CN118030207A - State monitoring method and system of gas turbine - Google Patents

State monitoring method and system of gas turbine Download PDF

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Publication number
CN118030207A
CN118030207A CN202410030465.5A CN202410030465A CN118030207A CN 118030207 A CN118030207 A CN 118030207A CN 202410030465 A CN202410030465 A CN 202410030465A CN 118030207 A CN118030207 A CN 118030207A
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gas
turbine
model
gas turbine
power
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李华
田灿
于子峰
李志勇
李秋娟
张丽稳
刘峻峰
肖旺
李春禹
刘海涛
古自强
邵强
刘少山
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National Petroleum And Natural Gas Pipeline Network Group Co ltd Science And Technology Research Institute Branch
China Oil and Gas Pipeline Network Corp
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National Petroleum And Natural Gas Pipeline Network Group Co ltd Science And Technology Research Institute Branch
China Oil and Gas Pipeline Network Corp
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Priority to CN202410030465.5A priority Critical patent/CN118030207A/en
Publication of CN118030207A publication Critical patent/CN118030207A/en
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
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  • Fluid Mechanics (AREA)
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  • Pure & Applied Mathematics (AREA)
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  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

The application relates to a state monitoring method and a state monitoring system of a gas turbine, wherein the method comprises the following steps: acquiring initial and stable operation parameters of the gas turbine, and determining an actually measured stable value of a gas circuit when the gas turbine stably operates according to the initial and stable operation parameters; determining performance index parameters of each preset part according to characteristic curves of different preset parts on the gas turbine; according to the performance index parameters corresponding to each preset part, constructing a gas circuit performance simulation model of the gas turbine; and determining the performance trend of the gas path according to the simulation result of the gas path performance simulation model, and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value. The application can monitor the state of the gas turbine without manual participation in the whole process and operate the gas circuit performance simulation model, thereby saving the labor cost, and the accuracy of acquiring the simulation result through the gas circuit performance simulation model is high and the maintenance efficiency is higher.

Description

State monitoring method and system of gas turbine
Technical Field
The invention relates to the technical field of gas turbines, in particular to a state monitoring method and system of a gas turbine.
Background
The gas turbine is an advanced power device featuring small volume, high power, compact structure and the like, and is widely used in various energy sources and aviation industry. Although providing good performance, it is subject to harsh environments such as high temperatures, high pressures, high rotational speeds, etc., which can make the gas path of a gas turbine susceptible to failure, thereby affecting its normal use and potentially causing serious safety hazards. The reliability and the safety of the gas turbine depend on the gas path system in the gas turbine, and the performance of the gas path system is directly related to the reliability and the stability of the whole gas turbine system, so that the research on the gas path performance of the gas turbine is very necessary, and the gas turbine can be effectively prevented from being deteriorated in fault through timely monitoring and diagnosis, and the optimal operation performance of the gas turbine is ensured.
However, the gas path performance of the existing gas turbine is generally achieved through manual inspection and test, the workload is large, and the maintenance efficiency and accuracy are low.
Disclosure of Invention
The invention provides a state monitoring method and system of a gas turbine, which aims to solve the problems that the gas path performance of the existing gas turbine is high in workload and low in maintenance efficiency and accuracy in a manual inspection and test mode.
In order to solve the above technical problems, the present invention provides a method for monitoring a state of a gas turbine, including:
Acquiring initial and stable operation parameters of the gas turbine, and determining an actually measured stable value of a gas circuit when the gas turbine stably operates according to the initial and stable operation parameters;
Determining performance index parameters of each preset part according to characteristic curves of different preset parts on the gas turbine;
According to the performance index parameters corresponding to each preset part, constructing a gas circuit performance simulation model of the gas turbine;
And determining the performance trend of the gas path according to the simulation result of the gas path performance simulation model, and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value.
In a second aspect, the present invention provides a condition monitoring system for a gas turbine, comprising:
The actual measurement stable value determining module is used for acquiring initial and stable operation parameters of the gas turbine and determining actual measurement stable values of the gas circuit when the gas turbine stably operates according to the initial and stable operation parameters;
The performance index parameter determining module is used for determining the performance index parameter of each preset part according to the characteristic curves of different preset parts on the gas turbine;
the gas path performance simulation model construction module is used for constructing a gas path performance simulation model of the gas turbine according to the performance index parameters corresponding to each preset part;
the monitoring module is used for determining the performance trend of the gas circuit according to the simulation result of the gas circuit performance simulation model and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value.
