| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 181213000 | Reaction engine type | 64 |
| 20080202847 | Method For Attenuating the Noise of a Turbofan - The invention concerns a turbofan, characterized in that edge of the outlet ( | 08-28-2008 |
| 20080217101 | Method of Reducing Noise Emissions at the Rear of a Turboshaft Engine and Turboshaft Engine thus Improved - The invention relates to a method of reducing noise emissions at the rear of a turboshaft engine and to a turboshaft engine thus improved. According to the invention, the thickness of the rear part ( | 09-11-2008 |
| 20090078496 | Mixed-flow exhaust silencer assembly - An exhaust silencer assembly comprising a casing having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening, and an acoustic-attenuating porous liner disposed within an interior chamber of the casing, thereby dividing the interior chamber into an inner region located between the exhaust gas entrance opening and the exhaust gas exit opening, and an outer region located between the acoustic-attenuating porous liner and the casing, where the cooling air inlet opening is located at the outer region. | 03-26-2009 |
| 20090266642 | Engine Assembly, Acoustical Liner And Associated Method Of Fabrication - An engine assembly, an acoustical liner and an associated fabrication method are provided to address fan blade flutter and fan noise control simultaneously within the same liner area. Fan blade flutter is therefore controlled without necessarily increasing the weight of the engine, impairing the structural integrity of the engine, or increasing the noise generated by the engine. The acoustical liner may have additional acoustical degrees of freedom which permit these seemingly competing concerns to be addressed in a complementary manner. The acoustical liner may include inner and outer barrels with the inner barrel having a perforated face sheet, a perforated back skin and a core disposed between the perforated face sheet and the back skin. The fluid communication between the core and the space between the inner and outer barrels provides additional acoustical degrees of freedom which may be utilized to reduce fan blade flutter while concurrently limiting fan blade noise. | 10-29-2009 |
| 20090277714 | GAS TURBINE EXHAUST SOUND SUPPRESSOR AND ASSOCIATED METHODS - The gas turbine exhaust sound suppressor, or exhaust silencer, and method are for a gas turbine and reduce low frequency exhaust flow noise while avoiding the creation of additional acoustical standing waves, e.g. from wake shedding at certain predictable frequencies. A plurality of elongated flow obstruction members, e.g. pipes or airfoils, extend within the exhaust passage to reduce acoustic waves within the exhaust flow, and at least some of the elongated flow obstruction members have different widths. Each of the elongated flow obstruction members is positioned at a respective angle within a predetermined angular range transverse to the flow direction, with the predetermined angular range being greater than or equal to 10 degrees from normal to the flow direction. | 11-12-2009 |
| 20100006368 | Localized Decisions and Actions Determined from Communal Network of Observations in Order to Achieve Global Solution - A method is provided for making localized decisions and taking localized actions to achieve a global solution. In an embodiment of the present invention, acoustic impedances for impedance-tunable acoustic segments are adjusted. A first acoustic segment through an N-th acoustic segment are defined. To start the process, the first acoustic segment is designated as a leader and a noise-reducing impedance is determined therefor. This is accomplished using (i) one or more metrics associated with the acoustic wave at the leader, and (ii) the metric(s) associated with the acoustic wave at the N-th acoustic segment. The leader, the N-th acoustic segment, and each of the acoustic segments exclusive of the leader and the N-th acoustic segment, are tuned to the noise-reducing impedance. The current leader is then excluded from subsequent processing steps. The designation of leader is then given one of the remaining acoustic segments, and the process is repeated for each of the acoustic segments through an (N−1)-th one of the acoustic segments. | 01-14-2010 |
| 20100122868 | ACOUSTIC BARREL FOR AIRCRAFT ENGINE NACELLE INCLUDING CRACK AND DELAMINATION STOPPERS - An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel 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 from the inner skin to the outer skin. | 05-20-2010 |
| 20100212998 | CELLULAR-CORE STRUCTURE FOR AN ACOUSTIC PANEL - The invention relates to a cellular-core structure ( | 08-26-2010 |
