CN114611300A - Method for soft measurement of efficiency parameters of key components of heavy-duty gas turbine - Google Patents

Method for soft measurement of efficiency parameters of key components of heavy-duty gas turbine Download PDF

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CN114611300A
CN114611300A CN202210248239.5A CN202210248239A CN114611300A CN 114611300 A CN114611300 A CN 114611300A CN 202210248239 A CN202210248239 A CN 202210248239A CN 114611300 A CN114611300 A CN 114611300A
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turbine
outlet
gas
compressor
combustion chamber
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胡孟起
肖俊峰
夏林
连小龙
王一丰
高松
王峰
王玮
李晓丰
王致程
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Xian Thermal Power Research Institute Co Ltd
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Abstract

The invention discloses a soft measurement method for efficiency parameters of key components of a heavy-duty gas turbine, which comprises the following steps: s1, establishing a compressor mathematical model; s2, establishing a mathematical model of the combustion chamber; s3, establishing a mathematical model for processing the turbine cooling air quantity; s4, establishing a turbine mathematical model on the basis of the S3 turbine cooling air quantity processing mathematical model; and S5, establishing an overall mathematical model for soft measurement of the performance parameters of the key parts of the heavy-duty gas turbine after calculating the connection between the input quantity and the output quantity in the steps S1, S2, S3 and S4. The method can solve the problem that soft measurement of comprehensive efficiency indexes or parameters of key parts of the heavy-duty gas turbine, which cannot be directly measured in actual operation such as the efficiency of a gas compressor, the efficiency of a turbine, the outlet temperature of a combustion chamber and the like, is realized by establishing and solving a determined thermodynamic coupling equation based on the thermodynamic principle of the gas turbine under the conditions that a chromatograph (for measuring the components and the heat value of fuel gas) and the measurement data of a fuel flow meter or the measurement data are inaccurate.

Description

Method for soft measurement of efficiency parameters of key components of heavy gas turbine
Technical Field
The invention belongs to the field of thermal energy power engineering, and particularly relates to a method for soft measurement of efficiency parameters of key parts of a heavy-duty gas turbine.
Background
The construction of a novel power system mainly based on new energy power generation is an inevitable choice for achieving the double carbon targets of 'carbon peak reaching and carbon neutralization'. As the new energy power generation has the characteristics of strong intermittence and large fluctuation, a large number of flexible power supplies are required to be equipped for ensuring the safe and stable operation of a power grid. The gas-steam combined cycle power generation unit has the characteristics and advantages of high efficiency, low carbon and flexibility, and in the process of constructing a novel power system taking new energy as a main body, before the safe and stable large-scale energy storage technology is commercialized, gas-steam combined cycle power generation is an important partner for supporting the new energy to grow into the main body in the novel power system, and becomes one of the indispensable important components of power grid installation.
In view of the fact that a gas turbine, which is a core device of a gas-steam combined cycle generator set, is operated under severe working conditions of high temperature, high pressure, high rotation speed, high mechanical stress and thermal stress, various mechanical damages and efficiency degradations are easily generated along with the increase of operation time of key components (such as a gas compressor, a combustion chamber and a turbine), and serious faults are easily caused to threaten the safe operation of the unit, the gas turbine operation state monitoring, fault diagnosis and early warning technology has gradually become one of the research hotspots in the field of gas turbine service maintenance in recent years.
In order to realize online diagnosis and early warning of faults of the gas turbine, one of the technical keys is how to utilize directly monitorable operation parameters to obtain the efficiency of key parts of a gas turbine compressor, a turbine and the like and the temperature of an outlet of a combustion chamber and other key comprehensive efficiency indexes or parameters which cannot be directly measured by a soft measurement method so as to realize monitoring and analysis of the operation state of the key parts. In the actual operation process of the gas turbine, when some parts have efficiency decline or damage, the performance indexes or parameters such as the efficiency of the parts can be changed, and further, measurable parameters (such as temperature, pressure, rotating speed and the like) can be changed, therefore, the essence of the soft measurement of the performance indexes of the parts of the heavy-duty gas turbine is that the comprehensive performance indexes or parameters such as the efficiency of the parts can be obtained by solving measurable thermodynamic parameters (such as atmospheric temperature, pressure, relative humidity, pressure loss of inlet and outlet gases of the gas turbine, fuel components, heat values and the like) through a thermodynamic coupling equation.
In addition, many in-service heavy-duty gas turbines in early domestic operation are not equipped with a chromatograph (for measuring fuel gas components and heat values) or a fuel flow meter independently, and even if some units are equipped with fuel flow meters or chromatographs (for measuring fuel gas components and heat values), the accuracy is poor, and the situation brings difficulty in establishing a specific thermodynamic coupling equation for an actual unit.