In a third aspect, the present invention also provides a computing device comprising a memory, a processor and a program stored on the memory and running on the processor, the processor implementing the steps of a method for monitoring the condition of a gas turbine as described above when the program is executed by the processor.
The beneficial effects of the application are as follows: the performance index parameters of different preset parts are used for constructing a gas path performance simulation model of the gas turbine, namely, the performance trend of the gas path of the gas turbine can be obtained through a simulation experiment of the gas path performance simulation model, and the performance trend is compared with an actually measured stable value to monitor the running state of the gas turbine. The application can monitor the state of the gas turbine without manual participation in the whole process and operate the gas circuit performance simulation model, thereby saving the labor cost, and the accuracy of acquiring the simulation result through the gas circuit performance simulation model is high and the maintenance efficiency is higher.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the present invention is further described below with reference to the drawings and the embodiments.
FIG. 1 is a flow chart of a method for monitoring the condition of a gas turbine according to an embodiment of the present invention;
FIG. 2 is a graph of fuel flow for a gas turbine under various conditions in accordance with an embodiment of the present invention;
FIG. 3 is a graph of data for ambient temperature under different conditions according to an embodiment of the present invention;
FIG. 4 is a graph of data for ambient pressure under different conditions according to an embodiment of the present invention;
FIG. 5 is a graph showing the quadratic fit of the high pressure turbine to the reduced flow characteristic curve according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of the PID controller of a gas turbine according to an embodiment of the invention;
FIG. 7 is a schematic view of a simulation model of gas path performance of a gas turbine according to an embodiment of the present invention;
FIG. 8 is a diagram showing the comparison of the rotational speed of the gas engine and measured data according to an embodiment of the present invention;
FIG. 9 is a diagram showing the comparison of the compressor outlet temperature and measured data according to an embodiment of the present invention;
FIG. 10 is a diagram showing the comparison of the compressor outlet pressure with measured data according to an embodiment of the present invention;
FIG. 11 is a graph showing the comparison of inlet pressure and measured data for a power turbine according to an embodiment of the present invention;
FIG. 12 is a graph showing a comparison of inlet temperature and measured data for a power turbine according to an embodiment of the present invention;
FIG. 13 is a graph showing the comparison of the outlet temperature of a power turbine with measured data in accordance with an embodiment of the present invention;
FIG. 14 is a schematic diagram of a condition monitoring system for a gas turbine according to an embodiment of the present invention.
Detailed Description
The following examples are further illustrative and supplementary of the present invention and are not intended to limit the invention in any way.
A method and system for monitoring the condition of a gas turbine according to embodiments of the present invention are described below with reference to the accompanying drawings.
As shown in fig. 1, an embodiment of the present invention provides a method for monitoring a state of a gas turbine, including:
s1, acquiring initial and stable operation parameters of the gas turbine, and determining an actually measured stable value of a gas circuit when the gas turbine stably operates according to the initial and stable operation parameters.
In this embodiment, the sensor is used to collect initial and stable operation parameters of the gas turbine, where the sensor may include a rotation speed sensor, a temperature sensor, a pressure sensor, and the like, and each sensor may collect various parameters of the gas turbine operation in real time, where the collected parameters mainly include a compressor inlet pressure, a compressor inlet temperature, a compressor outlet temperature, a power turbine inlet pressure, a power turbine inlet temperature, a power turbine outlet temperature, and the like.
In this embodiment, the sensor is installed at a key part of the gas turbine, such as a gas inlet, a gas compressor inlet and outlet, etc., so as to monitor the operation state of the gas turbine in real time. The data interval is about 20 minutes/group, the fuel oil working condition of the actual measurement data covers 0.84-1.0 working condition, the common operation working condition of the gas turbine is covered, the obtained data graphs of the fuel flow, the ambient temperature and the ambient pressure of the gas turbine under different working conditions are respectively shown in fig. 2, 3 and 4, the actual measurement stable value of the gas circuit can be obtained through calculation by the data in fig. 2 to 4, and the process is the prior art, so that the description is omitted.
S2, determining performance index parameters of each preset part according to characteristic curves of different preset parts on the gas turbine.
S3, constructing a gas path performance simulation model of the gas turbine according to the performance index parameters corresponding to each preset part.
S4, determining the performance trend of the gas path according to the simulation result of the gas path performance simulation model, and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value.
