RU2462609C1 - Flat nozzle of jet turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: flat nozzle of jet turbine engine includes body, subsonic doors hinged to it, supersonic doors, external doors, brackets and hydraulic cylinders connected to levers rigidly attached to subsonic doors, which are installed outside side walls of the nozzle body. Supersonic doors are hinged to subsonic doors. One end of external doors is attached to the housing and the other end is attached to supersonic doors. Brackets are arranged on longitudinal axes of side walls of nozzle body on their external side and hinged to subsonic door turning hydraulic cylinders. Each bracket is provided on its front and rear ends with rollers taken to the guides rigidly attached to the body and with two transverse eye lugs connected by means of rods to levers of subsonic doors. To each lever there hinged is additional rod that is equipped on the other end with rollers taken to the guides provided on external doors. On side walls of nozzle body there installed are additional hydraulic cylinders the stocks of which are hinged to additional rods for turning of external doors.

EFFECT: invention allows improving operating reliability and efficiency coefficient of jet turbine engine.

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Description

The invention relates to the field of aircraft engine manufacturing, in particular to the design of nozzles of turbojet engines (turbojet engines).

A flat nozzle of a turbojet engine is known, comprising a housing, on the side walls of which balanced subsonic flaps are articulated, supersonic flaps articulated with subsonic flaps, external flaps, one end of which is pivotally suspended from the side walls of the casing, and the other connected to supersonic flaps, and hydraulic rams of the dose actuator cusps connected to levers of subsonic cusps (see US patent No. 3973731 class 239.265.39, published in 1976).

The specified nozzle provides reversal and change of the thrust vector of the engine.

The disadvantage of this nozzle is the lack of synchronization of the drive of subsonic flaps and changes in the output area of the nozzle depending on the flight altitude. Since the ambient pressure decreases when climbing by aircraft, at a constant critical cross section, the nozzle exit area must be increased to reduce thrust loss due to under-expansion (the nozzle exit pressure is greater than the ambient pressure). The lack of synchronization of subsonic flaps, in which one flap can rotate at a larger angle than the other, during a change in the critical nozzle cross-sectional area, can lead to spontaneous deviation of the thrust direction and, consequently, to the deviation of the aircraft from the flight course.

The objective of the invention is to ensure synchronization of the movement of the subsonic valves of the nozzle.

This problem is solved by the fact that the known flat nozzle of the turbojet engine, comprising a housing, subsonic flaps pivotally attached to it, supersonic flaps pivotally connected to subsonic flaps, external flaps attached to the casing at one end and connected to supersonic flaps at the other, and hydraulic cylinders connected to levers rigidly attached to subsonic flaps mounted outside the side walls of the nozzle body, according to the invention is equipped with brackets placed on the longitudinal axes of the side walls of the nozzle body from their outer side, articulated to the hydraulic cylinders of rotation of the subsonic flaps, each bracket at the front and rear ends provided with rollers wound into guides rigidly attached to the body, and two transverse eyes connected by rods to the levers of the subsonic flaps, pivotally to each lever an additional rod is attached, which is provided on the other end with rollers guided in guides made on the external flaps, and additional gs are installed on the side walls of the nozzle body idro cylinders, the rods of which are pivotally connected to additional pull rods for turning the external wings.

This embodiment of the device provides synchronization of the movement of two symmetrical subsonic flaps, which increases the reliability of the nozzle and engine. In addition, it provides a change in the area of the exit section of the nozzle depending on the flight conditions (at a constant critical section of the nozzle), which reduces the thrust loss of the engine in the supersonic part of the nozzle.

Figure 1 shows the kinematic diagram of a flat nozzle on the side wall of the housing from its outer side;

figure 2 is a longitudinal section of a nozzle;

figure 3 is a fragment of a cross section of the side wall of the nozzle body.

The nozzle contains a housing 1, subsonic flaps 2, in the middle part pivotally attached to the side walls of the housing. Supersonic flaps 3 are hingedly attached to the subsonic flaps 2. The outer flaps 4 are hinged by the front end to the side walls of the housing 1, and at their rear end there are guides 5 into which the rollers 6 are inserted in the supersonic flap 3 (Fig. 2). On the outer side of the side walls of the housing 1, the hydraulic cylinders 7 of the rotation of the subsonic valves 2 are pivotally fixed to the ends of the rods of the hydraulic cylinders 7 are connected to the brackets 8, the ends of which are mounted on rollers 9, guided in guides 10, fixedly mounted on the housing 1 (Fig. 1, 3). The transverse lugs 11 of the brackets 8 are connected by rods 12 with levers 13 fixedly mounted on the axis of rotation of the subsonic valves 2. The levers 13 are pivotally connected to the rods 14, on the other end of which rollers 15 are mounted, guided in guides 16 made in the outer leaves 4. To the eyes 17, made in the middle of the rods 14, the rods of additional hydraulic cylinders 18 are pivotally connected, the liners of which are fixed on the side walls of the nozzle body 1.

The device operates as follows.

To change the critical sectional area of the nozzle or transfer it to the thrust reverse mode, hydraulic fluid 7 is supplied with hydraulic cylinders 7 and the rods move the brackets 8 with the rollers 9 along the guides 10. The eyes 11 of the brackets 8 turn the levers 13 and the subsonic shutters 2 through the rods 12 to the desired position. In this case, through the thrusts 14, the external flaps 4 and the supersonic flaps 3 are installed in the positions determined by the kinematics (positions a and b of FIG. 2, symmetrical with respect to the longitudinal axis of the nozzle).

To change the nozzle exit area when its critical cross section is established, when the flight conditions (altitude, speed, etc.) change, hydraulic fluid pressure 18 is applied to the hydraulic cylinders 18 (rod or rodless cavities), as a result of which the hydraulic cylinder rods 18 rotate the rods 14 and symmetrically open (for example, position a2, b2 of FIG. 2) or cover (position a1, b1 of FIG. 2) the outer wings 4 and, through the rollers 6, the supersonic valves 3.

To change the thrust vector, the signal gives the pressure of the working fluid in the rodless cavity of the hydraulic cylinders 18 located on one side of the longitudinal axis of the nozzle, and in the rod cavity of the hydraulic cylinders on the other side. Supersonic valves move to the position a1-b2, and vice versa, when pressure is applied to the opposite cavity of the hydraulic cylinders, the supersonic valves turn to the position a2-b1. This ensures the rotation of the thrust vector of the nozzle in a vertical plane.

The proposed design provides synchronous movements and symmetrical installation of subsonic flaps and allows you to change the nozzle exit area at a constant critical section, as well as deflect the thrust vector by rotating the supersonic valves.

The implementation of the invention allows to increase the reliability of the engine and increase its efficiency.

Claims (1)

A flat nozzle of a turbojet engine, comprising a housing, subsonic shutters articulated to it, supersonic shutters articulated to subsonic shutters, external shutters attached to the housing at one end and connected to supersonic shutters at the other, and hydraulic cylinders connected to levers rigidly attached to the subsonic flaps mounted outside the side walls of the nozzle body, characterized in that it is provided with brackets located on the longitudinal axes of the side walls of the nozzle body with their outer wall orons, pivotally connected to the hydraulic cylinders of rotation of the subsonic valves, each bracket at the front and rear ends equipped with rollers, guided rigidly attached to the body, and two transverse eyes connected by rods to the levers of the subsonic valves, with an additional link pivotally attached to each lever , which is equipped with rollers on the other end, guided in guides made on the outer flaps, and additional hydraulic cylinders are installed on the side walls of the nozzle body, pcs ki which is pivotally connected to the pivot rods additional external valves.

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