1707results about "De-icing equipments" patented technology

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

A composite structure includes a matrix material and a carbon nanotube (CNT)-infused fiber material that includes a plurality of carbon nanotubes (CNTs) infused to a fiber material. The CNT-infused fiber material is disposed throughout a portion of the matrix material. The composite structure is adapted for application of a current through the CNT-infused fiber material to provide heating of the composite structure. A heating element includes a CNT-infused fiber material includes a plurality of CNTs infused to a fiber material. The CNT-infused fiber material is of sufficient proportions to provide heating to a structure in need thereof.

The heating device comprises electrically conducting longitudinal fibers extending substantially parallel to a leading edge of the aerofoil close to said leading edge, and means for electrically connecting the ends of the longitudinal conducting fibers to an electric power supply. The conducting fibers are grouped together in conducting rovings forming part of a hybrid fabric which furthermore includes a weft of electrically insulating fibers woven together and woven with the conducting rovings.

An aircraft engine nacelle comprises: (a) an inlet lip and a skin having internal and external surfaces; (b) a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; and (c) an electrically powered de-icing system located on the external surface of the nacelle skin and in electrical connection to a power source. A method for de-icing and abating noise from an aircraft nacelle comprises: (a) providing a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; (b) providing an electrically powered de-icing system on the external surface of the nacelle skin; and (c) applying an electric current to the electrically powered de-icing system. The nacelle skin may be a perforated skin, and the de-icing system comprises a wire mesh bonded to the external surface of the perforated skin. The method and nacelle permit the use of noise abatement structures such as acoustic panels for noise reduction while advantageously avoiding detrimental high temperatures associated with conventional de-icing systems.

A de-icing and anti-icing arrangement for a Wind Energy Converting System (WECS), a WECS comprising a de-icing and anti-icing arrangement and a method for preventing and eliminating ice accretion on the rotor blades of a WECS are provided. The WECS comprises a tower, a rotor having a plurality of blades that rotate due to wind force, a nacelle including a first means for transforming the rotor's rotational movement to electric power, and a second means for permitting the flow of fluid from volumes defined by the rotor blades, the rotor blades comprising an external surface having openings in fluid connection with the volumes inside the blades for permitting the flow of fluid to the outside of the blades to fluid-thermodynamically interact with the wind hitting the part of the blade surface, and thereby prevent or eliminate the accretion of ice on the external surface of the blade.

Anti-icing methods and aerodynamic structures having laminated resistive heaters for de-icing are described. Several of the inventive aspects utilize laminated resistive heaters comprising a carbon nanotube layer and/or capacitors to store and supply electricity. The invention also includes methods of making aerodynamic structures having de-icing or anti-icing functionality.

The bay (12) of a turbofan engine (10) comprises a front structural element (30), whose external surface is continuous and extends over at least 50% of the geometrical chord of the bay. Said element (30) is installed on maintaining and guiding members (44), such as slides, which prevent a significant deformation in flight and allow a sliding to the front of the element (30) for maintenance purposes. A laminar air flow around the front half of the bay (12) is consequently ensured.

Systems and methods of detecting type I ice crystals using an aircraft's onboard weather radar system are disclosed. An exemplary embodiment identifies radar returns having a return level signal strength less than a radar return sensitivity threshold level, determines if at least one of a weather condition and a flight condition concurrently exists with the identified radar returns having the return level signal strength less than the radar return sensitivity threshold level, and identifies a region of airspace potentially having type I ice crystals when the at least one of the weather condition and the flight condition concurrently exists with the identified radar returns having the return level signal strength less than the radar return sensitivity threshold level.

An article has a surface topography for resisting bioadhesion of organisms and includes a base article having a surface. A composition of the surface includes a polymer. The surface has a topography comprising a pattern defined by a plurality of spaced apart features attached to or projected into the base article. The plurality of features each have at least one microscale dimension and at least one neighboring feature having a substantially different geometry. An average feature spacing between adjacent ones of the features is between 10 μm and 100 μm in at least a portion of the surface. The surface topography can be numerically represented using at least one sinusoidal function. In one embodiment, the surface can comprise a coating layer disposed on the base article.

An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding.

The concept of the present invention describes configurations to provide uniform heat distribution of resistive heaters. This configuration allows successful anti-icing and deicing with relatively low applied power. One aspect involves the use of a thin film heater applied just underneath the topcoat to efficiently direct all heat to the surface, allowing anti-icing and de-icing with minimal power. This can be accomplished by employing a hybrid electrode interface, using a metal foil or metal braid that is attached to the aircraft surface with a structural adhesive that has been smoothed along the edges with metal-filled adhesive. Another aspect of the present invention uses an array of heater cells created as a single sheet and a heat spreading material, provided underneath or overtop of the heater cells.