In the embodiment, the performance index parameters of different preset parts are used for constructing the gas path performance simulation model of the gas turbine, namely, the performance trend of the gas path of the gas turbine can be obtained through a simulation experiment of the gas path performance simulation model, and the performance trend is compared with the actually measured stable value to monitor the state of the gas turbine. The application can monitor the running state of the gas turbine without manual participation in the whole process and running the gas circuit performance simulation model, thereby saving the labor cost, and the accuracy of obtaining the simulation result through the gas circuit performance simulation model is high and the maintenance efficiency is higher.
In this embodiment, if the deviation between the performance trend and the measured stable value is within the preset range, it may be determined that the gas turbine is running normally, and if the deviation between the performance trend and the measured stable value is outside the preset range, it may be determined that the gas turbine is running abnormally.
In addition, the preset range can be set according to actual conditions, different thresholds can be set, and when the deviation of the performance trend and the actually measured stable value exceeds the different thresholds, the abnormal operation can be graded early-warned.
According to the embodiment, the gas path performance of the gas turbine is simulated by using a mathematical model and an algorithm, and whether the state and the performance of the gas turbine are normal or not can be accurately judged by comparing and analyzing the gas path performance with actual operation data, so that faults and abnormal conditions can be timely found.
In addition, the maintenance efficiency of the gas turbine is improved, the performance of the gas path of the gas turbine can be monitored in real time, and detailed state information and prediction results are provided. The information can assist maintenance personnel in fault diagnosis and maintenance decision, reduces the workload of manual inspection and test, and improves the maintenance efficiency and accuracy.
Optionally, determining the performance index parameter of each preset part according to the characteristic curves of different preset parts on the gas turbine comprises:
Acquiring a pressure ratio-rotating speed-flow curve and an efficiency-rotating speed-flow curve of each preset part on the gas turbine under different rotating speed working conditions;
Performing secondary fitting on the pressure ratio-rotating speed-flow curve of each preset part by using a least square method to determine the ratio reduced flow of each preset part;
And (3) performing secondary fitting on the efficiency-rotating speed-flow curve of each preset part by a least square method, and determining the specific efficiency of each preset part.
In this embodiment, each preset part includes two clusters of characteristic curves (which may be obtained from published literature), each cluster is a pressure ratio-rotation speed-flow curve and an efficiency-rotation speed-flow curve, each cluster is composed of six different rotation speed working conditions, from 0.5 rotation speed working condition to 1.0 rotation speed working condition, and then a least square method is adopted to perform secondary fitting on the extracted data, so as to obtain a set of fitting mathematical expression of the characteristic curve of the gas turbine, so as to realize extraction of performance index parameters of the gas turbine, and the fitting mathematical expression of the characteristic curve is as follows:
Wherein, For the preset part ratio of the reduced flow rate,/>Is the ratio of preset parts,/>For the preset part specific efficiency,/>For rotational speed, f 1 and f 2 are fitted expressions of the resulting pressure ratio-rotational speed-flow curve and efficiency-rotational speed-flow curve, implemented by writing an S-function in Simulink.
In this embodiment, in order to verify the accuracy of the fitting mathematical expression of the characteristic curve, error analysis is performed, and the errors of the fitting mathematical expression of the characteristic curve and the corresponding real characteristic curve under different working conditions are counted, as shown in fig. 5, wherein, x represents the actual value of the curve, and straight represents the fitting value of the fitting mathematical expression, it can be seen that the actual value of the curve and the fitting value almost coincide, and almost no error occurs, which indicates that the fitting mathematical expression can accurately express the characteristic curve of the gas turbine, and further the corresponding performance characteristic parameters are extracted.
Optionally, constructing a gas path performance simulation model of the gas turbine according to the performance index parameters of each preset part, including:
modeling a gas compressor, a combustion chamber, a high-pressure turbine and a power turbine of the gas turbine according to the specific folding flow and the specific efficiency of the preset parts;
and combining the constructed models of the gas compressor, the combustion chamber, the high-pressure turbine and the power turbine into the gas path performance simulation model according to the input-output relation.
The gas path performance simulation model of the embodiment comprises components such as a gas compressor, a combustion chamber, a power turbine and the like, and the gas flow characteristics and interactions of each component are accurately described and modeled so as to perform simulation analysis.