| 20100236862 | ENGINE INLET DEEP ACOUSTIC LINER SECTION - An inlet of an aircraft nacelle having an acoustic barrel configured to reduce engine fan flutter by attenuating various frequencies. The acoustic barrel may comprise an acoustic panel of a honeycomb configuration sandwiched between a first back sheet and a face sheet and extending from a forward bulkhead to an aft bulkhead of the inlet. The acoustic barrel may further comprise a deep liner section bonded to and sandwiched between the first back sheet and a second back sheet. The deep liner section may have a narrower width than the acoustic panel and may be located proximate the aft bulkhead. The sections of the first back sheet, the face sheet, and a septum of the acoustic panel may be perforated and may contain additional holes formed in portions aligned radially inward of the deep liner section. | 09-23-2010 |
| 20110005858 | NOISE-REDUCED AIRCRAFT ENGINE AND METHOD FOR REDUCING NOISE EMISSIONS OF AN AIRCRAFT ENGINE - A method for reducing noise emissions of an aircraft engine ( | 01-13-2011 |
| 20110168482 | VANE TYPE SILENCERS IN ELBOW FOR GAS TURBINE - A silencer for a gas turbine includes a first duct portion; a second duct portion connected to the first duct portion, the first and second duct portions forming an elbow region at the connection; and a plurality of elbow shaped vanes provided in the elbow region. The plurality of elbow shaped vanes have equal lengths and are spaced equally apart. | 07-14-2011 |
| 20110220433 | COMBUSTOR AND GAS TURBINE HAVING THE SAME - An object is to provide a combustor that requires a small mounting space for an acoustic damper, that can achieve size reduction, and that can improve the ease of maintenance. A combustor ( | 09-15-2011 |
| 20110232991 | METHOD FOR BONDING HONEYCOMB CORES - A method for splicing honeycomb core together to form a core structure, such as an acoustic panel for an aircraft. The core structure may comprise a first honeycomb core, a second honeycomb core, and an intermediate bonding part disposed between the first and second honeycomb cores. The intermediate bonding part may comprise a syntactic core wrapped with or sandwiched between a non-foaming film adhesive. The syntactic core sandwiched between a first and second layer of film adhesive and a first and second honeycomb core is then compressed by vacuum and cured to bond the honeycomb cores together, forming the core structure. | 09-29-2011 |
| 20110284318 | SOUNDPROOF EXHAUST PIPE FOR A TURBINE ENGINE - The soundproofed exhaust duct for a turbine engine comprises a perforated inner shell defining a flow passage, and a solid outer shell, the inner and outer shells defining between them a space that is closed at the upstream and downstream ends of said space. A core extends between the inner and outer shells at a distance therefrom, and contains at least one sound energy dissipating layer made up of hollow beads that are held against one another. A frame with upstream and downstream portions connected together by longitudinal members supports the core and partitions it into a plurality of boxes that are filled with hollow beads that are held between perforated textures, the frame being secured to the outer shell and/or to the inner shell via at least one of its upstream and downstream portions. | 11-24-2011 |
| 20120006614 | GAS-TURBINE EXHAUST CONE - A gas-turbine exhaust cone includes a cone shaped outside cone | 01-12-2012 |
| 20120138383 | RADIATED SOUND REDUCING STRUCTURE - A radiated sound reducing structure that reduces radiated sound generated in a pipe through which gas passes includes a first pipe and a second pipe that is arranged inside the first pipe and has, on an outer peripheral surface, a linear contact portion that is in linear contact with a portion of an inner peripheral surface of the first pipe. Also, a radiated sound reducing structure in a pipe through which gas passes includes a first pipe and a second pipe formed in a pseudo-cylindrical concave polyhedral shell that is arranged inside the first pipe and has, on an outer peripheral surface, a point contact portion, that is in point contact with a portion of the inner peripheral surface of the first pipe. | 06-07-2012 |
| 20120160600 | TUBULAR ACOUSTIC INSULATING ELEMENT - An exhaust system composed of a plurality of components for an internal combustion engine for connecting to a manifold, the exhaust system includes at least one, first section, which is provided indirectly or directly after the manifold in the flow direction, arid a second section, which is directly adjacent thereto in the flow direction, wherein the two sections are connected to each other by a mechanical decoupling element. The resonant oscillations in the range above 600 Hz are to be attenuated in the exhaust system by more than 15 dB and, at the same time, the exhaust system is to be sufficiently rigid and self-supporting and designed to be lastingly gas-tight. For this purpose, a single-walled arid self-supporting acoustic insulating element is integrated in the exhaust system in the flow direction upstream of, or in, the first section. | 06-28-2012 |
