The present invention provides an improved blade and blade hub assembly. According to a first preferred embodiment, the present invention provides an apparatus for attaching light-weight foam blades onto an injection molded hub to be used in an unguarded fan assembly. According to a further preferred embodiment, the present invention preferably further provides a foam blade design in which the more centrally located portion of the blade is inserted into slots that are molded into an injection molded hub. According to a further preferred embodiment, the slots of the present invention preferably keep the blade in a desired camber and support the blade in the proper angle and orientation.

There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.

A thermal coupling assembly for facilitating thermal transfer between a heat source and a heat sink is provided herein. The thermal coupling assembly includes a thermally conductive element, an insulative wrap, and a cover. The thermally conductive element includes a first end wall configured to engage a surface of the heat source, a second end wall configured to engage a surface of the heat sink, and a body including a thermal conductor. The insulative wrap at least partially surrounds the thermally conductive element, the heat source, and the heat sink. The cover at least partially surrounds at least one of said insulative wrap, the thermally conductive element, the heat source, and the heat sink.

A machine includes a section that defines a target vibrational mode to dampen and a nanocellular foam damper that includes interconnected ligaments in a cellular structure. The interconnected ligaments have an average ligament size defined with respect to a vibrational loss modulus of the nanocellular foam damper and the target vibrational mode. Also disclosed is a method of damping vibration.

A fan has a fan housing and an impeller mounted in the fan housing. The fan housing has a main case, and a foamed metal plate securely mounted in an air inlet of the main case. Hot air inhaled into the main case is forced to flow through pores in the foamed metal plate. Thus, heat in the hot air is conducted to the foamed metal plate and then to the main case. The heat in the hot air is dissipated to reduce temperature of the hot air in advance. Accordingly, heat dissipation efficiency of the fan is improved. Since the foamed metal plate hinders flow of the hot air, the hot air flowing into the main case is reduced. Therefore, air pressure and flowing speed of the hot air flowing into the main case is reduced, such that noise made by the fan is also reduced.

An air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.

An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

Provided is an arrangement for discharging current due to a lightning stroke at a tip add-on of a rotor blade of a wind turbine, the arrangement including a conductor adapted to conduct the current due to the lightning stroke; an insulation arranged around the conductor, the insulation with the conductor being arrangeable within the tip add-on.

An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.