RU2403548C1 - Method to control gas turbine plant state - Google Patents

Method to control gas turbine plant state Download PDF

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RU2403548C1
RU2403548C1 RU2009112237/06A RU2009112237A RU2403548C1 RU 2403548 C1 RU2403548 C1 RU 2403548C1 RU 2009112237/06 A RU2009112237/06 A RU 2009112237/06A RU 2009112237 A RU2009112237 A RU 2009112237A RU 2403548 C1 RU2403548 C1 RU 2403548C1
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gas turbine
turbine
gtp
gas
output shaft
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RU2009112237/06A
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RU2009112237A (en
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Валерий Владимирович Бурдин (RU)
Валерий Владимирович Бурдин
Виктор Александрович Гладких (RU)
Виктор Александрович Гладких
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Закрытое Акционерное Общество Научно-Производственная Фирма Запо Нпф "Газ-Система-Сервис"
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Abstract

FIELD: engines and pumps.
SUBSTANCE: proposed invention can be used in electronic ACS of gas turbine plant (GTP), gas compressor plant (GCP) and gas turbine power stations (GTPS). In GTP acceptance tests at test bench, dependence of gas temperature behind the turbine on its output shaft power is determined at various temperatures of air at turbine inlet. Obtained values are entered in GTP record. In operation of GTP, air temperature at GTP compressor inlet, as well as gas temperature behind the turbine, output shaft rpm and torque are measured in and for preset time intervals. Output shaft power is calculated as the product of measured rpm and torque. Design power is compared with the first preset value determined by experimental procedure and corrected in operation. In case design power exceeds the first preset value and there is no air bleed due to GTP compressor, averaged GTP compressor inlet air, gas temperature behind GTP compressor and design output shaft power are calculated by the second preset dependence using the data entered in GTP record. Recorded gas temperature behind GTP turbine is calculated to be compared with the averaged value. Obtained difference is compared with the second and third preset values of each GTP type. In case the difference exceeds the second preset value but is smaller than third value, signal "Fouled engine flow section" is generated for operator. In the latter case, at the first opportunity, flush the GTP flow section. In case said difference exceeds the third preset value, signal "Maximum tolerable fouling of engine flow section" is generated for GTP operator. GTP operation is inadmissible. Flush GTP flow section. For this, cut off GTP and flush its flow section.
EFFECT: higher quality control over GTP state and GTP reliability.
1 dwg

