FIELD: engines engineering.
SUBSTANCE: invention relates to thrust reversal of gas turbine engines. A method for reversing the thrust of a bypass gas turbine engine, which consists in shutting off the air flow in the secondary circuit and removing it from the engine in the form of jets directed in the direction of aircraft movement, according to the invention, when the engine is switched to the thrust reverse mode, holes are opened in the outer wall of the secondary circuit in the reverse section of the engine and a reverse hatch of the outer shell of the engine for the output of the reverse jet, at the same time, the air flow in the second circuit is blocked and the air from the second circuit is directed through open holes and radial channels into rotary inflatable air ducts made of airtight fabric, hermetically connected to their outlet, laid under the reverse hatch and having a smooth narrowing of the passage section, in which the air movement is turned to the side aircraft movements, accelerate it in the tapering part, and from which it is thrown into the atmosphere at an angle to the direction of movement of the aircraft; the outlet contour of the reverse nozzle, to which the fabric of the air ducts is attached, is extended beyond the cross section of the engine nacelle simultaneously with the opening of the reverse hatch with the help of power elements, setting the required angle of the reverse jet with respect to the axis of the engine, while placing the engine on a pylon under the wing, the reverse hatch is located in the upper part of the engine from the side of the pylon symmetrically to the vertical plane of the engine, and when the engine is located in the tail, it is located in the side of the engine from the side opposite the horizontal pylon. A reversing device is considered, containing a reverse hatch in the surface of the engine nacelle, rigidly connected to the movable part of the pylon fairing, if any, having an axis of rotation on the pivoting levers in the tail section and extending from under the reverse hatch beyond the shell on the pivoting levers, the output contour of the reverse nozzle in the bow of the engine, the outlet circuit of the nozzle is connected to the reverse hatch in its front part with the help of rollers installed on it, moving in the longitudinal grooves of the power ribs of the reverse hatch, the rotary levers of the nozzle through intermediate thrust-pushers are connected to the rods of the hydraulic cylinders of the nozzle drive and the reverse hatch, fixed on the power unit engine structure, under the reverse hatch are laid on both sides of the axis of the hatch with a smooth narrowing of the passage section, rotary inflated air ducts made of airtight fabric, the air inlet of which is connected to the outlet of the radial channels in the outer wall of the outer contour of the engine, and the air outlet of the woven air ducts is hermetically fixed on the outlet contour of the retractable reverse nozzle.
EFFECT: invention provides an increase in the efficiency of the thrust reverser, a reduction in the length of the aircraft landing run, as well as a decrease in the load on the friction brakes.
6 cl, 13 dwg
