774 results about "Turbojet engine" patented technology

The invention discloses a gear pump used for a microminiature turbo-jet engine, comprising a direct current motor, a pump body, an upper pump cover, a lower pump cover, a shell, a pair of driving and driven gears which are meshed and a driving shaft and a driven shaft. The driving gear is arranged on the driving shaft; the driven gear is arranged on the driven shaft and is aligned and meshed withthe driving gear; the lower pump cover is fixed on the direct current motor, the upper pump cover is connected to the lower pump cover and the plane of the pump body is pressed tightly and sealed so as to lead the structure to be simple; the shell is sleeved at the outside of the lower pump cover; the driving gear and the driving shaft adopt a method of combining clearance fit and a transmission pin to eliminate the installation error of an output shaft of the direct current motor; and an antifriction material is embedded at the positions on the lower pump cover and the upper pump cover corresponding to the driving gear and the driven gear so as to increase the reliability and durability of the gear pump. Most parts of the gear pump adopt aluminium alloy so as to reduce the weight furthest. The gear pump can control the rotating speed of the direct current motor by pulse-width modulation of a single-chip microcontroller and control the flow rate of the gear pump precisely.

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.

Device for aircraft thrust reovery 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).

The casing of the invention is of the type supporting series of stationary blades having disposed between them series of blades that are movable in rotation about a longitudinal axis. In characteristic manner, said casing comprises a main element and, at least facing one of the series of moving blades, an assembly comprising a plate made of a honeycomb material and a covering disposed on the face of the plate facing away from the blades so that said cells are open towards the blades, said covering being provided with holes that open out into cells of the plate, thereby forming open cells, said covering closing other cells of the plate, thereby forming closed cells, a cavity being formed between said plate and the inside face of said main element. Preferably, the casing forms the casing of an axial compressor operating at low pressure in a turbojet engine.