In this embodiment, the modeling is performed on the compressor of the gas turbine according to the performance index parameters of the preset components, and the formula is as follows:
Wherein, G C represents the folded flow rate of the compressor and the actual flow rate of the compressor respectively,/>G C0 represents the folded flow and the actual flow of the compressor under the preset working condition, T 1、P1 represents the inlet temperature and the inlet pressure of the compressor, and T 10、P10 represents the inlet temperature and the inlet pressure of the compressor under the preset working condition,/>The method respectively represents the compressor ratio reduced flow and the compressor ratio reduced efficiency under the preset working condition, eta c0 represents the compressor actual efficiency under the preset working condition, eta c represents the compressor actual efficiency, R represents the gas constant, c pc represents the constant pressure specific heat capacity of air, P ec represents the compressor power, T 2 represents the compressor outlet temperature, and pi c represents the compressor pressure ratio.
In the embodiment, the compressor is modeled, and the outlet temperature of the compressor and the compressor power, which are the operation parameters of the gas turbine, can be obtained through simulation tests, so that the operation state of the compressor is monitored.
In this embodiment, according to the performance index parameters of the preset components, the combustion chamber of the gas turbine is modeled according to the following formula:
P3＝σb·P2 (7)
Wherein T 3 represents the outlet temperature of the combustion chamber, LHV represents the low calorific value of the fuel, η b combustion efficiency, c p,t represents the variable specific heat of the gas, σ b represents the total pressure recovery coefficient of the combustion chamber, P 2 represents the compressor outlet pressure, P 3 represents the high pressure turbine inlet pressure, gcout represents the compressor outlet flow, and G f represents the combustion chamber outlet pressure.
In the embodiment, the combustion chamber is modeled, and a simulation test can be performed to obtain the outlet temperature of the combustion chamber and the outlet pressure of the combustion chamber, wherein the outlet temperature of the combustion chamber and the outlet pressure of the combustion chamber are all operation parameters of the gas turbine, so that the operation state of the combustion chamber is monitored.
In this embodiment, the modeling is performed on the high-pressure turbine of the gas turbine according to the performance index parameters of the preset components, and the formula is as follows:
Gtout＝Gtin (11)
Wherein, G t represents the high-pressure turbine reduced flow and the high-pressure turbine actual flow, respectively,/>G t0 represents the high-pressure turbine reduced flow and the high-pressure turbine actual flow, respectively, under the preset condition, T 3 represents the outlet temperature of the combustion chamber, and T 30、Pt0 represents the outlet temperature of the combustion chamber and the high-pressure turbine inlet pressure, respectively, under the preset condition,/>The method respectively represents a high-pressure turbine ratio reduced flow rate and high-pressure turbine ratio reduced efficiency under a preset working condition, eta t represents high-pressure turbine actual efficiency, eta t0 represents high-pressure turbine actual efficiency under the preset working condition, gtin represents high-pressure turbine inlet flow rate, gtout is high-pressure turbine outlet flow rate, pi t represents high-pressure turbine expansion ratio, P 4 represents high-pressure turbine outlet pressure, P et represents high-pressure turbine power, and c pt represents gas constant-pressure specific heat capacity.
In the embodiment, the high-pressure turbine is modeled, and a simulation test can be performed to obtain the outlet flow of the high-pressure turbine, the outlet pressure of the high-pressure turbine, the outlet temperature of the high-pressure turbine and the high-pressure turbine power, wherein the outlet flow of the high-pressure turbine, the outlet pressure of the high-pressure turbine, the outlet temperature of the high-pressure turbine and the high-pressure turbine power are all operation parameters of the gas turbine, so that the operation state of the combustion chamber is monitored.
In this embodiment, the power turbine of the gas turbine is modeled according to the performance index parameters of the preset components, and the formula is as follows:
Wherein T 5 represents the power turbine outlet temperature, pi pt represents the power turbine expansion ratio, eta pt represents the power turbine actual efficiency, G t represents the power turbine reduced flow and the power turbine actual flow, respectively,/>G t0 represents the power turbine folded flow and the power turbine actual flow under the preset working condition respectively, T 3 represents the outlet temperature of the combustion chamber, and T 30、Pt0 represents the outlet temperature of the combustion chamber and the inlet pressure of the high-pressure turbine under the preset working condition respectively,/>The power turbine ratio folding flow and the power turbine ratio folding efficiency under the preset working conditions are respectively represented, eta t0 represents the actual efficiency of the power turbine under the preset working conditions, c pt is the constant-pressure specific heat capacity of fuel gas, and P et represents the power of the power turbine.
In the embodiment, the power turbine is modeled, and a simulation test can be performed to obtain the outlet temperature and the power of the power turbine, wherein the outlet temperature and the power of the power turbine are the operation parameters of the gas turbine, so that the operation state of the power turbine is monitored.