| 20120228049 | ARRANGEMENT OF A SILENCER ON A COMBUSTION MOTOR WITH IMPROVED COUPLING TO THE CYLINDER - In order to improve an arrangement of a silencer on a combustion motor, whereby the silencer has a connection piece which with an end area adjoins an outlet in the cylinder of the combustion motor forms a flow connection between a combustion chamber of the combustion motor and the silencer in such a way a disturbance-free flow connection between a combustion chamber in the cylinder and the silencer is made possible, and more particularly to simplify the mounting of a silencer on the cylinder of a combustion motor, the internal diameter of the end area is made larger than the internal diameter of the outlet. | 09-13-2012 |
| 20120228050 | HELMHOLTZ RESONATOR FOR A GAS TURBINE COMBUSTION CHAMBER - A resonator is provided, having an adaptable resonator frequency for absorbing sound generated by a gas stream of a gas turbine. The resonator includes a neck section, a chamber and a deformable element being deformable under influence of a change of a gas turbine temperature of the gas stream. The shape of the deformable element is predetermined with respect to a respective gas turbine temperature. The neck section and the chamber form a volume of the resonator. The neck section forms a passage coupling the volume with the gas turbine. The deformable element is thermally coupled to the gas turbine in such a way that the shape of the deformable element depends on the respective gas turbine temperature. The deformable element forms a spiral and is installed to the neck section in such a way that an effective diameter of the neck section depends on the gas turbine temperature. | 09-13-2012 |
| 20120273297 | CHANNELING GAS FLOW TUBE - A tube for moving gas between an entry end into which gas is introduced and an exit end through which gas exits the tube, the tube comprising a plurality of adjoining adjacent□ guides, each guide comprising an outer half of a smoothly-curved, modified torus, and an outer rigid tube wall. Each guide forms an internal cavity with a cavity mouth opening into an inner portion of the tube, the cavities shaped such that a vortex forms within each of the cavities as gas passes through the tube, and the flow of fluid in the tube is unidirectional and axial from the entry end to the exit end. | 11-01-2012 |
| 20120292126 | METHOD FOR PROCESSING A SURFACE ELEMENT - A method for processing at least one surface element wherein at least one layer of a deformable, medium-tight material is respectively attached to each side of the surface element, inserts the surface element and attached deformable layers between at least two molding tool parts and applies a pressure to at least one area of a surface section of the inserted surface element in response to a predetermined shaping temperature by introducing a medium between one of the deformable layers and a first molding tool part. The pressure acts directly against the deformable layer so that the surface element together with the deformable layers is shaped into at least one adjacent cavity of a second molding tool part due to the pressure created. A possibility of molding surface elements, which can currently not be shaped via gas pressure, into complex geometries, namely into spatially bent geometries, is created with this method. | 11-22-2012 |
| 20130025962 | Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element - A gas-turbine exhaust cone has an outer wall with a plurality of recesses, a honeycomb-structured layer arranged at the inside of the outer wall and extending along said inside of the outer wall, an inner wall connected to the honeycomb structure and extending essentially parallel to the outer wall, and at least one annular chamber centered on a central axis and adjoining the inner wall. The inner wall has passage recesses connecting the area of the honeycomb structure to the annular chamber, with the annular chamber being subdivided in the circumferential direction by at least one partition wall into several chambers. The partition wall is made from a sheetmetal-like material and has a plurality of raised and/or recessed areas in a uniform arrangement formed by shaping of the sheetmetal-like material. | 01-31-2013 |
