215results about "Noise reduction installations" patented technology

Aspects of the invention are directed to an acoustic resonator with improved impingement cooling effectiveness. The resonator includes a plate with an inside face and an outside face. A plurality of passages extend through the plate. The resonator includes a side wall that extends from and about the plate. A plurality of cooling tubes are attached to the resonator plate such that an inner passage of each cooling tube is in fluid communication with a respective passage in the resonator plate. The resonator can be secured to a surface of a turbine engine combustor component to define a closed cavity. The ends of the cooling tubes are spaced from the surface. Thus, a coolant can enter the passages in the plate and can be directed to the surface so as to impingement cool the surface. The cooling tubes can minimize coolant loss by dispersion in the cavity.

In accordance with the present invention an aircraft floor panel is provided comprising a honeycomb core element having an upper core surface, a lower core surface, and a core thickness. An upper face sheet assembly is mounted to and seals the upper core surface and includes at least one upper material sheet impregnated with an upper epoxy resin. A lower damping face sheet assembly is mounted to and seals the lower core surface and includes at least one lower material sheet infused with a highly damped lower epoxy resin. The lower damping face sheet assembly dampens vibrational noise.

A lift-fan airplane lands vertically on dirt, kicking up debris but bringing a landing pad for use by others. The landing pad comprises many long slats hinged to each other at the sides. The slats are of generally increasing widths for rolling up into a tight spiral. This compact state allows low-drag air transport. After landing, the spiral is unrolled. A central slat has two stub axles sticking out the ends. Two men place a large wheel onto each stub axle, then push on the wheels to unroll the landing pad on the ground. An upturned wall at the end of the pad deflects upward the downwash from landing lift-fan VTOL airplanes, creating a shadow zone free of flying debris. This creates safe parking for massed operations. Inflated balloons, wedge-shaped to streamline necessary protuberances, detach and fill any large potholes under the landing pad.

An aircraft engine assembly is provided that is adapted to reduce noise produced by an engine included in the engine assembly. The engine assembly includes a nacelle having an inlet section and a main section that is houses the engine and fan assembly associated with the engine. The inlet section is coupled to the main section at a main bulkhead junction between the inlet section and the main section. A one piece annular acoustic panel is located within a recess in an internal wall of the nacelle. The annular acoustic panel extends from a forward portion of the inlet section to a forward portion of the main section such that the bulkhead is covered by the annular acoustic panel.

A cooled acoustic liner useful in a fluid handling duct includes a resonator chamber 52 with a neck 56, a face sheet 86, and a coolant plenum 80 residing between the face sheet and the chamber. Coolant bypasses the resonator chamber, rather than flowing through it, resulting in better acoustic admittance than in liners in which coolant flows through the resonator chamber and neck. In one embodiment, the liner also includes a graze shield 88. Openings 40, 38 penetrate both the face sheet and the shield to establish a relatively low face sheet porosity and a relatively high shield porosity. The shielded embodiment of the invention helps prevent a loss of acoustic admittance due to fluid grazing past the liner. Another embodiment that is not necessarily cooled, includes the resonator chamber, low porosity face sheet and high porosity shield, but no coolant plenum for bypassing coolant around the resonator chamber. An associated method of retrofitting an acoustic treatment into a fluid handling module includes installing openings in the module and mounting a resonator box 44 on the module so that the inlets to the resonator necks register with the installed openings.

Sound attenuating laminates, and methods of making the same, are provided. Heat is applied to a surface of a non-woven, fibrous layer of material to form a stratum of melted fibers having a density greater than that of the remainder of the fibrous layer. The density of the melted fibers is effective in attenuating noise traversing the fibrous layer of material. Upholstery material, such as carpeting, is attached to the surface of the heated fibrous layer. The fibrous layer and upholstery material are then subjected to compressive molding pressure to obtain a desired shape. The compressive molding pressure may further tune the sound attenuating properties of the fibrous layer by selectively changing the densities of portions of the fibrous layer.

One or more Helmholtz-type resonators (270) is / are provided at the junction (260) of a combustor (220) and a combustion chamber (240) of a gas turbine engine (100). In one embodiment, adjacent Helmholtz-type resonators (290, 291, 292), which may be separated by respective baffles (285), have different volumes that help provide for damping different undesired combustion-generated acoustic pressure waves. In some embodiments, a structural member (435) may be provided between adjacent Helmholtz-type resonators (425, 426, 427, 428) at the junction. At least one of the plurality of Helmholtz-type resonators comprises one or more inlet openings (480), and one or more exit openings (482). Embodiments (370, 425-429) are described in which Helmholtz-type resonators provided at the junction are enlarged in size using various approaches. The positioning at the junction, upstream of the space (242) in which combustion occurs, and providing a plurality of differently sized resonators, provides for improved flexibility and resonator damping efficiencies.

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.

An acoustic absorbing device includes a housing having a chamber formed by an outer peripheral wall and a bottom wall, a hood engaged into the housing, an absorbing member engaged into the hood, and a silencer engaged into the absorbing member, the silencer and the absorbing member may be selectively attached to the hood or may be easily replaced with the other ones or new or different ones according to different environment. The silencer may include an outer cap extended into or out of the absorbing member. The housing includes one or more couplers for selectively coupling the housing to the other coupling or supporting members.