Optionally, further comprising constructing a rotor model between the constructed compressor model and the high pressure turbine model, and constructing a volumetric model between the constructed gas chamber model and the power turbine model.
In the embodiment, the large volume inertia of the gas turbine connecting pipeline is considered, the pressure and the flow of the gas in the pipeline can be changed, a volume model is established by adopting an integral method, in addition, the rotational inertia of the gas generator shaft in the acceleration and deceleration process is considered, a first-order differential equation is used for describing the rotational inertia, a rotor model is established, and the rotating speed of the gas compressor is obtained; by adding the volume model and the rotor model into the air path performance simulation model, the performance trend of the final air path is more accurate, and the accuracy of the simulation result is improved.
Optionally, the constructing a rotor model between the constructed compressor model and the high pressure turbine model includes:
acquiring rotor rotational inertia, gas generator shaft rotational speed, high-pressure turbine output power, power required by a compressor and gas generator shaft efficiency;
And constructing a rotor model according to the rotor rotational inertia, the gas generator shaft rotational speed, the high-pressure turbine output power, the power required by the gas compressor and the gas generator shaft efficiency.
In the embodiment, considering that the rotation inertia exists in the acceleration and deceleration process of the gas generator shaft, a first-order differential equation is used for describing the rotation inertia, a rotor model is built, and the rotating speed of the gas compressor is obtained; by adding the rotor model into the air path performance simulation model, the performance trend of the final air path is more accurate, and the accuracy of the simulation result is improved.
Optionally, the formula of the rotor model is as follows:
Wherein dn represents the rotation speed of the compressor, The method is characterized in that the rotating speed of the compressor is calculated in real time in an integral mode, I represents the rotating inertia of a rotor, n represents the rotating speed of a gas generator shaft, P eT represents the output power of a high-pressure turbine, P eC represents the required power of the compressor, and eta m represents the efficiency of the gas generator shaft.
In this embodiment, the rotational speed of the compressor is affected by the rotational inertia of the gas generator shaft during acceleration and deceleration, and the rotational inertia affects the parameters related to the compressor model and the high-pressure turbine model, so that a rotor model is constructed between the compressor model and the high-pressure turbine model, thereby considering the influence of the high-pressure turbine model and the combustor model on the rotational speed of the compressor.
Optionally, the constructing a volumetric model between the constructed gas chamber model and the power turbine model includes:
acquiring a gas constant, the outlet temperature of a connecting pipeline of the gas turbine, the outlet flow of a cavity of the connecting pipeline, the inlet flow of the cavity of the connecting pipeline and the volume of the cavity of the connecting pipeline;
and constructing a volume model according to the gas constant, the outlet temperature of the connecting pipeline of the gas turbine, the outlet flow of the cavity of the connecting pipeline, the inlet flow of the cavity of the connecting pipeline and the volume of the cavity of the connecting pipeline.
In the embodiment, the fact that the large volume inertia exists in the connecting pipeline of the gas turbine is considered, the pressure and the flow of the gas in the pipeline can be changed, and a volume model is built by adopting an integral method; by adding the volume model into the air path performance simulation model, the performance trend of the final air path is more accurate, and the accuracy of the simulation result is improved.
Optionally, the volume model formula is as follows:
wherein dp represents the ratio of the pressure and the flow rate of the gas in the connecting pipeline, The pressure and flow ratio of the gas in the connecting pipeline are calculated in real time in an integral mode, R is a gas constant, tout is the outlet temperature of the connecting pipeline, gout is the outlet flow of the cavity of the connecting pipeline, gin is the inlet flow of the cavity of the connecting pipeline, and V is the volume of the cavity of the connecting pipeline.
In the embodiment, a volume model is also established, so that the influence of the volume inertia of the connecting pipeline of the gas turbine on the gas circuit is considered, the performance trend of the final gas circuit is more accurate, and the accuracy of the simulation result is improved.
In summary, the simulation result of the gas path performance simulation model may be a gas compressor rotation speed, a gas compressor outlet temperature, a gas compressor outlet pressure, a gas compressor power, a combustion chamber outlet temperature, a combustion chamber outlet pressure, an outlet flow of the high-pressure turbine, an outlet pressure of the high-pressure turbine, an outlet temperature of the high-pressure turbine, a high-pressure turbine power, a power turbine inlet pressure, a power turbine inlet temperature, an outlet temperature of the power turbine, a power turbine power, and the like.