Description

The invention relates to the field of gas turbine engine building and can be used in electronic systems (ACS) for automatic control of gas turbine units (GTU) of gas pumping units (GPU) and gas turbine power plants (GTES).
A known method of monitoring gas turbines with hydromechanical self-propelled guns, I. Keba. “Flight operation of helicopter gas turbine engines”, M., “Transport”, 1976, which consists in the fact that, during the engine start-up, the flight mechanic, according to the instrument in the helicopter cockpit, controls the gas temperature behind the turbine and, if the temperature rises above a predetermined limit, turns off engine.
The disadvantage of this method is its low efficiency.
Closest to this invention in technical essence is a method for monitoring the technical condition of gas turbines, implemented in a hydromechanical self-propelled guns with an electronic gas temperature limiter behind the turbine. Keba I.V. “Flight operation of helicopter gas turbine engines”, M., “Transport”, 1976, which consists in measuring the temperature of the gases behind the turbine turbine, comparing its value with the maximum permissible value, if the measured gas temperature exceeds the limit value by a predetermined value, stop fuel supply to the combustion chamber (CS) and perform emergency shutdown of the gas turbine.
The disadvantage of this method is that it does not allow to identify the cause of abnormal behavior of gas turbines, leading to an overflow of gas temperatures. The development of a defect that was not detected in time can lead, ultimately, to damage and premature removal of gas turbines.
Thus, the lack of automatic control of the engine condition reduces the reliability of the gas turbine.
The aim of the invention is to improve the quality of control of the technical condition of gas turbines and, as a result, increase the reliability of gas turbines, gas turbines and gas turbines.
This goal is achieved by the fact that in the method of monitoring the technical condition of the gas turbine, which consists in measuring the temperature of the gases behind the turbine of the gas turbine, compare its value with the maximum permissible value, if the measured gas temperature exceeds the limit value by a predetermined value, the fuel supply to the combustion chamber is stopped (CS) and perform emergency shutdown of the gas turbine, in addition, in the process of acceptance testing of gas turbines at the engine stand, the dependence of the temperature of the gases behind the turbine of the gas turbine on the power on the output shaft of the gas turbine is determined different air temperatures at the inlet to the gas turbine compressor, enter the received data into the gas turbine form, during operation of the gas turbine measure the temperature at the gas inlet to the gas turbine compressor, the temperature of the gases behind the gas turbine turbine, the speed of the output shaft GTU and torque on the output shaft of the GTU, calculate the power on the output shaft of the GTU as a product of the measured speed and torque, compare the calculated power with the first set If the calculated power is greater than the first forward set value and there are no air withdrawals due to the GTU compressor, the averaged value of the air temperature at the inlet of the GTU compressor, temperature of gases behind the turbine turbine unit and the rated power on the output shaft of the gas turbine unit, according to the second predetermined dependence, using the data from the form of the gas turbine unit, calculate the formulary temperature gas tours behind the gas turbine turbine, compare it with the averaged one, the difference obtained is compared with the second and third forward set values, determined for each type of gas turbine by calculation and experimental methods, if the difference is greater than the second predetermined value, but less than the third, they form a signal to the gas turbine operator "Pollution flow part of the engine. At the earliest opportunity, it is necessary to flush the flow section of the gas turbine "if the difference is greater than the third pre-set value, a signal to the operator of the gas turbine" Maximum pollution of the engine flow section is generated. The work of the gas turbine is unacceptable. It is necessary to flush the flow section of the gas turbine ”, turn off the gas turbine and flush the flow section of the gas turbine.
The drawing shows a diagram of a device that implements the inventive method.
The device contains a series-connected sensor unit 1 (DB), an electronic control unit 2 GTU (ECU), block 3 actuators (MI), dispenser 4, stop valve 5 (KO), limit switch 6 (KB), and dispenser 4 and KB 6 are connected to DB 1, and KO 5 to block 3, block 7 of executive valves (BIC) connected to DB 1 and block 3, operator panel 8 (PU) and starter control block 9, connected to ECU 2.
The device operates as follows.
The operator controlling the gas turbine, using the control unit 8, sets the operation mode of the gas turbine: start-up.
The operator’s command from the control unit 8 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 8 according to the signals of the sensors from the database 1 according to known dependencies (see, for example, Shevyakov A book .A. "Power plants of rocket engines and power plants. Control systems of power plants", Moscow, "Mashinostroenie", 1985), forms a control action on the unit 3 IM, which through the dispenser 4 controls the fuel consumption in the compressor station of the gas turbine through BIK 7 - the position of the mechanization of the gas turbine and through 9 - starter, ensuring that the firing timeline GTU. Information on the parameters of the gas turbine, the starter speed, the position of the dispenser 4, the mechanization of the compressor (through BIK 7) and the state of KO 5 (through KB 6) is formed in DB 1.
Information about the parameters of the gas turbine and the starter, received by the ECU 2 from the OBD 1, is transmitted through the digital communication channel to the control unit 8.
PU 8 is a PC in industrial design, on the hard magnetic disk (HDD) which recorded special software (SPO) - not shown in the drawing.
Monitoring the technical condition of gas turbines is carried out in control room 8 as follows.
In the process of operation of a gas turbine with the help of a DB 1, the temperature of the gases is measured behind the turbine of a gas turbine and in the air conditioner control unit 2 it is compared with a predetermined value determined for each type of gas turbine by the calculation and experimental method (for the D049 engine, which is part of the gas turbine gas turbine power plant-2.5 produced "Saturn-Gas Turbines", Rybinsk, this value is 510 ° C).
If the measured gas temperature has exceeded the limit value by a predetermined time (for the D049 engine this time is 1 s), the ECU 2 generates and transmits to the control unit 8 the signal “Overheating of the engine” and, with the help of unit 3 and CO 5, stops the fuel supply to the compressor station and turns off GTU on the cycle "Emergency Stop".
Additionally, in the process of acceptance tests of the gas turbine at the engine stand, the dependence of the temperature of the gases behind the turbine of the gas turbine on the power on the output shaft of the gas turbine at different temperatures at the inlet to the gas turbine compressor is determined
Figure 00000001
Where
Tg is the measured temperature of the gases behind the turbine GTU, K;
Nism. - measured power on the output shaft of the gas turbine, MW;
Twh. - measured air temperature at the inlet to the gas turbine.
The value of Tg and Tvh. measured using DB 1.
The value of Niz. measured using a special bench-top power measurement system (descriptions of such systems are given in the books of T. Basht and others. "Hydraulics, hydraulic machines and hydraulic drives", M., "Engineering", 1982 or Moth R. "Hydropneumoautomatics", M ., "Engineering", 1975).
