RU2431753C1 - Gas turbine plant control method - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention can be used in electronic hydro mechanical automatic control systems (ACS) of gas turbine plants (GTP) of various purpose. In addition, there measured is rotation frequency of high pressure rotor; depending on air temperature at GTP inlet there formed is minimum allowable values of high pressure rotor rotation frequency. If the measured high pressure rotor rotation frequency becomes smaller than minimum allowable value, there formed is "Extreme low rotation frequency of high pressure rotor" signal to GTP operator, and reduction of fuel flow rate to GTP combustion chamber is stopped. Rotation frequency of low pressure rotor is measured, compared to maximum allowable value determined with calculation-experimental method. If the measured rotation frequency of low pressure rotor becomes more than maximum allowable value, there shaped is "Maximum high rotation frequency of low pressure rotor" signal to GTP operator and fuel flow rate to GTP combustion chamber is decreased until rotation frequency of low pressure rotor becomes lower than maximum allowable value. Air pressure is measured after high pressure compressor, compared to maximum allowable value determined with calculation-experimental method. If the measured air pressure after high pressure compressor becomes bigger than maximum allowable value, there shaped is "Maximum high pressure after high pressure compressor" signal to GTP operator and fuel flow rate to GTP combustion chamber is decreased until air pressure after high pressure compressor becomes lower than maximum allowable value.

EFFECT: improving operation quality of ACS and reliability and operation safety of GTP.

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Description

The invention relates to the field of gas turbine engine building and can be used in electronic hydromechanical systems (ACS) for automatic control of gas turbine units (GTU) for various purposes.

A known method of controlling a gas turbine implemented in an electronic hydromechanical self-propelled guns of a supervisory type, B. Cherkasov "Automation and regulation of the WFD." - M.: Mechanical Engineering, 1974, p.299-296.

The method consists in the fact that in order to improve control accuracy, the control action of the hydromechanical controller is adjusted in a limited range by an electronic corrector.

The disadvantage of this method is its low efficiency.

Closest to this invention in technical essence is a gas turbine control method, which consists in measuring the speed of a power turbine, comparing the set and measured values of the speed of the power turbine, depending on the mismatch between the set and measured values of the speed of the power turbine, controlling fuel consumption to the gas turbine combustion chamber -6 / 8RM "8T1.000.014 TK., JSC" NPO "Saturn", Rybinsk, 2001, s.28-54.

The disadvantage of this method is the following.

If the self-propelled guns fail, unrecorded by the built-in control, an uncontrolled change in fuel consumption in the gas turbine compressor station is possible, which can lead to exceeding the gas turbine limit parameters or the gas generator to go to an off-design mode of operation. For a gas turbine of a complex design (for example, GTE-25PER manufactured by Aviadvigatel OJSC, Perm) with several rotors (GTE-25PER has three rotors: a low pressure cascade rotor, a high pressure cascade rotor and a power turbine rotor) and several cases ( each cascade has its own) the consequence of this may be a malfunction of the gas turbine engine elements (for example, rotor blades and disks of compressors and turbines due to their overheating or jamming due to the abnormal cooling mode of the casing), which can damage both the gas turbine and the device driven by GTU (electric generator, gas pumping unit).

This reduces the reliability and safety of the gas turbine.

The aim of the invention is to improve the quality of ACS in order to improve the reliability and safety of gas turbines.

This goal is achieved by the fact that in the control method of the gas turbine, which consists in measuring the speed of a power turbine, compare the set and measured values of the speed of the power turbine, depending on the mismatch between the set and measured values of the speed of the power turbine, control the fuel consumption in the compressor station GTU additionally measure the frequency of rotation of the high-pressure rotor, depending on the temperature of the air at the inlet of the GTU form the minimum allowable value of the rotor speed high pressure, if the measured rotational speed of the high-pressure rotor has become less than the minimum allowable value, a signal to the GTU operator “Extremely low rotational speed of the high-pressure rotor” is generated and the fuel consumption is stopped in the compressor station of the gas turbine, the rotational speed of the low-pressure rotor is measured, compared with the maximum permissible value determined by calculation and experimental means, if the measured rotational speed of the low-pressure rotor has become greater than the maximum allowable value, an operator signal is generated at GTU “Extremely high rotor speed of a low pressure rotor” and reduce fuel consumption in a gas turbine compressor station until the rotational speed of a low pressure rotor is less than the maximum permissible value, measure the air pressure behind the high pressure compressor, compare it with the maximum permissible value, determined by calculation and experimental means, if the measured air pressure behind the high-pressure compressor has become more than the maximum permissible value, a signal to the GTU operator “Extremely high pressure downstream of the high-pressure compressor ”and reduce the fuel consumption in the compressor station of the gas turbine until the air pressure behind the high-pressure compressor drops below the maximum permissible value.

The drawing shows a diagram of a device that implements the inventive method.

The device contains series-connected sensor unit 1 (DB), engine control unit 2 (ECU), dosing unit control unit 3, dosing unit 4 (DG), check valve 5 (SCR), and DG 4 is connected to DB 1, and SLE 5 - to the ECU 2, the ECU 2 is connected to the gas turbine control panel 6.

