51results about "NACA type air intakes" patented technology

A door assembly has a first door integrated with a second door. The first door has a first door cowl. The second door is pivotably mounted to the first door and has a second door cowl forming at least a portion of the first door cowl. The door assembly includes at least one actuator coupled to the first and second doors. Each one of the first and second doors is pivotable between open and closed positions and defines an opening when moved to the open position. The openings of the first and second doors face in opposite directions. The actuator is operative to pivotably move at least one of the first and second doors between the open and closed positions.

The invention relates to a fresh air inlet for an aircraft that features at least one ram air inlet with at least one ram air inlet opening, at least one secondary air inlet opening that is spaced apart from the ram air inlet and at least one movably mounted flap, wherein the flap can be moved into a first position and into a second position, and wherein the flap essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and at least in certain areas extends into the air flow directed toward the ram air inlet opening in order to shield the ram air inlet opening from foreign matter in the second position. The air inlet according to the invention makes it possible to reduce the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. This results in that the actual ram air inlet can be optimized for cruising phases, and that the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.

An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment.

An air duct for supplying ambient air in an aircraft includes an air inlet, a flow duct portion and a feed device that is devised to feed ambient air through the air inlet and the flow duct portion. A flow control flap closes the air inlet in a first position, releases a first flow cross-section of the air inlet in a second position and releases a larger second flow cross-section of the air inlet in a third position. The flow control flap is designed to not increase drag significantly in the second position while still enabling flow through the flow duct portion, while increasing drag to increase air fow through the flow duct portion in the third position.

A ram-air duct includes a ram-air inlet duct and a ram-air outlet duct arranged downstream of the ram-air inlet duct and in fluid communication with the ram-air inlet duct. At an inlet of the ram-air inlet duct, a first movable element is arranged and adapted to set an inlet parameter of the inlet. At an outlet of the ram-air outlet duct, a second movable element is arranged and adapted to set an outlet parameter of the outlet. The outlet parameter and the inlet parameter are linked together by a function, so that an outlet parameter corresponding to a value of the function is assigned to each inlet parameter. A controller implements the control function by actuating movements of the first and second movable elements.

A fresh air inlet for an aircraft features a ram air inlet with a ram air inlet opening, a secondary air inlet opening separate from the ram air inlet and a movably mounted flap. The flap can be moved into a first or second position, and essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and extends away from the aircraft body in the second position to shield the ram air inlet opening from foreign matter in the air. The secondary air inlet reduces the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. The ram air inlet can be optimized for cruising phases, and the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.

A fluid cooling device for the propulsion unit of a propfan type aircraft including a compressed air intake at the air compressor of the turbomachine, an air vein capable of conveying the collected compressed air to a cooler, and a system for conveying the heat of the lubricant to the cooler is provided. The cooler includes a matrix body provided with a plurality of ducts for a cooling agent, the ducts extending along a first inner surface up to a second outer surface of the matrix body such that the collected pressurized air serving as a cooling agent can pass through the matrix body, the matrix body of the cooler forming a portion of the outer skin of the propulsion unit; and a set of fins extending from the outer surface towards the outside of the propulsion unit, and oriented mainly parallel to the air flow direction when the aircraft is in flight.

A ram air fan inlet housing for containing a ram air fan rotor. The inlet housing includes a flanged surface and an interior surface. The flanged surface is perpendicular to an axis of the inlet housing and defines a flange plane at an axial end of the inlet housing. The interior surface is symmetric about the axis of the inlet housing and includes a flange section, a transition section, an outlet section, a rotor section, and an inlet section.

The invention relates to a fluid cooling device (1) for the propulsive unit of an aircraft of the so-called propfan type, comprising a compressed air intake (11) at the air compressor of the turbine engine (8), an air seam (13) capable of conveying the collected compressed air to a cooler (14), means for conveying the heat of the lubricant to the cooler, said cooler (14) comprising a matrix body (15) provided with a plurality of pipes (20) for a coolant, said pipes (20) extending along a first so-called inner surface (17) up to a second so-called outer surface (16) of the matrix body (15), such that the collected compressed air serving as a coolant can pass through the matrix body (15), the matrix body (15) of the cooler (14) forming a portion of the outer skin (6) of the propulsive unit, as well as a blade assembly (18) extending from the outer surface (16); towards the outside of the propulsive unit, and oriented mainly parallel to the air flow direction (X) when the aircraft is in flight.

An apparatus comprises a leading edge of an inlet. The leading edge of the inlet is positioned relative to a direction of air flow such that a total pressure of air along the leading edge of the inlet is equalized within selected tolerances.