At present, no public method for soft measurement of the efficiency index of the heavy gas turbine part is available, which can realize soft measurement of key comprehensive efficiency indexes or parameters which can not be directly measured, such as the efficiency of key parts of a gas turbine compressor, a turbine and the like, the outlet temperature of a combustion chamber and the like, under the conditions of no chromatograph (for measuring the components and the heat value of fuel gas), inaccurate measurement data of a fuel flow meter or inaccurate measurement data.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a method for soft measurement of the efficiency parameters of key parts of a heavy-duty gas turbine.
The invention is realized by adopting the technical scheme that:
a soft measurement method for efficiency parameters of key components of a heavy-duty gas turbine comprises the following steps:
s1, establishing a compressor mathematical model, wherein the calculated output quantity is used as the known input quantity provided by the establishment of the combustion chamber mathematical model in the step S2;
s2, establishing a combustion chamber mathematical model, wherein the calculated output quantity of the combustion chamber mathematical model is used as the known input quantity provided by the establishment of the turbine mathematical model in the step S4;
s3, establishing a mathematical model for processing the turbine cooling air quantity;
s4, establishing a turbine mathematical model on the basis of the S3 turbine cooling air quantity processing mathematical model;
and S5, establishing an overall mathematical model for soft measurement of the performance parameters of the key parts of the heavy-duty gas turbine after calculating the connection between the input quantity and the output quantity in the steps S1, S2, S3 and S4.
The invention is further improved in that in step S1, when the mathematical model of the compressor is established, the total inlet temperature T is determined2Total pressure p2Flow rate G2Air extraction flow and air extraction enthalpy value hbleed1、hbleed2、hbleed3Total pressure p at the outlet3As input quantity, the isentropic efficiency eta of the compressorcAs an assumed value, the value is finally obtained by iterative calculation; calculating the output as the total temperature T of the outlet of the compressor3Outlet flow rate G3Gas compressor power consumption Nc；
The basic calculation formula of the compressor mathematical model is as follows:
(1) according to the formula (1) and the formula (2), the total temperature T of the inlet of the compressor is determined2Calculating the air inlet relative pressure ratio pi of the compressor2And specific enthalpy ha,T2；
lgπ2＝f1(T2) (1)
Figure BDA0003545769070000031
(2) Calculating the relative pressure ratio pi of the outlet of the compressor according to the formula (3) and the formula (4)3；
Figure BDA0003545769070000032
π3＝πc×π2 (4)
(3) Calculating the isentropic temperature T of the outlet of the compressor according to the formula (5)3S；
T3S＝f3[lg(π3)] (5)
(4) According to equation (6), from T3SCalculating the isentropic specific enthalpy h of air at the outlet of the compressora,T3S；
Figure BDA0003545769070000033
(5) According to the formula (7), calculating the actual specific enthalpy h of the air at the outlet of the compressora,T3；
Figure BDA0003545769070000034
(6) According to the formula (8), the air temperature at the outlet of the air compressor is obtained
Figure BDA0003545769070000041
(7) Calculating the compressor outlet air flow G according to the formula (9)3；
G3＝G2-Gbleed1-Gbleed2-Gbleed3 (9)
(8) Calculating the power consumption N of the compressor according to the formula (10)C；
NC＝G3h3-G2h2+Gbleed1hbleed1+Gbleed2hbleed2+Gbleed3hbleed3 (10)
In the above formulas (1), (2), (5) and (8), f1、f2、f3、f4By looking up correlationsObtaining the air physical property parameter table;
in the above equations (1) to (10), the temperature is expressed in K, the specific enthalpy is expressed in kJ/kg, the pressure is expressed in kPa, the flow rate is expressed in kg/s, and the power is expressed in kW.