Optionally, the method for monitoring the state of the gas turbine provided by the embodiment of the invention further includes constructing a P ID control module, where the P ID control module is connected with the established combustion chamber model and the power turbine model respectively, and is specifically used for:
the fuel quantity input into the combustion chamber is regulated, and a simulation operation test of the gas turbine is carried out through the gas path performance simulation model;
acquiring power turbine outlet power and judging whether the power turbine outlet power is equal to a target value or not;
And if the power turbine outlet power is smaller than the target value, acquiring deviation of the power turbine outlet power from the target value, and controlling the magnitude of the fuel quantity input into the combustion chamber according to the deviation until the power turbine outlet power is equal to the target value.
The PID controller can be used for simulating the operation process of the gas turbine, controlling the output value of the gas turbine and optimizing the performance of the gas turbine, thereby improving the operation efficiency and the safety of the gas turbine.
As shown in fig. 6, the operation state of the gas turbine is simulated based on the power reference, the fuel amount is input to the gas turbine according to the preset fuel flow, the output power (power turbine outlet power) of the gas turbine is compared with the target value, and if the output power does not reach the target value, the magnitude of the fuel amount input to the gas turbine is adjusted by the PID controller, so that the output power reaches the target value.
Alternatively, as shown in fig. 7, the gas path performance simulation model includes a compressor model, a combustion chamber model, a high pressure turbine model, a power turbine model, a rotor model, and a volume model, wherein the compressor model, the combustion chamber model, the high pressure turbine model, and the power turbine model are sequentially connected, and in addition, the rotor model 1 is connected between the compressor model and the high pressure turbine model, the volume model is connected between the gas chamber model and the power turbine model, and one rotor model 2 is separately added in the power turbine model for measuring the rotation speed of the power turbine.
The whole gas path performance simulation model outputs simulation results of all preset parts to codes programmed by basicuxy programming languages for calculating performance trend of the gas path, and meanwhile, the gas path performance simulation model is also connected with a PID controller, and the fuel quantity input into the gas turbine is regulated through the PID controller, so that the output power (power turbine outlet power) of the gas turbine is equal to a target value.
Optionally, in this embodiment, the gas path performance state of the gas turbine is monitored and predicted in real time through a gas path performance simulation model, wherein a portion of the simulation results are selected to be compared with the measured stable value, for example, the comparison of the rotational speed of the gas compressor and the measured stable value at different operating points is shown in fig. 8, the comparison of the outlet temperature of the gas compressor and the measured stable value at different operating points is shown in fig. 9, the comparison of the outlet pressure of the gas compressor and the measured stable value at different operating points is shown in fig. 10, the comparison of the inlet pressure of the power turbine and the measured stable value at different operating points is shown in fig. 11, the comparison of the inlet temperature of the power turbine and the measured stable value at different operating points is shown in fig. 12, and the comparison of the outlet temperature of the power turbine and the measured stable value at different operating points is shown in fig. 13. 8-13, whether the gas path performance of the gas turbine is abnormal can be judged, and early warning information can be provided.
As shown in FIG. 14, the present invention provides a condition monitoring system for a gas turbine, comprising:
The actual measurement stable value determining module is used for acquiring initial and stable operation parameters of the gas turbine and determining actual measurement stable values of the gas circuit when the gas turbine stably operates according to the initial and stable operation parameters;
The performance index parameter determining module is used for determining the performance index parameter of each preset part according to the characteristic curves of different preset parts on the gas turbine;
the gas path performance simulation model construction module is used for constructing a gas path performance simulation model of the gas turbine according to the performance index parameters corresponding to each preset part;
the monitoring module is used for determining the performance trend of the gas circuit according to the simulation result of the gas circuit performance simulation model and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value.
Optionally, the performance index parameter determining module is specifically configured to:
the characteristic curves of the gas turbine are obtained, wherein the characteristic curves comprise a pressure ratio-rotating speed-flow curve and an efficiency-rotating speed-flow curve of each preset part on the gas turbine under different rotating speed working conditions;
Performing secondary fitting on the pressure ratio-rotating speed-flow curve of each preset part by using a least square method to determine the ratio reduced flow of each preset part;
performing secondary fitting on the efficiency-rotating speed-flow curve of each preset part by a least square method to determine the specific efficiency of each preset part;
the performance index parameters include the specific folding flow and the specific folding efficiency of each preset component.