An apparatus comprises a leading edge of an inlet. The leading edge of the inlet is positioned relative to a direction of air flow such that a total pressure of air along the leading edge of the inlet is equalized within selected tolerances.

A method for increasing the total-to-static pressure ratio across a Ram Air Turbine (RAT) has designed and experimentally tested. The invention develops a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Full-scale wind tunnel experimenting testing shows that creating this low static pressure region behind the turbine resulted in significant increases in turbine output power when compared to a turbine that is not subjected to this invention. The invention showed the ability to increase the total-to-static pressure ratio across the turbine.

A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler.

The assembly has a ventilation device (1) for ventilation of a compartment (4) formed between an engine (2) and a nacelle (3). The ventilation device includes an air intake (11) adapted to capture air flow (F) outside the compartment (4), an air diffuser (12) adapted to guide the air flow (F) into the compartment (4), and an air distributor (13) adapted to distribute the air flow (F) within the compartment (4). The air distributor (13) in the device is separated from the air diffuser (12) and positioned within the compartment (4) at distance from the air diffuser (12).

A ventilation device for a compartment, preferably a compartment of an aircraft engine, the device including an air intake adapted to capture a flow of air outside the compartment, an air diffuser adapted to guide the air flow into the compartment, and an air distributor adapted to distribute the air flow within the compartment, the air distributor in this device being separated from the air diffuser, and being placed inside the compartment at a distance from the air diffuser

The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.

The invention relates to an air duct (10) for supplying ambient air in an aircraft, comprising an air inlet (12), a duct channel section (16) extending downstream of the air inlet (12) and an air conveying device (22) which is adapted to convey ambient air through the air inlet (12) and the duct channel section (16). A flow control flap (24) closes the air inlet (12) in a first position, releases a first flow cross-section of the air inlet (12) in a second position and releases a second flow cross-section of the air inlet (12), which is larger than the first flow cross-section, in a third position.; The flow control flap (24) is designed and arranged in such a manner that a first surface section (28) of the flow control flap (24) is oriented substantially parallel to an aircraft shell section (18) surrounding the air inlet (12) in the area of the air inlet (12) in the second position of the flow control flap (24) and that the first surface section (28) of the flow control flap (24) is oriented at an angle with respect to the aircraft shell section (18) surrounding the air inlet (12) in an area of the air inlet (12) in the third position of the flow control flap (14).

An aircraft ventilating air intake arrangement has an air passage channel and an air vent that ventilate a confined cone in an aircraft with fresh air entering the channel upstream and exiting the channel downstream towards the zone to be ventilated. A controllable blocking device enables the cross section of the channel to be varied with an elastically deformable membrane, under the action of fluid control, according to the speed and the altitude of the aircraft.

An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a second end that is coupled to the outer surface. The recessed portion further includes a first sidewall, a second sidewall opposing the first sidewall, and an inlet opening defined within the recessed portion. The inlet opening is bounded by the first sidewall, the second sidewall, and the second end, and the inlet opening is configured to receive a fluid stream therethrough. The air intake system further includes an actuation component coupled to the angled bottom member. The actuation component includes a shape memory alloy, and the actuation component is responsive to a change in a thermal condition and configured to move the second end, thereby regulating the inlet opening.

Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air.

The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.

The invention relates to an arrangement (1) that comprises a mobile plate (18) controlled by a means for fluid communication (23) between the outer (18A) and inner surfaces of the mobile plate (18), wherein said means is located at least in the vicinity of a limited downstream area (24) of said outer surface (18A), are at a high pressure when the aircraft flies at cruising speed, and are capable of transmitting said high pressure to an extended area (26) of said inner surface.

Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air.

An air intake arrangement includes a mobile plate controlled by at least one fluid communication passage or opening extending between the outer and inner surfaces of the mobile plate. The fluid communication passage or opening is located at least in the vicinity of a limited downstream area of the outer surface, is at a high pressure when the aircraft flies at cruising speed, and is capable of transmitting the high pressure to an extended area of the inner surface. The air flowing through the air intake arrangement may be used to refresh an enclosed area with electrical or mechanical equipment.

An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

An environmental control system including an upstream assembly supplying outside air to a rotary system of an aircraft, the air not having passed through a propulsion engine of the aircraft, and wherein the rotary system includes a rotary shaft, a power turbine, a compressor and a cold turbine, and wherein the upstream supply assembly is connected to an inlet of the compressor mounted with the rotary shaft that is rotated by the power turbine and wherein the shaft is supplied with compressed gas from the compressor toward the cold turbine.