| 20130206500 | ACOUSTIC DAMPER, COMBUSTOR, AND GAS TURBINE - An acoustic damper is fixed to a vibration source to be provided along an outer surface of the vibration source, forms a passage that takes in air vibration generated by the vibration source, and is provided with an acoustic portion having a partition member closing the downstream side of the passage with respect to the propagation of the air vibration to serve as resistance against the air vibration, in which the acoustic portion allows air vibration to propagate in a reverse direction, and has partition members arranged so as to serve as resistance against the air vibration in respective directions. This allows to prevent from generating stress due to pressure fluctuation caused when reducing vibration, and to achieve a relatively compact size. | 08-15-2013 |
| 20130306400 | Method of Designing and Making an Acoustic Liner for Jet Aircraft Engines - A method for designing and manufacturing an acoustic liner for jet aircraft engines employing a spherical wedge-shaped physical model employing conservation of mass and momentum. The model has three dimensions and four empirical parameters: the location of the far-field driving acoustic pressure; the location wherein the acoustic-mean-flow is pumped into and out of the resonator volume; and two parameters that describe the acoustic-mean flow rates pumped into and out of the resonator. | 11-21-2013 |
| 20130319789 | TWO-STROKE ENGINE COMPRISING A MUFFLER - The invention relates to a two-stroke engine for an engine-driven tool, including a muffler, especially for a manually operated engine-driven tool such as a maintenance device for gardens or green spaces, for a hand-held tool such as a chain saw, a hand-held circular saw or an angle grinder or for a small motorcycle, a boat engine and the like, wherein the flow channel between the muffler inlet and the first chamber is formed so as to promote flow such that the exhaust gas entering the muffler inlet mainly enters the first chamber due to its inertia and once the first chamber is full flows back again. The counterpressure of the exhaust gas is produced at a point in time in which the piston releases the outlet and the fuel-air mixture at least for its most part has entered the combustion chamber through the at least one transfer passage. | 12-05-2013 |
| 20140020975 | RESONATOR SILENCER FOR A RADIAL FLOW MACHINE, IN PARTICULAR FOR A RADIAL COMPRESSOR - A volute for a radial turbomachine is proposed. The turbomachine includes a radial compressor or a radial turbine. The volute is in particular for a radial compressor. The volute has a substantially annular cavity which is delimited at least by a first radial side surface. At least one substantially annularly circumferential groove is formed in the side surface. | 01-23-2014 |
| 20140116801 | SILENCER AND A METHOD FOR PRODUCING SAME - A silencer ( | 05-01-2014 |
| 20140124289 | NOZZLE WITH GUIDING DEVICES - A nozzle has a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements. A wall element connects a first guiding device and a second guiding device. At least some of the first azimuthal guide walls of the first guiding device and at least some of the second azimuthal guide walls of the second guiding device have differing axial lengths, so that first and second trailing edges thereof have differing axial positions. | 05-08-2014 |
| 20150021117 | DUCT AND METHOD FOR DAMPING PRESSURE WAVES CAUSED BY THERMOACOUSTIC INSTABILITY - A duct and a method for damping pressure waves caused b thermoacoustic instability, the duct comprising: a locking Helmholtz resonator positioned on the circumference of the duct, the locking Helmholtz resonator tuned to a first frequency, and one or more damping Helmholtz resonators positioned on the circumference of the duct at or adjacent to 90 and/or 270 degrees from the locking Helmholtz resonator, wherein the damping Helmholtz resonators are tuned to a second frequency which is different from the first frequency of the locking Helmholtz resonator. | 01-22-2015 |
| 20150068834 | Resonance Generating Muffler - In accordance with at least one embodiment: a muffler with a case (comprised of at least one inlet, at least one outlet, and a body), and elongated members comprised of material capable of a predetermined resonance. The elongated members have sufficient length after their final point of attachment to vibrate when exposed to flowing exhaust gasses. This vibration results in resonance that is noise canceling and/or sound enhancing. The muffler may also contain any combination of sound baffles, sound absorbent material, and other sound altering devices. | 03-12-2015 |