A further refinement of the invention is that in step S2, the combustor inlet air flow rate G is modeled as a mathematical model of the combustor31Air temperature T31As an input quantity; input quantity Q of combustion chamber energyfAs an assumed value, the value is finally obtained by iterative calculation; calculating the output as the flow G of the flue gas at the outlet of the combustion chamber4Temperature T4Composition and enthalpy h4；
The principle calculation formula of the combustion chamber model is as follows:
Figure BDA0003545769070000042
in the above formula:
Gfis the fuel flow, kg/s;
hfsensible enthalpy kJ/kg corresponding to the temperature of fuel entering a combustion chamber; the enthalpy display of the fuel is recommended by the Standard "gas turbine acceptance test" GB/T14100-2016
Figure BDA0003545769070000043
Calculating a polynomial;
hf0the sensible enthalpy of the fuel at 15 ℃ is kJ/kg;
Qlothe fuel low calorific value is kJ/kg at the temperature of 15 ℃ and normal pressure; the low calorific value of the fuel is obtained by calculating the components of natural gas according to the standard calculation method of natural gas calorific value, density, relative density and Wobbe index;
G31the air quantity is the inlet air quantity of the combustion chamber, kg/s; if no other flow rate is between the outlet of the compressor and the inlet of the combustion chamber, the inlet air quantity of the combustion chamber is equal to the outlet air quantity G of the compressor3；
h31Is the enthalpy value of the air at the inlet of the combustion chamber, kJ/kg; if the compressor is outNo other flow and energy are in or out from the inlet of the combustion chamber, and the air enthalpy value of the inlet of the combustion chamber is equal to the air enthalpy value h of the outlet of the compressor3；
p31The inlet air pressure, kPa, of the combustion chamber is equal to the outlet air pressure p of the compressor3；
h0airThe enthalpy value of air at a reference temperature (15 ℃) is kJ/kg;
Qfis the energy input of the combustion chamber, kW;
G4the calculation formula is that the combustion chamber outlet gas flow is kg/s:
G4＝G31+Gf (12)
h4is the enthalpy value of the fuel gas at the outlet of the combustion chamber, kJ/kg; the enthalpy value of the fuel gas is equal to the sum of products of enthalpy values of components of the fuel gas and mass fractions of the components of the fuel gas, the enthalpy value of each component of the fuel gas can be calculated by looking up a related physical property parameter table, the enthalpy value of each component of the fuel gas is calculated by using a shining formula in open literature, and the components of the fuel gas are calculated by a combustion chemical reaction equation;
h0gasis the enthalpy value of the gas at the outlet of the combustion chamber at the reference temperature (15 ℃), kJ/kg;
p4is the combustion chamber outlet gas pressure, kPa.
The invention is further improved in that h0airThe enthalpy of air at a reference temperature is taken to be 15 ℃.
The invention is further improved in that, in step S3, the mass conservation and the principle of equal work in the turbine are converted into a total equivalent flow, and the total equivalent flow consists of two parts: one part of the cooling air flows in from the inlet of the turbine stationary blade and then participates in work, and the work amount of the cooling air is equal to the work amount of the cooling air which flows in from each part; the other part flows in from the turbine outlet, does not participate in work, and only reduces the temperature of the gas at the turbine outlet, and the basic equation is as follows:
the calculation formula of the equivalent flow at the inlet of the turbine is as follows:
GTein＝GTin+Gein (13)
the turbine outlet flow is:
GTout＝GTin+Gein+Geout (14)
in the formula, GTinIs the gas flow at the inlet of the turbine in kg/s, if no other flow enters or exits from the outlet of the combustion chamber to the inlet of the turbine, the gas flow at the inlet of the turbine is equal to the gas flow G at the outlet of the combustion chamber4；
GeinThe equivalent cooling air flow rate of a turbine inlet participating in work is kg/s;
Geoutthe flow rate of equivalent cooling air at the outlet of the turbine which does not participate in work is kg/s;
GToutthe gas flow at the outlet of the turbine is kg/s;
on the basis of the formula calculation, the components, enthalpy value and temperature of the mixed flue gas can be calculated according to the basic principles of the mass and energy conservation in the flue gas mixing process.
In a further development of the invention, in step S4, a turbine model is created on the basis of a turbine cooling air equivalent processing model, and the turbine inlet flue gas flow G is measured41Temperature T41Enthalpy value h41Pressure p41The flue gas pressure p at the turbine outlet5As an input quantity; efficiency of turbine etatAs an assumed value, the value is finally obtained by iterative calculation; calculating the flow G of the flue gas at the outlet of the turbine6Temperature T6Enthalpy value h6Work done by turbine NT；
The principle calculation formula of the turbine model is as follows:
(1) calculating the relative pressure ratio of each gas component at the inlet of the turbine:
Figure BDA0003545769070000063
in the formula, the lower subscript i represents each smoke component, f5According to the expression of the historical shining inquired in the open literature;
(2) calculating the gas relative pressure ratio of the turbine inlet;
Figure BDA0003545769070000061
in the formula: pig,T41Is the relative pressure ratio of the flue gas,
Figure BDA0003545769070000062
is a mole fraction;
(3) calculating the expansion ratio epsilon of the turbinetIsentropic relative pressure ratio pi of turbine outletg,T5S；
Figure BDA0003545769070000071
Figure BDA0003545769070000072
(4) Calculating turbine outlet isentropic temperature T5SAnd enthalpy value hg,T5S；
Figure BDA0003545769070000076
Figure BDA0003545769070000077
(5) Calculating the actual specific enthalpy h of the gas at the turbine outletg,T5；
Figure BDA0003545769070000073
(6) Calculating the actual temperature T of the turbine outlet5
Figure BDA0003545769070000074
(7) Calculating the working power N of the turbineT
Figure BDA0003545769070000075
(8) Calculating the turbine outlet temperature T mixed with the cooling amount from the mass and energy balance5And enthalpy value hg,T6；
In the above equations (15) to (23), the temperature is expressed in K, the specific enthalpy is expressed in kJ/kg, the pressure is expressed in kPa, the flow rate is expressed in kg/s, and the power is expressed in kW.
