RU2530955C1 - Method of coordinate positioning control of gas turbine - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: invention relates to coordinate positioning control of gas turbine. Gas is supplied to the turbine vanes before achieving the point of coordinate positioning meanwhile by the signal of the feedback sensor at the approach to the point of coordinate positioning the control system switches a continuous mode of gas supply to the turbine vanes to the mode of impulse gas supply with ensuring of braking of the turbine shaft during intervals between driving impulses, and at achieving of the point of coordinate positioning by the signal of the feedback sensor the turbine shaft is stopped completely.

EFFECT: ensuring of positional control of gas turbine with necessary dynamic and precision of positioning.

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Description

The claimed invention relates to the field of automation and can be used for positional control of a gas turbine.

It is known the use of air turbines to drive a working tool without positioning (see, for example, AS Natalevich. Air microturbines. M., Engineering. 1979, 192 S.).

A study is also known of controlling the PDT-100 type air microturbine in a servo drive in which gas is supplied to the turbine blades until the positioning point is reached (see A. Mikerov. Investigation of the dynamic characteristics of a low-power reversible turbine air motor as an element of a closed automatic control system. Department of funds of NIITEIR, 1975, S.3, 15, 21, 22. UDC 681.516.2 + 681.523.5) (prototype).

The disadvantage of this method of controlling a gas turbine in the work of A.G. Mikerova is a long run-up time (large time constant) of such an engine compared to engines of a different type due to the large inertia of the turbo drive, which significantly reduces the applicability of the turbine for a positional drive, as well as a decrease in the drive torque of the turbine when approaching the positioning point.

The objective and technical result of the present invention is the provision of positional control of a gas turbine to obtain the necessary dynamics and accuracy of positioning.

The technical result is achieved by the fact that gas is supplied to the turbine blades until the positioning point is reached, and upon the feedback sensor signal approaching the positioning point, the control system switches the continuous (marching) mode of gas supply to the turbine blades to the pulse gas supply mode while providing braking the turbine shaft in the intervals between the drive pulses, and when the positioning point is reached by the feedback sensor signal, the turbine shaft is completely braked.

The essence of the proposal is that the introduction of braking in the area of the turbine impulse motion between the driving pulses when approaching the positioning point causes additional dissipation of the inertia energy of the rotation of the turbine, thereby limiting the uncontrolled turbine run-off, and setting the start of the transition to a pulsed gas supply, the pulse duration gas supply, the duration and braking force between the pulsed gas supply achieve the necessary dynamics and accuracy of positioning beans; in this case, the driving moment in pulsed motion can reach the magnitude of the driving moment during marching motion.

The implementation of the proposed method is illustrated in figures 1-4.

Figure 1 shows a front view of the mechanical diagram of a gas turbine, figure 2 shows a side view of the mechanical diagram of a gas turbine, figure 3 shows a functional diagram of a positional control system of a gas turbine, figure 4 presents graphs of the action of the turbine in time.

Thus, the circuit of the device that implements the proposed method contains a gas turbine 1, turbine blades 2, reverse supply of working gas to the turbine blades 3, brake clutch 4, gas supply to the brake clutch 5, turbine output shaft 6, turbine control system 7, output turbine gearbox 8, actuator 9, feedback sensor 10.

, б) - усилие воздействия на муфту трения $$F_M^{*}$$

, в) - угловая скорость на валу турбины $${\omega }_{В}^{*}$$

.In Fig. 4, time t is plotted along the abscissa, and dimensionless parameters are plotted along the ordinates: a) the force exerted on the turbine blades $$F_T^{*}$$

, b) - force of impact on the friction clutch $$F_M^{*}$$

, c) is the angular velocity on the turbine shaft $${\omega }_{\mathrm{AT}}^{*}$$

.

и турбина находится в движении с угловой скоростью $${\omega }_{В}^{*}$$

. По сигналу от датчика обратной связи (момент t₁) дается команда перехода на импульсное движение, и на период от t₁ до t₂ подача газа на лопатки прекращается и включается торможение турбины муфтой трения с усилием $$F_M^{*}$$

, и угловая скорость $${\omega }_{В}^{*}$$

снижается. На период от t₂ до t₁ возобновляется подача газа на лопатки, торможение муфтой трения прекращается и угловая скорость повышается. На период от t₃ до t₄ процесс происходит аналогично периоду от t₁ до t₂, а на период от до t₅ процесс происходит аналогично периоду от t₂ до t₃. В момент t₅ от датчика обратной связи поступает сигнал о достижении точки позиционирования и муфта трения полностью затормаживает турбину. Выбором частоты импульсной подачи и усилием промежуточного торможения может быть установлена точность позиционирования. При этом в импульсном движении сохраняется усилие воздействия на лопатки турбины.A device that implements the proposed method works as follows. In the cruising speed mode, the fluid is continuously supplied to the blades 2 of the turbine 1 through one of the reversing channels 3 (Fig. 1) and the turbine 1 drives the actuator 9 through the reduction gear 8 (Fig. 2). When approaching the positioning point of the movement of the actuator 9 with a certain pre-emptive lead from the feedback sensor 10, the control system 7 gives a signal of transition to a pulsed (step) movement, in which a transition to the pulsed supply of fluid to the blades 2 is performed while braking the turbine shaft the brake clutch 4 in the intervals between the drive pulses, and when the positioning point is reached by the signal of the feedback sensor 10, the turbine 1 is completely braked rmoznoy clutch 4. Figure 4 shows that the time from "0" to t _1, the gas is supplied by one of the reverse channels to force $$F_T^{*}$$

and the turbine is in motion with angular velocity $${\omega }_{\mathrm{AT}}^{*}$$

. The signal from the feedback sensor (moment t ₁ ) gives a command to switch to impulse motion, and for a period from t ₁ to t _{2 the} gas supply to the blades stops and the turbine brakes with friction clutch $$F_M^{*}$$

, and angular velocity $${\omega }_{\mathrm{AT}}^{*}$$

declining. For a period from t ₂ to t ₁ , gas supply to the blades resumes, braking by the friction clutch stops and the angular velocity increases. For a period from t ₃ to t _{4, the} process occurs similarly to a period from t ₁ to t ₂ , and for a period from to t _{5 the} process occurs similarly to a period from t ₂ to t ₃ . At time t _5, a feedback signal is received from the feedback sensor that a positioning point has been reached and the friction clutch completely brakes the turbine. By selecting the frequency of the pulse feed and the intermediate braking force, positioning accuracy can be established. At the same time, in a pulsed motion, the force of action on the turbine blades is preserved.

The proposed method has the advantage compared to the known that, when approaching the positioning point, there is a transition to a pulsed supply of working gas to the turbine blades with the braking of the turbine using a brake clutch in the intervals between the supply of working gas, which reduces the turbine run-off time due to forced dissipation of the inertia of the turbine in the intervals of pulsed motion while maintaining the magnitude of the drive moment when approaching the positioning point, and setting the beginning of the transition to the impulse waistband feed gas, the duration of the impulse supply of gas, the duration and the brake force of the braking torque coupling achieve the necessary momentum and positioning accuracy of the turbine; in this case, the driving moment in pulsed motion can reach the magnitude of the driving moment during marching motion.

Claims (1)

The method of positional control of a gas turbine, in which gas is supplied to the turbine blades until the positioning point is reached, characterized in that, upon feedback from the feedback sensor when approaching the positioning point, the control system switches the continuous mode of supplying gas to the turbine blades to the pulse gas supply mode while providing braking of the turbine shaft in the intervals between the drive pulses, and when the positioning point is reached by the feedback sensor signal, the turbine shaft completely brakes Xia.

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