| 20150337878 | CHANNELING FLUIDIC WAVEGUIDE SURFACES AND TUBES - Waveguide or flow guide surfaces can improve the efficiency of fluid flow through tubes or over surfaces. When incorporated in a tube, the waveguides improve flow and function as sound absorbers making them useful in engine mufflers, firearm silencer/suppressors and jet engine exhaust attenuators. On surfaces, the waveguides can reduce fluid drag and find use on projectiles (e.g., bullets), airfoils for aircraft, and land borne vehicles. The waveguide array in either a tubular chamber or on a surface comprises a plurality of successive wave-like undulations inclined generally in the direction of flow and when employed in tubes extending inwardly to permit an unobstructed path for the fluid gas from entry to exit. The waves define annular wave cavities between their successive inwardly extending edges and the wall of the chamber with each cavity having a cavity mouth open to the unobstructed path. The waveguides are sized and spaced so that gas vortices are created within the cavities when gas flow occurs which vortices create a fluid boundary layer that assists the gas flow. | 11-26-2015 |
| 20160001890 | APU EXHAUST SYSTEM - An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout. | 01-07-2016 |
| 20160017775 | NOISE ATTENUATING ACOUSTIC PANEL - An acoustic panel is provided that includes a first layer, a perforated second layer, a core and a noise attenuating feature. The core forms a chamber between the first and the second layers. The noise attenuating feature projects partially into the chamber. The noise attenuating feature is formed integral with the first layer, the second layer and/or the core. | 01-21-2016 |
| 181214000 | Upstream (e.g., intake silencer) | 15 |
| 20090014234 | Acoustic Panel - An acoustic panel for a fan casing of a gas turbine engine includes one or more Helmholtz resonators to absorb acoustic energy propagated upstream from the fan. By arranging that the periodic air flow out of the resonators has some axial momentum, by inclining the passages that from the necks of the resonators in a downstream direction, some of the energy in this air flow can be realised as a useful pressure rise in the direction of the air flow into the fan, rather than a pressure drop as in known acoustic panels. | 01-15-2009 |
| 20100096213 | COATING FOR ACOUSTIC TREATMENT HAVING A HOT AIR ICING PROCESSING FUNCTION OF FROST TREATMENT WITH HOT AIR - A coating for acoustic treatment relative to an aircraft's surface, in particular a leading edge such as an air intake of an aircraft nacelle, includes an acoustically resistive layer, at least one alveolar structure ( | 04-22-2010 |
| 20100108435 | METHOD FOR MAKING AN ACOUSTIC ABSORPTION PANEL IN PARTICULAR FOR THE NACELLE OF AN AIRCRAFT ENGINE - The invention relates to a method for making an acoustic absorption panel in particular for the nacelle of an aircraft engine, the panel being of the type comprising a cellular core covered on one side with a so-called outer air-permissive skin and on the other side with a so-called inner perforated skin, the cellular core being formed by the edge-to-edge junction of a plurality of blocks with a cellular core (B | 05-06-2010 |
| 20100206664 | Acoustic panel - An acoustic panel for a fan casing of a gas turbine engine includes one or more Helmholtz resonators to absorb acoustic energy propagated upstream from the fan. By arranging that the periodic air flow out of the resonators has some axial momentum, by inclining the passages that exit from the necks of the resonators in a downstream direction, some of the energy in this air flow can be realised as a useful pressure rise in the direction of the air flow into the fan, rather than a pressure drop as in known acoustic panels. | 08-19-2010 |
| 20100243370 | Aero-acoustic aviation engine inlet for aggressive noise abatement - An aero-acoustic aviation engine inlet with a single air blowing slot or multiple air blowing slots flows air over one or more segments of inlet acoustic lining surfaces at speeds that are higher than the inlet mean air flow speed, for aggressive inlet noise abatement. | 09-30-2010 |
| 20100263964 | INTAKE SILENCER FOR GAS TURBINE - An intake silencer of a gas turbine capable of efficient noise reduction in which a high frequency sound-absorbing splitter group composed of a plurality of sound-absorbing splitters capable of reducing highfrequency component noise and a middle/low sound-absorbing splitter group composed of a plurality of sound-absorbing splitters capable of reducing middle/low frequency component noise are disposed separately in a gas flow direction. High frequency component noise is reduced by the high frequency sound-absorbing splitter group, and middle/low frequency component noise is reduced by the middle/low sound-absorbing splitter group. | 10-21-2010 |
