760 results about "Turbojet engine" patented technology

An air vehicle, such as a manned or unmanned air vehicle, has a fuselage, a rotor/scissors wing, and a scissors wing. At helicopter mode, the rotor/scissors wing rotates to make the air vehicle fly like a helicopter to achieve vertical and/or short take-off and landing, hovering, and low speed flying. At airplane mode, the rotor/scissors wing and scissors wing form a scissors wings configuration to maximize the air vehicle's flying efficiency at a wide range of speed and flying conditions by adjusting the yaw angle of the rotor/scissors wing and scissors wing. During the conversion from helicopter mode to airplane mode, the scissors wing generates lift to offload the rotating rotor/scissors wing and eventually the offloaded rotor/scissors wing's rotating speed is slowed and stopped so that the rotor/scissors wing can be locked at a specific position and the conversion can be achieved. In a reverse order, the air vehicle can convert from airplane mode to helicopter mode. Either turbofan or turbojet engine, or turboshaft/turbofan convertible engine can be used to power the air vehicle.

Turbojet engines and aircraft configurations for advantageous use of the turbojet engines; the turbojet engines utilizing ram air turbine units that centrifugally compress air isothermally for use in various combustion configurations designed for stoichiometric combustion, wherein a stream of by-pass ram-air jets is mixed with combustion gas jets for discharge in a common discharge nozzle.

The nacelle (1) comprises an air intake (5) upstream of the turbojet engine (2), a middle section (6) an internal casing (6a) of which is intended to surround a fan (3) of the turbojet engine (2), and a downstream section (7) comprising an external structure (7a)which is rigidly connected to a downstream part of the casing (6a) of the fan (3) so as to support the turbojet engine (2) and has means of attachment to a strut (12) intended to be connected to a fixed structure (13) of an aeroplane.

The present invention relates to a nacelle (1) for a turbojet engine comprising an air intake structure (4) capable of ducting a flow of air towards a fan and a central structure (5) intended to surround the said fan and to which the air intake structure is attached, the central structure comprising a casing (9) intended to surround the fan and an external structure (13), characterized in that the air intake structure comprises, on the one hand, at least one internal panel (41) attached to the central structure via the casing and therewith forming a fixed structure and, on the other hand, at least one longitudinal external panel (40) attached removably to the fixed structure and incorporating an air intake lip (4a), the said external panel being removable between an operating position in which the external panel is aerodynamically continuous with the external structure of the central section and the air intake lip provides aerodynamic continuity with the internal panel of the air intake structure, and a maintenance position in which the external panel is separated from the external structure of the central section and the air intake lip is separated from the internal panel of the air intake structure.

A lubrication system for an expendable gas turbine engine (20) having a rotatable shaft (26) is provided. Bearings (28) journal the shaft (26) for rotation about an axis. The system includes a vessel (46) for containing lubricating oil, a conduit (58) extending from the vessel (46) to the bearings (28), and a solenoid operated valve (70,76) in the conduit (58) and operable to only either fully open or fully closed. A control circuit (16) is provided for pulsing the solenoid (70) at a controlled rate to alternatingly (a) allow oil flow and (b) halt oil flow to the bearings (28) for a time insufficient to cause oil starvation of the bearings (28).

Device for aircraft thrust recovery capable of linking a turboshaft engine and an engine strut. A device for thrust recovery (16) linking a turboshaft engine to an aircraft engine strut comprising an attachment fitting (22) fixed to an engine strut, a control bar (38) articulated on the attachment fittings (22) and two coupling rods (24) linking the control bar (38) to the central engine casing, almost along the longitudinal axis of the latter. Links with play are envisaged between each of the coupling rods (24) and the attachment fitting (22), to ensure transmission of thrust forces in the event of rupture of one of the parts of the device. These links with play comprise pivoting axes (48) which intersect the longitudinal axes of the corresponding coupling rods (24).

Filter for application in motor vehicles in general, urban or rural use, terrestrial, aquatic or aerial use, such as car, motorcycle, truck, bus, train, boat, ship, vessel, airplane, jet ski, snowmobile, tractor, any vehicle or machine powered by a combustion engine, electric, hybrid, hydrogen, gasoline, methanol, ethanol, butanol, diesel, kerosene, or any other technology or fuel, which can also be applied to any equipment using a combustion engine, like generators or turbines for stationary power generation, large water pump and agricultural equipment use, and aircraft powered by turbo-jets, turbo-fans, turbo propellers, piston engines or others, and may also provide versions for residential, commercial, industrial and hospital use, among others, with the addition of a power supply (transformer) on the power input and a possible adjustment in a cabinet with appropriate design for each use.

Noise reduction sandwich panel, notably for an aircraft turbojet engine. In order to produce a noise reduction sandwich panel having a structure with two degrees of freedom, inserted separative components (20) are placed into the hexagonal cells (16) of the unique waffle core of the panel. More specifically, the separative components (20) have an substantially circular external peripheral edge, which allows them to be easily assembled, in spite of the deformations of the walls (18) of the cells (16) due to manufacturing tolerances and to the optional forming of the waffle core. Advantageously, several separative components (20) are supported by a same positioning unit (22), which then allows relative displacement between the separative components.

The present invention relates to a turbojet engine nacelle (1) comprising:—an air intake structure (4) capable of channelling an airflow towards a fan of the turbojet engine and comprising at least one longitudinal external panel (40) incorporating an air intake lip (4a),—a central structure (5) intended to surround the said fan and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity,—at least one internal panel (41) comprising an acoustic shelving fixed at its downstream end to an upstream end of the central structure (5) therewith forming a fixed structure of the nacelle (1), and—guide means (15) for guiding the external panel or panels (40) which are capable of allowing substantially rectilinear movement of the external panel (40) towards the upstream end of the nacelle (1) so as to be able to open up the air intake structure (4), the guide mans (15) being entirely fixed to the central structure (5).