For the D049 engine, for example, the dependence of the temperature of the gases behind the gas turbine turbine on the power on the gas turbine output shaft is determined at four different air temperatures at the inlet to the gas turbine compressor:
Figure 00000002
Where
Tg is the measured temperature of the gases behind the turbine turbine, ° C;
Nism. - measured power on the output shaft of the gas turbine, MW.
The dependence is removed at TVh. = - 45 ° C.
Figure 00000003
Where
Tg is the measured temperature of the gases behind the turbine turbine, ° C;
Nism. - measured power on the output shaft of the gas turbine, MW.
The dependence is removed at TVh. = - 10 ° C.
Figure 00000004
Where
Tg is the measured temperature of the gases behind the turbine turbine, ° C;
Nism. - measured power on the output shaft of the gas turbine, MW.
The dependence is removed at Tv. = 15 ° C.
Figure 00000005
Where
Tg is the measured temperature of the gases behind the turbine turbine, ° C;
Nism. - measured power on the output shaft of the gas turbine, MW.
The dependence is removed at Tv. = 40 ° C.
The data obtained are entered in the regular (paper) and electronic (stored in the memory of the PU 8) GTU forms.
During operation, during operation of a gas turbine, with the help of a DB 1, the air temperature at the inlet to the gas turbine compressor, the temperature of the gases behind the gas turbine turbine, the speed of the gas turbine output shaft and the torque on the gas turbine output shaft are measured at predetermined time intervals during a predetermined period of time.
For the aforementioned D049 and GTU-2.5 engine, these measurements are made every two hours of continuous operation of the GTU for 600 seconds.
Simultaneously with measurements in the control unit 8 (all information about the measured parameters is supplied to the control unit 8 through the ECU 2), the power on the output shaft of the gas turbine is calculated as the product of the measured rotation speed and torque
Figure 00000006
Where
Calc. - rated power on the output shaft of gas turbines, MW;
MKR - torque measured on the output shaft of the gas turbine, N × m;
n st - measured speed of the output shaft of the gas turbine, 1 / s
Next, in PU 8, the calculated power is compared with the first predetermined value of A, determined by the calculation-experimental way and refined during the operation of the gas turbine.
For the engine D049 and GTU-2.5, this value is equal to
Figure 00000007
Where
And - the first predetermined value, MW.
If the calculated power is greater than the first predetermined value and there are no air withdrawals due to the gas turbine compressor (there is no signal about the inclusion of sampling from the ECU 2 in the control unit 8), the average value of the air temperature at the inlet to the gas turbine compressor is calculated from the first forward set dependence; the temperature of the gases behind the turbine of the gas turbine and the rated power on the output shaft of the gas turbine. Examples of averaging are given in the books of Kovalenko I.N., Filippova A.A. “Probability Theory and Mathematical Statistics”, M., Higher School, 1982, or Luke Yu., “Special Mathematical Functions and Their Approximations”, M., Mir Publishing House, 1980.
Next, in the control unit 8, according to the second predetermined dependence, using the data from the GTU electronic form obtained by formulas (2) - (5), the formular value of the gas temperature behind the GTU turbine is calculated.
For the D049 and GTU-2.5 engine, depending on the air temperature at the inlet of the gas turbine and the rated power on the output shaft of the gas turbine, obtained by the formula (6), this is done as follows.
If Tw.≥15 ° С, then
Figure 00000008
Where
Twh. - measured air temperature at the inlet to the gas turbine, ° C.
Tg forms. - formulated gas temperature behind the turbine turbine, ° C;
Tg (15) is the temperature of the gases behind the gas turbine turbine, obtained according to dependence (4) stored in the electronic gas turbine form in the control unit 8, taking into account the estimated power on the output shaft of the gas turbine, ° С;
Tg (40) is the temperature of the gases behind the gas turbine turbine, obtained according to dependence (5) stored in the electronic gas turbine form in the control unit 8, taking into account the value of the calculated power on the output shaft of the gas turbine, ° С;
Twh. Wed - averaged air temperature at the entrance to the gas turbine, ° C.
If - 10 ° С≤Твх.≤15 ° С, then
Figure 00000009
Where
Twh. - measured air temperature at the inlet to the gas turbine, ° C.
Tg forms. - formulated gas temperature behind the turbine turbine, ° C;
Tg (15) is the temperature of the gases behind the gas turbine turbine, obtained according to dependence (4) stored in the electronic gas turbine form in the control unit 8, taking into account the estimated power on the output shaft of the gas turbine, ° С;
Tg (-10) - gas temperature behind the turbine turbine, obtained according to dependence (3) stored in the electronic form of the gas turbine in the control room 8, taking into account the estimated power on the output shaft of the gas turbine, ° С;
Tweet - averaged air temperature at the entrance to the gas turbine, ° C.
If Tvh. <- 10 ° С, then
Figure 00000010
Where
Twh. - measured air temperature at the inlet to the gas turbine, ° C.
Tg forms. - formulated gas temperature behind the turbine turbine, ° C;
Tg (-45) is the temperature of the gases behind the turbine turbine, obtained according to dependence (2) stored in the electronic form of the gas turbine in the control room 8, taking into account the estimated power on the output shaft of the gas turbine, ° С;
Tg (-10) - gas temperature behind the turbine turbine, obtained according to dependence (3) stored in the electronic form of the gas turbine in the control room 8, taking into account the estimated power on the output shaft of the gas turbine, ° С;
Tweet - averaged air temperature at the entrance to the gas turbine, ° C.
Next, the obtained formular value of the gas temperature behind the turbine is compared with the averaged:
Figure 00000011
Where
ΔTg - difference between the formulated and averaged gas temperatures, ° С;
Tg form.- formulated gas temperature behind the turbine turbine, ° C;
Tg Wed - the average temperature of the gases behind the turbine GTU, ° C.
The resulting difference in PU 8 is compared with the second (B) and third (C) predetermined values determined for each type of gas turbine by calculation and experimental means.
For the engine D049 and GTU-2.5
Figure 00000012
Where
In - the second predetermined value, ° C;
Figure 00000013
Where
C - the third predetermined value, ° C.
If the difference is greater than the second forward set value, but less than the third
Figure 00000014
then in the control unit 8 they form a signal to the operator of the gas turbine unit “Pollution of the engine flow section. At the earliest opportunity, it is necessary to flush the flowing part of the gas turbine unit ”, which is displayed on the PU 8 monitor screen.
If the difference is greater than the third predetermined value
Figure 00000015
then in PU 8 they form a signal to the operator of the gas turbine unit “Maximum pollution of the engine’s flowing part. The work of the gas turbine is unacceptable. It is necessary to flush the flow part of the gas turbine unit ”, which is displayed on the monitor screen of the console. At the same time, a control signal is generated from the control unit 8 in the ECU 2, according to which the ECU 2, with the help of unit 3 and CO 5, stops the fuel supply to the compressor station and turns off the gas turbine unit.
After that, the washing of the flow part of the gas turbine is carried out.
Thus, by increasing the volume of automatic control of the engine condition (introducing pollution control of the gas generator flow path), the quality of monitoring the technical condition of gas turbines and, as a result, improving the reliability of gas turbines, gas turbines and gas turbines is improved.