| 20120024622 | Gaseous-fluid supply system for noise abatement application - Gaseous-fluid supply system for a general industrial power machinery application and a class of laboratory noise research and development comprises three subsystems, namely a gaseous-fluid delivery subsystem, a gaseous-fluid settling subsystem and a gaseous-fluid duct subsystem. Each subsystem must satisfy a set of fluid dynamic requirements determined by the situation in hand. For noise abatement application and research, an addition set of self-noise requirements must also be satisfied. | 02-02-2012 |
| 20120241248 | TWO-STROKE ENGINE WITH A SILENCER - A silencer includes a silencer inlet followed by a flow channel. The inlet can be attached to an outlet of a combustion chamber of a two-stroke engine. The flow channel at the channel end located opposite the silencer inlet leads into a first chamber where a second chamber is provided into which exhaust gas flows through a main outlet branched off the flow channel. The second chamber preferentially encloses the first chamber. The flow channel is flow-favourably moulded between the silencer inlet and the first chamber so that the exhaust gas flowing into the silencer inlet, because of its mass inertia, predominantly flows into the first chamber and, after filling the first chamber, flows back again in the direction towards the combustion chamber. The silencer allows a piston of the engine to include a piston skirt that is substantially designed closed. | 09-27-2012 |
| 20120241249 | PANEL FOR THE ACOUSTIC TREATMENT WITH A PROGRESSIVE THICKNESS - An aircraft nacelle includes an air inlet ( | 09-27-2012 |
| 20130126265 | ENGINE INLET VARYING IMPEDANCE ACOUSTIC LINER SECTION - An inlet for an aircraft engine nacelle having an acoustic barrel panel, a septum buried or sandwiched within the acoustic barrel panel, and a perforated face sheet. The inlet may be located forward of an engine and/or an engine fan housed within the aircraft engine nacelle. Both the septum and the perforated face sheet may have perforations or holes therein of varying sizes and varying distances apart from each other. The smaller the area of the perforations or holes and the further apart they are from each other, the higher the impedance of a given area of the septum or the perforated face sheet. The impedance of the septum and/or the perforated face sheet may progressively increase in a direction away from the engine fan. | 05-23-2013 |
| 20130168180 | GAS TURBINE INLET SYSTEM - A gas turbine inlet system includes a main inlet portion, wherein an airflow is introduced to the gas turbine inlet system. Also included is a silencer assembly. The silencer assembly includes a first silencing panel, wherein the first silencing panel is oriented substantially perpendicularly to the airflow, and wherein the first silencing panel includes a first plurality of airflow apertures. The silencer assembly also includes a second silencing panel, wherein the second silencing panel is oriented substantially perpendicularly to the airflow, and wherein the second silencing panel includes a second plurality of airflow apertures. | 07-04-2013 |
| 20140069738 | DAMPING SYSTEM FOR COMBUSTOR - An acoustic damper arrangement for a combustor which has an inner liner configured for use at a first temperature during operation and an outer liner configured for operation at a second temperature lower than the first temperature during operation is disclosed, the acoustic damper arrangement comprising: a plurality of flexible sheets; and at least one hollow body having an interior volume, each of said at least one hollow body being fixed to one of the plurality of flexible sheets, wherein the acoustic damper arrangement is configured to be fixed to both the inner liner and the outer liner such that the interior volume of the at least one hollow body is in communication with a chamber formed by the inner liner, and the plurality of flexible sheets accommodate expansion and contraction of the inner liner relative to the outer liner. | 03-13-2014 |
| 20140291066 | AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural. | 10-02-2014 |
| 20150107935 | INTAKE SYSTEM HAVING A SILENCER DEVICE - An intake silencer device is described herein. The intake silencer device includes an outer housing and a plurality of sequential arranged expansion chambers separated by walls. The intake silencer device further includes an inner tube positioned in each of the sequential chambers, each of the inner tubes including an opening providing fluidic communication between an interior of the tube and the corresponding expansion chamber, a size of the openings increasing in size sequentially in a downstream direction. | 04-23-2015 |
