Abstract: A gas turbine engine (10) comprises a main fluid flow exhaust nozzle (30) bounding a main fluid flow path, and a cooling nozzle (38) provided upstream of the main fluid flow exhaust nozzle (30) in the main fluid flow path. The cooling nozzle (38) is arranged to provide cooling air to a surface (36) of the main fluid flow exhaust nozzle (30), the cooling nozzle (38) comprises first and second outlets (44, 46). The first outlet (44) is located adjacent the main fluid flow exhaust nozzle surface (36) and is spaced from the main fluid flow path by the second outlet (46). The second outlet (46) comprises a convergent divergent nozzle configured to accelerate cooling air exhausted from the second outlet (46) to a velocity greater than air exhausted from the first outlet (44).

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, a door, a main actuator, and an assist actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The door is pivotally coupled to the support structure and is rotatable between at least a first position and a second position when the transcowl translates between the stowed position and the deployed position, respectively. The main actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The assist actuator is coupled to the door, and is configured to supply an actuation assist force to the door and, upon rotation of the door to an intermediate position between the first position and the second position, to commence load sharing with the main actuator.

Abstract: A variable area fan nozzle actuation (“VAFN”) system is disclosed. The VAFN system may include an electrohydrostatic actuator (“EHA”) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

Abstract: The present invention relates to an aircraft gas turbine comprising a thrust-reverser device that is arranged at the rear area of an engine cowling and that has multiple cascade elements which are distributed at the circumference and which divert a stream, characterized in that the cascade elements are mounted in a displaceable manner, in that on both sides of each cascade element at least one gear rack is formed that can be displaced via a respective cog wheel which is coupled to a driving device, and in that each cascade element is connected to a rear area of the engine cowling via a coupling element for the purpose of displacing the engine cowling in the axial direction.

Abstract: A thrust reverser of a turbofan engine has a stationary structure, a translating structure capable of moving linearly between a forward position and an aft position, a translating member capable of moving linearly between a forward condition and an aft condition when the translating structure is in the aft position, and a blocker door device engaged pivotally to the translating member and capable of rotating from a stowed state when the translating member is in the forward position and to a deployed state when the translating member is in the aft condition. When the thrust reverser is stowed, the blocker door device is located radially outward from a pressure sleeve of the translating structure and does not substantially obstruct flow in a flowpath defined at least in-part by the pressure sleeve.

Abstract: A rear suspension for attaching an aeroengine (20) of longitudinal axis X to a carrier structure or mast (12) of an aircraft, the suspension including at least two clevis-forming vertical uprights (26A, 26B; 28A, 28B) supporting a respective horizontal slideway (30A, 30B) having a roller (32) freely mounted thereon that is suitable for moving in a slot (34A, 34B) in a lug (20A) arranged in a YZ plane of transverse axis Y and of vertical axis Z, in such a manner as to enable the aeroengine to move only in translation along the longitudinal axis X and in pivoting about said longitudinal axis X.

Abstract: An aircraft jet engine includes an exhaust-gas nozzle having a device configured to blow out an exhaust gas in a pulsating manner into an exhaust-gas stream so as to reduce noise. The exhaust-gas nozzle includes openings distributed along a circumference of the exhaust-gas nozzle and disposed upstream from a nozzle outlet. The openings communicate with the device.

Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.

Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.

Abstract: In one embodiment, a system includes a variable geometry resonator configured to couple to a fluid path upstream from a combustor of a turbine engine. The variable geometry resonator is configured to dampen pressure oscillations in the fluid path and the combustor.

Abstract: A box-shaped enclosure of a storage box includes a deadening wall or walls defining a storage space between first and second planes. The storage space is open at the first and second planes. A deadening wall member extends along the first plane. An auxiliary box-shaped enclosure is connected to the box-shaped enclosure so as to close the first plane of the box-shaped enclosure. The auxiliary box-shaped enclosure defines an auxiliary space isolated from the storage space with a deadening wall member. The storage space is connected to the fresh air through the ventilation opening and the auxiliary space. The deadening wall or walls of the box-shaped enclosure and the deadening wall member serve to prevent the leakage of the operating sound.

Abstract: It presents the novelty that the duct (6) for the exhaust (4) comprises at least two telescopic sections (5) with their corresponding perimetric acoustic cavities (7), in order to permit the length of the duct (6) to be varied and achieve a required attenuation of the noise produced in the combustion. By extending the sections (5) the attenuation of the noise is increased and by retracting them it is decreased, obtaining an exhaust (4) that is adapted to the needs of the noise required in each moment. It is applied to the exhaust of the APU of an aircraft, designed with the smaller dimensions of the exhaust (4) improving the aerodynamic conditions of the aircraft. So when the aircraft is in flight, in which the requirement of noise attenuation is less, the exhaust (4) is maintained in its retracted position, while when the aircraft is on the ground it is extended for greater attenuation of the noise, as is required on ground.

