RU1747U1 - STAND FOR TESTING AIRCRAFT ENGINES - Google Patents

Abstract

TEST STAND FOR Aircraft Engines, comprising a synchronous generator connected by an elastic shaft to an asynchronous motor with a phase rotor and an asynchronous motor with a squirrel-cage rotor, which are electrically connected to each other, a DC generator electrically connected to the rectifier unit, which is connected to the rotor phase of the asynchronous motor rotor, characterized in that it contains an aircraft engine mechanically connected by a shaft with a synchronous generator, and the rotating magnetic The second field of the asynchronous motor with the phase rotor is directed opposite to the rotation of the shaft of the aircraft engine and synchronous generator.

Description

Test bench for aircraft engines.

A utility model is disclosed related to the field (electrical engineering and can be used to test aircraft engines.

A device for testing a multiply connected mechanical transmission with a branched kinematic chain and flexible links, containing two primary induction motors, two load synchronous generators, four torque sensors, six comparison elements, a program unit, the first and second output associated with the control inputs of each of the excitation systems synchronous generators. (3 SHSJ, N 02 P 5/00, AS of the USSR M 1001400, 1E81).

A disadvantage of the known device is that at various loads of the SYNCHRONOUS generator, the drive motor unloads; the complexity of the circuitry.

The closest to the proposed technical essence and the achieved 1-result is an automatic test drive for transmissions, consisting of the tested gearbox, two drive and two elastic axle shaft, containing a synchronous generator connected by elastic shaft with a load induction motor with a phase rotor, asynchronous squirrel-cage racing engine and a converter unit electrically interconnected, a rectifier unit interacting with the converter agr Gath (MKI 4, G 01 M 13/02, a, c, USSR N 1460640, 1987.).

A disadvantage of the known device is that with different loads of the synchronous generator, the drive motor is unloaded; the complexity of the circuitry.

The purpose of the claimed utility model is to ensure smooth, stable loading of aircraft engines in various operating modes and simplify the design.

This goal is achieved due to the fact that the test bench for aircraft engines containing a synchronous generator connected by an elastic shaft with an asynchronous motor with a phase rotor and an asynchronous motor with a squirrel-cage rotor, which are electrically connected to each other, a DC generator electrically connected to the rectifier unit, which is connected to the rotor circuit of an induction motor with a phase rotor, contains an aircraft engine mechanically connected by a shaft with a synchronous generator, and a rotating m The magnetic field of an induction motor with a phase rotor is directed opposite to the rotation of the shaft of the aircraft engine and synchronous generator. 6

G 01 M 15/00

2.Borisov Yu.M., Sokolov N.M.,) electrical equipment for hoisting-and-transport of HUX cars, M. 1958. p. 270-278.

3. Zhivov A.G., Drive and automation of lifting machines, ed.2. M. Engineering, 1E64G.

In known technical solutions, the drive motor is unloaded in the anti-inclusion mode,

In the proposed technical solution, the opposition mode is used to load the drive motor.

On Fig, 1 shows a General block diagram of a bench for testing aircraft engines;

in FIG. 2 - mechanical characteristics of the SYNCHRONOUS generator and asynchronous motor with a phase rotor.

The stand contains an aircraft engine 1 connected by an elastic shaft 2 with a synchronous generator 3, an excitation device 4 connected by an elastic shaft 5 with an asynchronous motor 6 with a phase rotor, an asynchronous motor 7 with a squirrel-cage rotor and a direct current generator 8 with independent excitation, Stator windings of a synchronous gene Ator 3, an asynchronous motor 6 with a phase rotor and an asynchronous motor 7 are electrically connected to each other. The squirrel-cage induction motor 7 and the direct current generator 8 are mechanically connected by an elastic shaft 9, the direct current generator 8 contains an excitation winding 10 electrically connected to a resistor 11, which allows you to adjust the excitation current of the direct current generator 8, which is counterclosed with the rectifier 12. allows you to change the current in the rotor circuit, and therefore the loading moment of the asynchronous motor 6 with a phase rotor,

The stand works as follows,

The aircraft engine 1, which is the drive of the synchronous generator 3, is started. The corresponding voltage, determined by the speed of the aircraft engine, is set on the synchronous generator 3

1, while the asynchronous motor 6 with the phase rotor 1 ohm runs at the xoji turn (point 13, FIG. 2), since the voltage on the generator of the current current 8, installed using the resistor 11, is greater than the voltage taken from rectifier device 12, There is no current in the rotor circuit of an induction motor 6 with a Phase ROTOR and its moment of static resistance is zero (point 13, FIG. 2), The magnetic field of the stator of the induction motor 6 with a phase rotor is directed to the opposite side of rotation of the shaft 5 of the synchronous generator 3 (counter mode for prison staff)

 3 (

We load the induction motor 6 with the Phase rotor by decreasing the current with the help of the resistor 11 in the excitation winding 10 of the direct current generator 8. As soon as the voltage on the direct current generator 8, connected counter to the rectifying device 12, is less than on the rectifying device 12, in the rotary circuit of the asynchronous a motor 6 with a phase rotor, a current will appear and a braking torque will occur, which will load the synchronous generator 3 (point 14, Figure 2) and the aircraft engine 1.

Thus, by changing the excitation current by the resistor 11, the voltage across the terminals of the generator 8 changes, and the value of the rotor current (torque) of the induction motor 6 with the phase rotor also changes. Thereby we obtain the various, necessary load of the synchronous generator 3 and the aircraft engine 1 (see mechanical characteristics in FIG. 2, points 14.15), which allows testing the aircraft engine 1, smoothly changing the load over a wide range. Head of the OPRIR S.V. Tsypkov

Claims (1)

TEST STAND FOR Aircraft Engines, comprising a synchronous generator connected by an elastic shaft to an asynchronous motor with a phase rotor and an asynchronous motor with a squirrel-cage rotor, which are electrically connected to each other, a DC generator electrically connected to the rectifier unit, which is connected to the rotor phase of the asynchronous motor rotor, characterized in that it contains an aircraft engine mechanically connected by a shaft with a synchronous generator, and the rotating magnetic The second field of the asynchronous motor with the phase rotor is directed opposite to the rotation of the shaft of the aircraft engine and synchronous generator.