| 20150354513 | Resonator Apparatus for Vehicles - A resonator apparatus for vehicles may include a housing configured to have a pipe shape and be disposed in an air passage to have air penetrating thereinto, a first baffle configured to have a pipe shape, be inserted into the housing, have an inner diameter smaller than an inner diameter of the housing, and be slidable in a length direction of the housing, and a second baffle configured to have a pipe shape, be inserted into the housing, have an inner diameter smaller than an inner diameter of the housing, be slidable in the length direction of the housing, and be spaced apart from the first baffle by a predetermined distance. | 12-10-2015 |
| 181215000 | With adjustable outlet nozzle | 5 |
| 20100314194 | TRAILING EDGE FOR AN AIRCRAFT ENGINE, OF THE TYPE WITH MOVING CHEVRONS - This trailing edge is of the type with moving chevrons ( | 12-16-2010 |
| 20110139540 | NOISE REDUCTION DEVICE FOR TURBOJET NACELLE WITH MOBILE CHEVRONS, AND ASSOCIATED NACELLE - The invention relates to a turbojet nacelle ( | 06-16-2011 |
| 20120255806 | NOISE REDUCTION OF SUPERSONIC JET ENGINES - A jet engine adapted for reducing far-field noise levels is disclosed. The jet engine has a plurality of flap assemblies that are disposed around a perimeter of an exhaust port of the jet engine. Each flap assembly is movable between a first position and a second position. The jet engine also includes a plurality of actuators respectively coupled to the plurality of flap assemblies. Each actuator is configured to selectively move the coupled flap assembly between the first and second positions. The jet engine also includes a controller that is coupled to each actuator. The controller is configured to cause at least one actuator to move the coupled flap assembly between the first and second positions at a determined frequency. | 10-11-2012 |
| 181216000 | Longitudinally adjustable section | 2 |
| 20080264718 | JET NOZZLE HAVING NOISE ATTENUATING SHIELD AND METHOD THEREFOR - An arcuate or semi-circumferential shield in the shape of a visor that is adapted to be secured to an external surface of a nozzle housing of a jet nozzle to attenuate jet noise generated by the jet nozzle. The shield may be fixedly secured to the nozzle housing or movably supported so that it can be moved between retracted and deployed positions. When used as a fixedly mounted component, or when positioned in its deployed position, a downstream edge of the shield extends past a downstream edge of the nozzle housing and the shield is spaced apart from an outer surface of the nozzle housing to form a channel therebetween. The shield is preferably orientated at approximately a bottom dead center of the nozzle housing. The shield operates to attenuate jet installation noise, and particularly jet installation noise experienced during the takeoff phase of flight of a jet aircraft, as well as to reduce jet installation noise that would otherwise propagate forwardly toward the cockpit of the aircraft. | 10-30-2008 |
| 20120111662 | ENGINE EXHAUST - It presents the novelty that the duct ( | 05-10-2012 |
| 181220000 | With disparate fluid mingling | 3 |
| 20110042162 | DEVICE FOR REDUCING NOISE GENERATED BY AN AIRCRAFT JET ENGINE WITH CURVE DUCTS - A jet engine, including a wall surrounding a first gas flow ejected from a downstream end of the wall along a longitudinal axis, a second flow of gas running outside the wall in a direction of ejection of the first gas flow, at least one duct arranged on the periphery of the downstream end of the wall which is desired to eject a gas flow for interacting with one and/or the other gas flow, the at least one duct including a terminal section provided at the free end thereof with an outlet opening through which the fluid is ejected. The terminal section successively includes a first section of straight duct aligned along a median axis and a second duct section forming a bend relative to the straight section, the second portion having a free end provided with the outlet opening and sufficiently close to the median axis of the first section to give the terminal section a reduced restriction in a direction of formation of the bend. | 02-24-2011 |
| 20110048847 | NOISE ATTENUATION DEVICE FOR REDUCING NOISE ATTENUATION IN A JET ENGINE TEST CELL - A noise attenuation device for use in a jet engine test cell for testing a jet engine comprising a carbon steel pipe which is aligned axially with direction of exhaust from the jet engine. The carbon steel pipe is positioned within an augmenter within the test cell. Cold air enters the front end of the carbon-steel pipe. Adding three times the mass of cold air to that of the hot jet exhaust allows the hot jet exhaust to mix with the cold air forming an engine exhaust-cool air mixture. When the engine exhaust-cool air mixture reaches the outlet end of the carbon steel pipe, its temperature is reduced from 3800° F. to less than 1200° F., which substantially reduces noise generated by the jet exhaust. Located in proximity to the rear end of the carbon steel pipe is an annular region which is formed between perforated side plates within the carbon steel pipe and the inner wall of the augmenter. The flow is diffused as the flow area expands in the annular region. The combination of the carbon steel pipe and the annular region slow the velocity of the jet engine exhaust-cool air mixture, further reducing noise production from the jet engine. | 03-03-2011 |