Optionally, the gas path performance simulation model construction module is specifically configured to:
modeling a gas compressor, a combustion chamber, a high-pressure turbine and a power turbine of the gas turbine according to the specific folding flow and the specific efficiency of the preset parts;
and combining the constructed models of the gas compressor, the combustion chamber, the high-pressure turbine and the power turbine into the gas path performance simulation model according to the input-output relation.
Optionally, the system further comprises a rotor model construction module, specifically configured to:
acquiring rotor rotational inertia, gas generator shaft rotational speed, high-pressure turbine output power, power required by a compressor and gas generator shaft efficiency;
And constructing a rotor model according to the rotor rotational inertia, the gas generator shaft rotational speed, the high-pressure turbine output power, the power required by the gas compressor and the gas generator shaft efficiency.
Optionally, the rotor model building module is specifically configured to:
the formula of the rotor model is as follows:
Wherein dn represents the rotation speed of the compressor, The method is characterized in that the rotating speed of the compressor is calculated in real time in an integral mode, I represents the rotating inertia of a rotor, n represents the rotating speed of a gas generator shaft, P eT represents the output power of a high-pressure turbine, P eC represents the required power of the compressor, and eta m represents the efficiency of the gas generator shaft.
Optionally, the system further comprises a volume model construction module, specifically configured to:
acquiring a gas constant, the outlet temperature of a connecting pipeline of the gas turbine, the outlet flow of a cavity of the connecting pipeline, the inlet flow of the cavity of the connecting pipeline and the volume of the cavity of the connecting pipeline;
and constructing a volume model according to the gas constant, the outlet temperature of the connecting pipeline of the gas turbine, the outlet flow of the cavity of the connecting pipeline, the inlet flow of the cavity of the connecting pipeline and the volume of the cavity of the connecting pipeline.
Optionally, the volumetric model building module is specifically configured to:
the volume model formula is as follows:
wherein dp represents the ratio of the pressure and the flow rate of the gas in the connecting pipeline, The pressure and flow ratio of the gas in the connecting pipeline are calculated in real time in an integral mode, R is a gas constant, tout is the outlet temperature of the connecting pipeline, gout is the outlet flow of the cavity of the connecting pipeline, gin is the inlet flow of the cavity of the connecting pipeline, and V is the volume of the cavity of the connecting pipeline.
Optionally, the system further comprises an adjustment module, in particular for:
the fuel quantity input into the combustion chamber is regulated, and a simulation operation test of the gas turbine is carried out through the gas path performance simulation model;
acquiring power turbine outlet power and judging whether the power turbine outlet power is equal to a target value or not;
And if the power turbine outlet power is smaller than the target value, acquiring deviation of the power turbine outlet power from the target value, and controlling the magnitude of the fuel quantity input into the combustion chamber according to the deviation until the power turbine outlet power is equal to the target value.
The computing device of the embodiment of the invention comprises a memory, a processor and a program stored on the memory and running on the processor, wherein the processor realizes part or all of the steps of the state monitoring method of the gas turbine when executing the program.
The computing device may be a computer, and correspondingly, the program is computer software, and the parameters and steps in the above-mentioned computing device of the present invention may refer to the parameters and steps in the above-mentioned embodiment of a method for monitoring the status of a gas turbine, which are not described herein.
Those skilled in the art will appreciate that the present invention may be implemented as a system, method, or computer program product. Accordingly, the present disclosure may be embodied in the following forms, namely: either entirely hardware, entirely software (including firmware, resident software, micro-code, etc.), or entirely software, or a combination of hardware and software, referred to herein generally as a "circuit," module "or" system. Furthermore, in some embodiments, the invention may also be embodied in the form of a computer program product in one or more computer-readable media, which contain computer-readable program code. The computer readable storage medium can be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or a combination of any of the foregoing.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.

Claims (10)

1. A method of monitoring the condition of a gas turbine, comprising:
Acquiring initial and stable operation parameters of the gas turbine, and determining an actually measured stable value of a gas circuit when the gas turbine stably operates according to the initial and stable operation parameters;
Determining performance index parameters of each preset part according to characteristic curves of different preset parts on the gas turbine;
constructing a gas path performance simulation model of the gas turbine according to the performance index parameters of each preset part;
And determining the performance trend of the gas path according to the simulation result of the gas path performance simulation model, and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value.