Abstract: A system for reducing an acoustic load of a fluid flow includes a first pipe to carry the fluid flow; a standpipe connected to the first pipe at an opening in the first pipe; and a standpipe flow tripper provided in the standpipe. The flow tripper includes an edge extending through the opening into the flow on a downstream side of the opening. A method of reducing an acoustic load of a standing wave in a standpipe connected to a first pipe configured to carry a flow includes disrupting the flow in the first pipe at a downstream side of an opening in the first pipe to which the standpipe is connected.

Abstract: A box-shaped enclosure of a storage box includes a deadening wall or walls defining a storage space between first and second planes. The storage space is open at the first and second planes. A deadening wall member extends along the first plane. An auxiliary box-shaped enclosure is connected to the box-shaped enclosure so as to close the first plane of the box-shaped enclosure. The auxiliary box-shaped enclosure defines an auxiliary space isolated from the storage space with a deadening wall member. The storage space is connected to the fresh air through the ventilation opening and the auxiliary space. The deadening wall or walls of the box-shaped enclosure and the deadening wall member serve to prevent the leakage of the operating sound.

Abstract: A box-shaped enclosure of a storage box includes a deadening wall or walls defining a storage space between first and second planes. The storage space is open at the first and second planes. A deadening wall member extends along the first plane. An auxiliary box-shaped enclosure is connected to the box-shaped enclosure so as to close the first plane of the box-shaped enclosure. The auxiliary box-shaped enclosure defines an auxiliary space isolated from the storage space with a deadening wall member. The storage space is connected to the fresh air through the ventilation opening and the auxiliary space. The deadening wall or walls of the box-shaped enclosure and the deadening wall member serve to prevent the leakage of the operating sound.

Abstract: A system for reducing an acoustic load of a fluid flow includes a first pipe. The first pipe includes a first end and a second end and a first aperture and a second aperture, the first and second apertures being intermediate the first and second ends. A second pipe includes a first end and a second end and a third aperture intermediate the first and second ends. The second pipe is connected at its first end to the first pipe at the first aperture. A bypass pipe includes a first end connected to the second aperture of the first pipe and a second end connected to the third aperture of the second pipe. A method of reducing an acoustic load of a flow in a standpipe connected to a first pipe configured to carry a main flow includes providing a bypass flow from the first pipe to the standpipe.

Abstract: A box-shaped enclosure of a storage box includes a deadening wall or walls defining a storage space between first and second planes. The storage space is open at the first and second planes. A deadening wall member extends along the first plane. An auxiliary box-shaped enclosure is connected to the box-shaped enclosure so as to close the first plane of the box-shaped enclosure. The auxiliary box-shaped enclosure defines an auxiliary space isolated from the storage space with a deadening wall member. The storage space is connected to the fresh air through the ventilation opening and the auxiliary space. The deadening wall or walls of the box-shaped enclosure and the deadening wall member serve to prevent the leakage of the operating sound.

Abstract: A jet engine includes a hollow nacelle including a front air intake section and a rear air outlet section having outer and inner annular surfaces which converge to form a trailing edge. A fan opposite the front air intake section to generate a cold stream. A generator downstream of the fan, to generate an axial hot stream. A cowl system including a rear section with outer and inner annular surfaces which converge to form an outlet orifice for the hot stream. The trailing edge of the nacelle forms the outlet orifice for the cold stream. Blind notches attenuate the jet noise at the periphery of the outlet orifice for at least one of the streams. The notches cut into one of the convergent annular surfaces forming the outlet orifice without cutting into the other of the convergent annular surfaces.

Abstract: The invention uses tubes for the reduction of radiated duct noise. The tubes may be used to attenuate narrow band noise by diverting a portion of the acoustic energy through the tubes back into the duct. Upon reintroducing the diverted flow out of phase with the primary flow, acoustic cancellation is achieved. The frequency at which this occurs is dependent on the difference in the path lengths through the tubes and the separation distance—the distance separating the inlet and outlet of the tube. This invention can be used over varying frequency ranges by using an arrangement of flexible, constant length tubes. The effective frequency range is tailored by varying the separation distance and also allows the varying the angular arrangement of the tubes for more effective attenuation of spinning modes having varying propagation angle.

Abstract: The invention uses tubes for the reduction of radiated duct noise. The tubes may be used to attenuate narrow band noise by diverting a portion of the acoustic energy through the tubes back into the duct. Upon reintroducing the diverted flow out of phase with the primary flow, acoustic cancellation is achieved. The frequency at which this occurs is dependent on the difference in the path lengths through the tubes and the separation distance—the distance separating the inlet and outlet of the tube. This invention can be used over varying frequency ranges by using an arrangement of flexible, constant length tubes. The effective frequency range is tailored by varying the separation distance and also allows the varying the angular arrangement of the tubes for more effective attenuation of spinning modes having varying propagation angle.

Abstract: 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.

Abstract: Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a bulkhead collar on the aircraft, a body section that is coupled to the forward section and a stinger cap that includes the replaceable acoustic liner. The replaceable acoustic liner is configured to be slideably received by the body section.