The device operates as follows.

The operator controlling the gas turbine with the help of the control unit 6 sets the gas turbine operating mode: start, idle, nominal mode, maximum mode, overload mode.

The operator’s command from the control unit 6 via a digital communication channel (for example, RS 485 or Ethernet) is transmitted to the control unit 2. The control unit 2 in accordance with the command received from the control unit 6 according to the signals of the sensors from the database 1 according to known dependencies (see, for example, the book by Keb And .V. “Flight Operation of Helicopter GTEs”, Moscow: Transport, 1976, pp. 117-135) calculates the required fuel consumption in the gas turbine compressor station and, with the help of unit 3 and diesel engine 4, maintains the gas turbine engine operating mode by changing the fuel consumption in the gas compressor station GTU.

In particular, in the ECU 2, using the OBD 1, the speed of the power turbine is measured, the set and measured values of the speed of the power turbine are compared, depending on the mismatch between the set and measured values of the speed of the power turbine, the fuel consumption in the compressor station of the gas turbine is controlled.

During operation of the gas turbine SLE 5 is in the “Open” position.

Additionally, at all modes of operation of the gas turbine from idle to maximum, the gas turbine is protected by the limiting parameters as follows.

In the ECU 2, using the OBD 1, the rotational speed of the high-pressure rotor is measured; depending on the air temperature at the inlet of the gas turbine, the minimum permissible rotational speed of the high-pressure rotor is formed. For GTE-25PER, for example, this is done as follows:

where C _Twx ⁿ = f (T * _in ).

The dependence C _Twx ⁿ = f (T * _I ) is presented in table 1

Table 1 T * _in , K ≤213 233 253 267 273 288 298 308 ≥318 C _tvh ⁿ 0.8833 0.9142 0.9457 0.9671 0.9770 1,0 1.015 1,030 1,044

If the measured rotational speed of the high-pressure rotor has become less than the minimum permissible value, in the ECU 2 a signal is generated and transmitted to the control unit 6 to the GTU operator “Extremely low rotational speed of the high-pressure rotor” and, with the help of unit 3 and DG 4, the fuel consumption reduction in the compressor unit of the gas turbine is stopped.

In the ECU 2, using the OBD 1, the rotational speed of the low pressure rotor is measured, it is compared with the maximum permissible value determined by the calculation and experimental method (for GTE-25PER this value is 4275 rpm.). If the measured rotational speed of the low-pressure rotor has become greater than the maximum permissible value, in the ECU 2 a signal is generated and transmitted to the control unit 6 to the operator of the gas turbine unit "Extremely high rotational speed of the low-pressure rotor" and with the help of unit 3 and ДГ 4 reduce the fuel consumption in the compressor station of the gas turbine to until the rotational speed of the low-pressure rotor is less than the maximum permissible value.

In the ECU 2, with the aid of OBD 1, the air pressure is measured behind the high-pressure compressor, it is compared with the maximum permissible value determined by the calculation and experimental method (for GTE-25PER this value is 35.5 kg / cm ² ). If the measured air pressure behind the high-pressure compressor has become more than the maximum permissible value, in the ECU 2 a signal is generated and transmitted to the control room 6 to the operator of the gas turbine unit "Extremely high pressure behind the high-pressure compressor" and with the help of unit 3 and diesel engine 4 reduce the fuel consumption in the gas turbine compressor station to until the air pressure behind the high-pressure compressor is less than the maximum permissible value.

Thus, by improving the quality of work of self-propelled guns, gas turbine engines are protected by limiting parameters, which helps to prevent the gas generator from reaching off-design operating modes and, as a result, provides increased reliability and safety of gas turbine engine operation.

Claims (1)

The method of controlling a gas turbine, which consists in measuring the speed of a power turbine, comparing the set and measured values of the frequency of rotation of the power turbine, depending on the mismatch between the set and measured values of the frequency of rotation of the power turbine, control the fuel consumption in the compressor station of the gas turbine, characterized in that measure the rotational speed of the high-pressure rotor, depending on the air temperature at the inlet of the gas turbine, form the minimum allowable value of the rotational speed of the high-pressure rotor, if the measured rotational speed of the high-pressure rotor has become less than the minimum permissible value, they generate a signal to the operator of the gas turbine "Extremely low rotational speed of the high-pressure rotor" and stop the decrease in fuel consumption in the compressor station of the gas-turbine, measure the rotational speed of the low-pressure rotor, compare it with the maximum permissible value determined by calculation -experimentally, if the measured rotational speed of the low-pressure rotor has become greater than the maximum permissible value, they form a signal to the operator of the gas turbine high rotational speed of the low-pressure rotor ”and reduce fuel consumption in the gas turbine compressor station until the rotational speed of the low-pressure rotor is less than the maximum permissible value, measure the air pressure behind the high-pressure compressor, compare it with the maximum permissible value determined by the experimental by, if the measured air pressure behind the high-pressure compressor has become more than the maximum allowable value, a signal to the operator of the gas turbine "Extremely high pressure behind the compressor high pressure ”and reduce fuel consumption in the gas turbine compressor station until the air pressure behind the high-pressure compressor becomes less than the maximum permissible value.

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