SU613132A1 - Transmitter of turbine machine maximum revolutions - Google Patents

Description

one

The invention relates to the field of power engineering, in particular, to sensors for limiting revolutions of an aircraft engine turbomachine.

Known sensors limit speed turbo.machines containing a sensitive element mounted in the hollow shaft of the turbine, and mounted on the body of the actuator. When the permissible rpm is exceeded, the sensing element acts on the actuator, which turns off the turbomachine

one.

However, these sensors limit speed and. Have large dimensions and weight, and therefore it is impossible to use them in aircraft units.

Also known sensors limit revolutions of the turbomachine, mainly aircraft unit, comprising a housing with an actuator and a pusher having a seal, and a sensing element. The seal is made in the form of a ring covering the cylindrical part of the pusher 2.

This sensor is the closest technical solution to the invention according to the technical essence and the achieved result.

However, such sensors due to increased friction on the pusher, which changes in

during operation, do not provide stability of operation and the possibility of checking the actuator without disassembly.

The purpose of the invention is to improve the accuracy of operation.

The goal is achieved by the fact that the casing has a flat seated surface and an additional spring is installed in it, and the pusher is provided with a head and the seal is located at its lower end in contact with a flat saddle surface, with the power end of the spring placed between the head of the pusher and the actuator.

In addition, a rotary eccentric is installed in the housing under the power end of the spring, and a lever connected to the eccentric is mounted on the outside of the housing.

Pa figs. 1 shows the proposed sensor section; on phpg. 2 shows section A-A in FIG. one; in fig. 3 shows but arrow B in FIG. 2

The sensor contains a sensing element made in the form of two centrifugal weights 1 mounted on axis 2 in roller 3 placed on two bearings 4 and 5. Roller 3 nrn of bevel gear 6 is kinematically connected to the shaft of a turbomachine (not shown) aircraft

Claims (2)

unit. The weights of weights 1 rest on the end of the stem 7 loaded with a spring 8. Bearings 4 and 5 are mounted in a sleeve 9 connected to the housing 10, in which the actuator is mounted on the bracket 11 in the form of a microswitch 12. Between the 5 rod 7 and the microswitch 12 a pusher 13 is installed, equipped with a mushroom-shaped head 14, on the lower end of which an annular seal 15 is fixed, which contacts the flat saddle top 16, made on the housing 10. The housing 10 has a spring plate 17, the power end of which is The echelon between the head 14 of the pusher 13 and the button 18 of the microswitch 12. The terminals of the microswitch 12 are connected by wires 19 and 20 to the plug 15 by the mating connector 21. In the case 10 under the power end of the spring 17 there is a rotary eccentric 22 connected to the lever 10 placed outside the case 23 (see FIG. 3), fixed by the spring 24 on the stop 25. The sensor works as follows. When the turbomachine operates in the operating speed range, the weights 1 are closed and the rod 7 does not touch the pusher 13, which, under the action of the spring 17, is in the lowermost nozheepin, so that the seal 15 is tightly pressed to the saddle surface 16, resulting in the cavity of the housing 10 where the microswitch 12 is located, is sealed from the 30th oil cavity of the turbomachine, in which the weights 1 grow. When the turbomachine rises above the allowable weights 1, it consumes the rod 7, which, overcoming 35 resistance of the spring 8, mixes up. At the same time, after sampling the gap, the rod 7 moves the pusher 13, which, with its head 14 through the spring 17, acts on the button 18 of the microswitch 12 to its 40 trigger. As a result, using the emergency system (not shown in the drawings), the supply of the working fluid to the turbomachine is stopped, turning it off from work. Since the seal 15 is installed on the lower 45 end of the head 14, when the upward movement of the pusher 13 is low, the friction is small, as a result of which the sensor is triggered at the set limit revolutions. At the same time, the frictional force during operation of the turbomachine 50 practically does not change. The spring plate 17, pressing the seal 15 to the seat surface 16, increases the reliability of sealing the cavity of the housing 10. To check the operability of the emergency system when the turbo-bearing is not working, the lever 23 is manually shifted to the extreme left position until it stops 26. The eccentric 22 raises the power end of the leaf spring 17, which mixes the microswitch button 18 until it is triggered. Thus, such an implementation of the turbomachine speed limit sensor, due to the stability of the friction on the pusher, increases its operation, and the presence of a constant compression of the seal to the saddle surface ensures a case of tightness of the cavity where the microswitch is located. Claims 1. A turbomachine speed limit sensor, preferably an aircraft unit, comprising a housing with an actuating mechanism and a pusher having a seal, and a sensing element, characterized in that, in order to improve the response accuracy, a flat seat surface and It is additionally installed with a plate nruzhppa, and the pusher is provided with a head and the seal is located at its lower end in contact with a flat saddle surface, the power end ruzyne placed between the head of the pusher and the actuator. 2. The sensor according to claim 1, characterized in that in the case under the power end of the probe there is a rotary eccentric installed, and outside the housing there is a lever connected to the eccentric. Sources of information, taken into account by the expertise of Kirillov I. I., Automatic regulation of steam and gas turbines, M., “Maschgiz, 1961, p. 106-109, FIG. 79, 81. 2. Instructions for operation of the NK-8-4 turbofan engine. Part I., M., “Mashgiz, 1971, p. 75 (PUZ.2