Abstract: Sound and power are an important part of the motorcycling experience. From the early days people have been attempting to get it “right” and have tried numerous ways to achieve the best of both worlds. Generally one had to be sacrificed to some degree to get the other. Tuning the exhaust rather than tuning the carburetor or increasing cubic inches is a less expensive and more efficient way to get both the sound and midrange power that motorcyclists are looking for. With the exhaust enhancement device of the present invention, exhaust pipes can be tuned for sound and increased midrange power very simply and easily by installing them in the exit end of an aftermarket straight type pipe using various combinations to achieve a desired sound and not sacrifice power.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (i) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube portion therebetween; and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube. The assembly of this invention may be used in a method for reducing noise, the method comprising: (a) providing means for generating non-uniform noise energy about an inner surface and within a disclosure having at least an inlet; (b) providing an assembly for reducing noise comprising; (i) at least one having an inlet end, an outlet end and a central tube portion therebetween, and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube; and (c) directing at least a portion of the non-uniform noise into the assembly.

Abstract: A motorcycle exhaust control system for covering exhaust cross-over pipes is comprised of an elongate tubular crossover block-off member having a side wall. The crossover block-off member side wall has a slit extending the length thereof. The crossover block-off member forms the springed structure capable of placement in a motorcycle exhaust pipe. The crossover block-off member is capable of self-detainment in the motorcycle exhaust pipe. The crossover block-off member is capable of blocking the motorcycle exhaust pipe crossover.

Abstract: In order to reduce noise effectively and to provide a light-weight noise reducing apparatus and an exhaust nozzle for a jet engine, a mixer for mixing an exhaust gas and an external air is disposed behind an engine, a flow channel for accelerating an exhaust gas toward a mixer and a flow channel for introducing an external air to a mixer are formed by a flow channel forming section in a noise reducing mode.

Abstract: Sound and power are an important part of the motorcycling experience. From the early days people have been attempting to get it “right” and have tried numerous ways to achieve the best of both worlds. Generally one had to be sacrificed to some degree to get the other. Tuning the exhaust rather than tuning the carburetor or increasing cubic inches is a less expensive and more efficient way to get both the sound and midrange power that motorcyclists are looking for. With the Exhaust Enhancement exhaust pipes can be tuned for sound and increased midrange power very simply and easily by installing them in the exit end of an aftermarket straight type pipe using various combinations to achieve a desired sound and not sacrifice power.

Abstract: A sound suppressor exhaust structure for a jet engine. The exhaust structure has a nozzle body having a generally cylindrical forward intake opening to accommodate an aft end of a jet engine, and a generally quadrilateral aft exit opening. An openable sound suppression chamber is situated aft of the exit opening and is formed by two opposing enclosure structures each having a major surface and each hingedly attached in a clamshell manner to the nozzle body. The opposing enclosure structures are movable between an open and a closed configuration such that, when the enclosure structures are closed, a chamber having a generally quadrilateral cross section is defined and situated aft of the exit opening. Each enclosure structure has a major surface through which are substantially uniformly disposed a plurality of small apertures such that from about 15% to about 25% per square foot of each major surface is void and from about 45 to about 65 apertures are provided per square foot.

Abstract: An active noise reduction device for reducing the noise produced by cooling fans in a computer. The active noise reduction device comprises a duct mounted on the casing of the computer and having at least one air passage. One end of the passage communicates with the interior of the casing near the cooling fans and the other end is open to the atmosphere. A first microphone is arranged in the duct near the first end opening for detecting noise, and a second microphone is arranged in the duct near the second end opening. A speaker is arranged in the duct near the second opening, and a controller controls the speaker in response to outputs of the first and second microphones for reducing the noise produced in the casing. The speaker makes a sound having a reverse phase to that of the noise produced in the computer and the speaker sound is superimposed on the noise.

Abstract: A noise suppression system for use with a jet aircraft engine having a plug support cylinder affixed to the engine, a tubular ejector shroud affixed to the engine and encompassing the plug support, the shroud having a reduced internal diameter adjacent the aft end and a plurality of spaced apart blow-in openings formed circumferentially about the shroud forward end providing passageways for the entrance of ambient air from the exterior to the interior of the shroud. A blow-in door is secured to the shroud for opening and closing each of the blow-in openings. A translating plug is supported on the plug support cylinder and is positionable between a forward position and an aft position and forms an annular exhaust nozzle between the exterior of the plug and the interior of the aft end of the shroud. A daisy mixing nozzle is positioned within the shroud aft of the blow-in doors, the nozzle being configured of a plurality of lobes providing undulating interior and exterior surfaces.

Abstract: An aircraft jet propulsion power plant is fitted with a sliding ejector sleeve for the provision by selection, of an auxiliary flow of ambient air within the sleeve so as to quieten the noise of the gas efflux. The sleeve is mounted independently of the power plant and is supported from a side of the aircraft fuselage. The sleeve mounting structure has an arm which projects into the fuselage to provide a further mounting point, the reaction loads of which act downwardly so as to counteract the downwardly acting weight of the cowl on the side mounting.