| 20130112497 | TURBOJET ENGINE NACELLE - A turbojet engine nacelle includes at least one nacelle element having a wall delimiting a main flow channel. The flow channel has a variable flow passage section. The cross-sectional area of at least one first area of the channel is greater than that of at least one second area of the channel. The turbojet engine nacelle further includes at least one secondary flow conduit establishing a fluidic connection between the first area and the second area of the channel and is arranged parallel to the channel. The wall of the nacelle element is at least partly covered by an acoustic damping panel extending in said areas of the channel. The conduit passes through the acoustic damping panel in order to establish the secondary flow via the acoustic damping panel. The present invention can be used in the avionics field. | 05-09-2013 |
| 181222000 | With sound absorbing material | 8 |
| 20080308345 | Assembly for Reducing Noise in Turbofan Engines - An assembly is provided for reducing the noise that is generated in the heating gas zone by turbofan engines. The assembly consists of an acoustically absorbent cladding in the heating gas flow channel of the turbofan engine. The cladding includes a plurality of neighboring cavities, into each of which four horns extends. The mouths of the horns are fixed to a perforated cover sheet. The cover sheet forms one wall of the heating gas flow channel. | 12-18-2008 |
| 20100126798 | PROCESS FOR THE PRODUCTION OF AN ACOUSTICALLY RESISTIVE STRUCTURE, THE ACOUSTICALLY RESISTIVE STRUCTURE THUS OBTAINED, AND COATING USING SUCH A STRUCTURE - A process for the production of an acoustically resistive structure that can be inserted in an alveolar structure so as to obtain a coating for the acoustic treatment, whereby the acoustically resistive structure includes at least one porous layer ( | 05-27-2010 |
| 20110108357 | ACOUSTIC PANEL FOR AN EJECTOR NOZZLE - The invention relates to an acoustic panel ( | 05-12-2011 |
| 20120228051 | ACOUSTIC SKIN FOR AN AIRCRAFT NACELLE ACOUSTIC PANEL - The invention relates to an acoustic skin ( | 09-13-2012 |
| 20130220731 | SPLICING OF CURVED ACOUSTIC HONEYCOMB - Honeycomb sections are bonded together with seams made up of an adhesive that is carried by a honeycomb seam support or a linked-segment seam support. The seams are particularly useful for splicing together curved honeycomb sections that contain acoustic septum. The curved acoustic honeycomb sections are spliced or seamed together to form engine nacelles and other acoustic dampening structures. | 08-29-2013 |
| 20140090923 | ACOUSTIC PANEL - An acoustic panel includes a first cellular layer with cells having a first axis, a second cellular layer with cells having a second axis, and a perforated septum layer separating the first layer and the second layer. The cells of both layers have an end distal to the septum layer and an end which meets the septum layer, and the maximum diameter of the cells of the first layer is less than the maximum diameter of the cells of the second layer. | 04-03-2014 |
| 20140158458 | EXHAUST CONE FOR AIRCRAFT TURBOJET ENGINE - An exhaust cone for an aircraft turbojet engine includes a front part which has a front end and a rear end. The front end is equipped with a front connecting flange connecting to an outlet of a turbojet engine and the rear end is equipped with a rear connecting flange connecting to a rear part of the exhaust cone. In particular, the front part is further equipped with a sound attenuation structure including an outer skin, and the outer skin overlaps the front connecting flange and the rear connecting flange. | 06-12-2014 |
| 20150367953 | ACOUSTIC LINER - An acoustic liner that may be for a turbofan engine includes a first panel that may be non-permeable and a permeable panel spaced from the first panel. A non-permeable wall located between the first panel and the permeable panel faces in a first direction away from the first panel and a non-permeable wall, also between the panels, faces in a second direction away from the first panel and traversing the first direction. The liner may further include a plurality of sidewalls spaced from one-another, extending between the panels, and through the walls. | 12-24-2015 |