The present invention relates to a thrust reversal device (1) for a turbojet engine nacelle, characterized in that: (i) the movable cowl (3) is provided with at least one driving lead screw (30) having at least one peripheral groove over at least part of the length thereof, whereby said groove can engage with a stationary guide means (31) of the nacelle so as to rotate the lead screw during the translational movement of the movable cowl; and (ii) the lead screw is associated with at least one means for transmitting (32, 35, 36) the rotational movement thereof towards at least one drive system (33, 34, 25) of the flap.

The invention discloses an aero-engine bearing fault diagnosing method. The method comprises: first, acquiring the vibration signal of a turbojet engine, the engine speed, the engine rotation speed, the engine exhaust temperature, the fuel flow, and the engine thrust; extracting the classical time-domain statistical characteristics, the frequency-domain characteristics of the various signals and obtaining the time-frequency domain characteristics based on wavelet packet decomposition; then using the deep Boltzmann machine to perform characteristics learning to the characteristic parameters of the various signals; then, proceeding to use the data integration technology to integrate the characteristics of the various sources learned by the deep Boltzmann machine; and finally, using the integrated characteristic parameters as the input of the classifier to the support vector machine, and classifying and identifying the engine fault. The method of the invention improves the identification precision and stability of the turbojet engine bearing fault, effectively mining the essential characteristics of data and greatly increasing the fault precision of the turbojet engine bearing.

The invention relates to the technical field of plane pneumatic layout design and discloses a plane in a supersonic speed plane layout. Wings are symmetrically arranged on the two sides of a fuselage; empennages are symmetrically arranged on the tail of the fuselage; rudders are arranged on the empennages; an engine is arranged on the fuselage; the head portion of the fuselage is sharp; the wings are two-degree-of-freedom wings and are connected with the fuselage through spherical hinges; wing control surfaces are arranged on the wings; the wing control surfaces are in shaft driving connection with the wings through actuation shafts; the engine is a turbojet engine and is arranged on the rear portion of the fuselage. The plane in the supersonic speed plane layout is provided with the two-degree-of-freedom wings, variable sweepback of the whole wings is achieved, and low-speed, subsonic-speed and supersonic-speed flying can be well considered. According to the demands of different flying states of the plane, efficient and safe control over the plane is achieved by controlling the two degrees of freedom of the wings, stability is high, and the plane is safe and reliable.

The invention discloses a centrifugal compressor. The centrifugal compressor comprises a central spindle, a centrifugal vane wheel, a centrifugal machine box, a continuous pressure expander and a pressure expander machine box, wherein the centrifugal vane wheel is arranged on the central spindle in a sleeving mode; the centrifugal machine box is arranged around the centrifugal vane wheel, and a first airflow passage is formed between the centrifugal machine box and the centrifugal vane wheel; the continuous pressure expander is connected with the centrifugal vane wheel and is positioned at the outlet of the first airflow passage, and the continuous pressure expander is a vane pressure expander; the pressure expander machine box is connected with the centrifugal machine box and surrounds the continuous pressure expander, and a second airflow passage communicated with the first airflow passage is formed between the pressure expander machine box and the continuous pressure expander. According to the centrifugal compressor in the embodiment, due to the adoption of a centrifugal structure, the disadvantage of an axial-flow compressor on the application of a small turbojet engine is overcome. Meanwhile, with the structure, the amount of components is reduced relative to a traditional centrifugal compressor.

The invention relates to a simulation experiment device for an aero-engine suction object on-line static monitoring system. An air inlet extension pipe is connected with an air inlet end of an aviation turbojet engine, a particle injection device is communicated with the air inlet extension pipe through an injection port in the air inlet extension pipe, and the air inlet extension pipe is provided with monitoring devices in a subsection mode. One end of an exhaust nozzle extension pipe is connected with a jet end of the aviation turbojet engine, and the other end of the exhaust nozzle extension pipe is connected with a tail gas cooling device. The air inlet extension pipe, the particle injection device, the aviation turbojet engine, the exhaust nozzle extension pipe and the tail gas cooling device are fixed on a mounting platform. The simulation experiment device can provide warning information at an early stage when the engine sucks abnormal particles and impeller damage breakdowns happen, effectively simulate engine gas path environment, and provide a low-cost and high-simulation effective experiment platform for research of the aero-engine suction object on-line static monitoring system.

The actuating device for opening and closing at least one shutter in a gas turbine engine such as a turbojet engine, comprises at least one actuator made of a two-way shape memory alloy having a first stable state at a first given temperature (θ1, θ3) in which state it actuates either the opening or the closing of the shutter, and a second stable state at a second given temperature (θ2, θ4), in which state it actuates either the closing or the opening of the shutter, respectively.

The invention discloses a suspension for suspending a jet engine on an aircraft support, comprising a beam (10) with a platform (11), a first side connection (20) and a second side connection (40), The second side connector (40) extends into the area of ​​the first pin by fingers (43) interstitially embedded in holes provided in the beam to form a backup safety connection; an intermediate connection (30) between side connections (20, 40), said beam comprising a clevis (13) for receiving said first connection pin (31 ) of said central connection (30), The first pin has a distance from the platform (11) so as to form a space between said platform (11) and said central connection (30), which space constitutes said hole, said second side in normal operation. Said fingers (43) of the connector (40) engage in said holes with clearance. The solution of the invention makes it possible to reduce the weight of the suspension and to simplify the corresponding machining.

The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistant mats, characterised in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.