opening of each channel. | 03-17-2016 |
| 20160084108 | NACELLE INLET AND ENGINE FAN HOUSING ASSEMBLY AND METHOD FOR MAKING SAME - A system and method is provided for coupling a nacelle inlet assembly to an engine fan housing structure that provides adequate clearance and access for removing a blisk fan from a turbofan engine. This is accomplished by utilizing a nacelle inlet forward compartment, referred to herein as the “D-lip”and an acoustic liner that are inseparable and removable as an integral unit, providing sufficient clearance for removable of the blisk fan. The nacelle inlet assembly may be slidably coupled to the engine fan housing structure, minimizing assembly interfaces and therefore overall aircraft engine weight. | 03-24-2016 |
| 20160090860 | DAMPING SYSTEM FOR A TURBOMACHINE SLIP RING - A damping system for a turbomachine slip ring includes a slip ring assembly. The slip ring assembly includes a rotating component which is coupled at one end to a rotor shaft of the turbomachine and a stator component which circumferentially surrounds a rotatable center core portion of the rotating component. The system further includes a static structure which defines a carrier sleeve where the carrier sleeve circumferentially surrounds a portion of the stator component. The system also includes a damping material which extends radially between an inner surface of the carrier sleeve and an outer surface of the stator component so as to dissipate vibrational energy of the slip ring assembly during rotation of the rotor shaft. | 03-31-2016 |
| 20160090916 | INNER BYPASS DUCT - An inner bypass duct of a gas turbine engine includes a plurality of non-structural front panels arranged circumferentially. Each front panel has an outer surface and an inner surface. The inner surface is at least partially covered by a composite structure. The composite structure includes a fireproof layer and an acoustic layer disposed between the fireproof layer and the inner surface. A non-structural panel for an inner bypass duct and a method of forming such panel are also presented. | 03-31-2016 |
| 20160097301 | Aircraft gas turbine engine with shock-absorbing element for fan blade loss - An aircraft gas-turbine engine having a fan mounted on a fan shaft and including several fan blades, where the fan shaft is mounted on an engine structure by means of an upstream fan bearing, when seen in the flow direction, and a downstream bearing, where at least one predetermined breaking point is provided in the area of the fan bearing, characterized in that at least one shock-absorbing element designed as metal fabric damper is arranged at a radial gap to have a parallel effect relative to the predetermined breaking point. | 04-07-2016 |
| 20160138401 | BLADE OR VANE ARRANGEMENT FOR A TURBOMACHINE - The present invention relates to a blade or vane arrangement for a turbomachine having a turbomachine blade or vane ( | 05-19-2016 |
| 20160138573 | INERTIAL ENERGY ACCUMULATING DEVICE - The invention relates to a device for accumulating inertial energy having a rotor chamber in housing, a rotor in the rotor chamber having a first end face and a substantially opposite second end face, the rotor being mounted, so that it can be displaced and rotate relative to the housing leaving free a gap between the outer rotor perimeter and the inner perimeter of the rotor chamber, wherein a seal is provided in said gap separating a first section of the rotor chamber and a second section of the rotor chamber, exposing means; creating a differential pressure over the rotor for levitation thereof, wherein the device further comprises stabilizing means for counteracting vibration of the rotor. | 05-19-2016 |
| 20160146039 | ACOUSTIC ATTENUATION WITH ADAPTIVE IMPEDANCE - An acoustic liner may include a core with a plurality of resonator chambers, a perforated top sheet coupled to the core, and a backskin coupled to the core. A thermoacoustic speaker including nanomaterials may be coupled to at least one of the core, the backskin, and the perforated top sheet. A voltage may be applied to the thermoacoustic speaker. The thermoacoustic carbon nanotube speaker may create a dynamic excitation within a resonator chamber in the core. The dynamic excitation may change the liner acoustic impedance to achieve optimum noise attenuation over a wide range of frequencies or engine operating conditions. | 05-26-2016 |
| 20160146041 | BLADE OR VANE FOR A TURBOMACHINE AND AXIAL TURBOMACHINE - The present invention relates to a blade ( | 05-26-2016 |
| 20160146106 | REDUCTION OF TURBOFAN NOISE - The invention relates to an aircraft turbofan type engine ( | 05-26-2016 |
| 20160146220 | COMPRESSOR COVER ASSEMBLY METHOD AND FORMING TOOL - A method of assembling and retaining a noise attenuation device ( | 05-26-2016 |
| 20160153287 | PLATED POLYMER TURBINE COMPONENT | 06-02-2016 |
| 20160153352 | TURBOCHARGER TURBINE WASTEGATE MECHANISM | 06-02-2016 |
| 20160160651 | AIRFOIL INCLUDING LOOSE DAMPER - An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity. | 06-09-2016 |
| 20160160863 | PLATED POLYMER FAN - Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure. | 06-09-2016 |
| 20160177810 | HEAT EXCHANGER SYSTEM FOR A VEHICLE | 06-23-2016 |
| 20160186604 | FLEXIBLY DAMPED MOUNTING ASSEMBLIES FOR POWER GEAR BOX TRANSMISSIONS IN GEARED AIRCRAFT ENGINE ARCHITECTURES - An assembly for flexibly damping a power gear box for a gas turbine engine, the assembly includes a flexible mount connected to the power gear box at a first end of the flexible mount; a member connected to the flexible mount at the first end of the flexible mount and a second end of the flexible mount, wherein the first end of the flexible mount includes an outer rim connected to the member and an inner rim connected to the power gear box and a set of circumferentially segmented squeeze film damper lands configured to receive a damping fluid is provided between the inner rim and the outer rim. | 06-30-2016 |
| 20160195106 | CENTRIFUGAL FAN, AND FAN EQUIPPED WITH SOUND-MUFFLING BOX AND USING CENTRIFUGAL FAN | 07-07-2016 |
| 20160201691 | SUCTION DEVICE WITH SOUND MIRROR DEVICE | 07-14-2016 |
| 20160376929 | TURBINE EXHAUST CYLINDER STRUT STRIP FOR SHOCK INDUCED OSCILLATION CONTROL - An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided. | 12-29-2016 |
| 20170234331 | FAN AND AIR-CONDITIONING APPARATUS USING THE SAME | 08-17-2017 |