Claims (1)

  1. A method of monitoring the technical state of a gas turbine, which consists in measuring the temperature of the gases behind the turbine of a gas turbine, comparing its value with the maximum permissible value, if the measured gas temperature exceeds the limit value by a predetermined value, the fuel supply to the combustion chamber (CS) is stopped and an emergency stop is performed GTU, characterized in that, in addition, during the final tests of the GTU on the engine stand, the dependence of the temperature of the gases behind the turbine of the GTU on the power on the output shaft of the GTU at different temperatures x the air at the inlet to the gas turbine compressor, enter the received data into the gas turbine form, during operation of the gas turbine measure the air temperature at the gas inlet to the gas turbine compressor, the gas temperature behind the gas turbine turbine, the speed of the gas turbine output shaft and the torque on the output shaft of the gas turbine, calculate the power on the output shaft of the gas turbine as a product of the measured speed and torque, compare the calculated power with the first predetermined value, determined If the calculated power is greater than the first forward set value and there are no air withdrawals due to the gas turbine compressor, the average value of the air temperature at the inlet of the gas turbine compressor and the temperature of the gases behind the turbine are calculated from the first predetermined dependence GTU and rated power on the output shaft of GTU, according to the second predetermined dependence, using the data from the GTU form, calculate the formular value of the gas temperature for turbines gas turbine engine, compare it with the averaged one, the difference obtained is compared with the second and third predetermined values, determined for each type of gas turbine by calculation and experimental means, if the difference is greater than the second predetermined value, but less than the third, they form a signal to the gas turbine operator about contamination of the engine flow and if necessary, at the first opportunity, it is necessary to flush the gas-turbine flow section, if the difference is greater than the third predetermined value, they form a signal to the gas-turbine operator about the maximum pollution ary part of the engine, wherein the gas turbine operation is not permitted, and switch off the GTU carried flushing flow part GTP.
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2536759C1 (en) * 2013-12-04 2014-12-27 Открытое акционерное общество "Севернефтегазпром" Technical diagnosis method for gas turbine plant
RU2656083C1 (en) * 2017-06-21 2018-05-30 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Method of operation of gas turbine engine
RU2662258C1 (en) * 2017-06-21 2018-07-25 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Gas-turbine engine testing method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
КЕБА И.В. Летная эксплуатация вертолетных ГТД. - М.: Транспорт, 1976. *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2536759C1 (en) * 2013-12-04 2014-12-27 Открытое акционерное общество "Севернефтегазпром" Technical diagnosis method for gas turbine plant
RU2656083C1 (en) * 2017-06-21 2018-05-30 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Method of operation of gas turbine engine
RU2662258C1 (en) * 2017-06-21 2018-07-25 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Gas-turbine engine testing method
RU2662258C9 (en) * 2017-06-21 2018-09-17 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Gas-turbine engine testing method

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