2. The method of claim 1, wherein said determining performance index parameters for each of said predetermined components based on characteristics of different predetermined components on the gas turbine comprises:
Acquiring a pressure ratio-rotating speed-flow curve and an efficiency-rotating speed-flow curve of each preset part on the gas turbine under different rotating speed working conditions;
Performing secondary fitting on the pressure ratio-rotating speed-flow curve of each preset part by a least square method to determine the ratio reduced flow of each preset part;
and performing secondary fitting on the efficiency-rotating speed-flow curve of each preset part by a least square method to determine the specific efficiency of each preset part.
3. The method of claim 2, wherein constructing a gas path performance simulation model of the gas turbine based on the performance index parameters of each of the predetermined components comprises:
modeling a gas compressor, a combustion chamber, a high-pressure turbine and a power turbine of the gas turbine according to the specific folding flow and the specific efficiency of the preset parts;
and combining the constructed models of the gas compressor, the combustion chamber, the high-pressure turbine and the power turbine into the gas path performance simulation model according to the input-output relation.
4. A method according to claim 3, further comprising constructing a rotor model between the constructed compressor model and the high pressure turbine model, and constructing a volumetric model between the constructed gas chamber model and the power turbine model.
5. The method of claim 4, wherein said constructing a rotor model between the constructed compressor model and the high pressure turbine model comprises:
acquiring rotor rotational inertia, gas generator shaft rotational speed, high-pressure turbine output power, power required by a compressor and gas generator shaft efficiency;
And constructing a rotor model according to the rotor rotational inertia, the gas generator shaft rotational speed, the high-pressure turbine output power, the power required by the gas compressor and the gas generator shaft efficiency.
6. The method of claim 5, wherein the formula of the rotor model is as follows:
Wherein dn represents the rotation speed of the compressor, The method is characterized in that the rotating speed of the compressor is calculated in real time in an integral mode, I represents the rotating inertia of a rotor, n represents the rotating speed of a gas generator shaft, P eT represents the output power of a high-pressure turbine, P eC represents the required power of the compressor, and eta m represents the efficiency of the gas generator shaft.
7. The method of claim 4, wherein the constructing a volumetric model between the constructed gas chamber model and the power turbine model comprises:
acquiring a gas constant, the outlet temperature of a connecting pipeline of the gas turbine, the outlet flow of a cavity of the connecting pipeline, the inlet flow of the cavity of the connecting pipeline and the volume of the cavity of the connecting pipeline;
and constructing a volume model according to the gas constant, the outlet temperature of the connecting pipeline of the gas turbine, the outlet flow of the cavity of the connecting pipeline, the inlet flow of the cavity of the connecting pipeline and the volume of the cavity of the connecting pipeline.
8. The method of claim 7, wherein the volumetric model formula is as follows:
wherein dp represents the ratio of the pressure and the flow rate of the gas in the connecting pipeline, The pressure and flow ratio of the gas in the connecting pipeline are calculated in real time in an integral mode, R is a gas constant, tout is the outlet temperature of the connecting pipeline, gout is the outlet flow of the cavity of the connecting pipeline, gin is the inlet flow of the cavity of the connecting pipeline, and V is the volume of the cavity of the connecting pipeline.
9. A method according to claim 3, further comprising constructing a PID control module, which is connected to the established combustor model and power turbine model, respectively, in particular for:
The fuel quantity input into the combustion chamber model is regulated, and a simulation operation test of the gas turbine is carried out through the gas path performance simulation model;
Obtaining the outlet power of a power turbine model, and judging whether the outlet power of the power turbine model is equal to a target value or not;
And if the outlet power of the power turbine model is smaller than the target value, acquiring the deviation between the outlet power of the power turbine model and the target value, and adjusting the amount of fuel input into the combustion chamber model according to the deviation until the outlet power of the power turbine model is equal to the target value.
10. A condition monitoring system for a gas turbine, comprising:
the actual measurement stable value determining module is used for acquiring initial and stable operation parameters of the gas turbine and determining an actual measurement stable value of a gas circuit when the gas turbine stably operates according to the initial and stable operation parameters;
The performance index parameter determining module is used for determining the performance index parameter of each preset part according to the characteristic curves of different preset parts on the gas turbine;
The gas path performance simulation model construction module is used for constructing a gas path performance simulation model of the gas turbine according to the performance index parameters corresponding to each preset part;
and the monitoring module is used for determining the performance trend of the gas circuit according to the simulation result of the gas circuit performance simulation model and determining the running state of the gas turbine according to the deviation of the performance trend and the actually measured stable value.
CN202410030465.5A 2024-01-09 2024-01-09 State monitoring method and system of gas turbine Pending CN118030207A (en)

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