In a further improvement of the present invention, in step S5, the input variables in the performance parameter analysis model of the key components of the gas turbine include: compressor inlet air temperature T2Pressure p2Flow rate G2Outlet pressure p3Turbine exhaust pressure p5(ii) a There are three unknowns as iteration parameters, namely: etac、Qf、ηtcAnd the final iteration results of the three unknown quantities enable the deviation of three output results of the outlet temperature of the gas compressor, the outlet temperature of the turbine and the output power of the gas turbine generator set from the measured value to be smaller than the set residual value.
The further improvement of the invention is that in step S6, the whole mathematical model for the performance parameter analysis of the key components of the heavy-duty gas turbine has a unique solution because the unknown number is equal to the number of the equations, and the solution is performed by using a newton-raphson numerical iteration solution according to the least square principle.
The invention has at least the following beneficial technical effects:
the method for soft measurement of the efficiency parameters of the key components of the heavy-duty gas turbine can solve the problem that the comprehensive efficiency indexes or parameters of the key components of the heavy-duty gas turbine which cannot be directly measured in actual operation such as the efficiency of a gas compressor, the efficiency of a turbine, the outlet temperature of a combustion chamber and the like are soft-measured by establishing and solving a defined thermodynamic coupling equation on the basis of the thermodynamic principle of the gas turbine under the conditions that a chromatograph (for measuring the components and the heat value of fuel gas) and the measurement data of a fuel flowmeter are not accurate or the measurement data are inaccurate.
Drawings
FIG. 1 is a schematic view of a compressor model
FIG. 2 is a schematic view of a combustion chamber model
FIG. 3 is a schematic view of a turbine model
FIG. 4 is a schematic diagram of an overall soft-measurement model of performance parameters of key components of a gas turbine
Fig. 5 is a schematic diagram of the compressor efficiency calculation results.
FIG. 6 is a schematic representation of the results of the turbine efficiency calculations.
FIG. 7 is a graph showing the results of combustion chamber outlet temperature calculations.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The invention provides a method for soft measurement of efficiency parameters of key parts of a heavy-duty gas turbine, which comprises the following steps:
s1 establishing mathematical model of compressor
The compressor model is schematically shown in figure 1. When a mathematical model of the gas compressor is established, the total inlet temperature T is measured2Total pressure p2Flow rate G2And the flow rate of the exhaust gas (three for example) Gbleed1、Gbleed2、Gbleed3And enthalpy value h of pumpingbleed1、hbleed2、hbleed3Total pressure p at the outlet3Etc. as input quantities; isentropic efficiency eta of gas compressorcAs an assumed value, the value is finally obtained by iterative calculation; calculating the output as the total temperature T of the outlet of the compressor3Outlet flow rate G3Gas compressor power consumption Nc。
The basic calculation formula of the compressor mathematical model is as follows (three strands of gas extraction in the middle stage of the compressor in the embodiment are taken as an example):
(1) according to the formula (1) and the formula (2), the total temperature T of the inlet of the compressor is determined2Calculating the air inlet relative pressure ratio pi of the compressor2And specific enthalpy ha,T2；
lgπ2＝f1(T2) (1)
Figure BDA0003545769070000091
(2) Calculating the relative pressure ratio pi of the outlet of the compressor according to the formula (3) and the formula (4)3；
Figure BDA0003545769070000092
π3＝πc×π2 (4)
(3) Calculating the isentropic temperature T of the outlet of the compressor according to the formula (5)3S；
T3S＝f3[lg(π3)] (5)
(4) According to equation (6), from T3SCalculating the isentropic specific enthalpy h of air at the outlet of the compressora,T3S；
Figure BDA0003545769070000093
(5) According to the formula (7), calculating the actual specific enthalpy h of the air at the outlet of the compressora,T3；
Figure BDA0003545769070000101
(6) According to the formula (8), the air temperature at the outlet of the air compressor is obtained
Figure BDA0003545769070000102
(7) Calculating the compressor outlet air flow G according to the formula (9)3；
G3＝G2-Gbleed1-Gbleed2-Gbleed3 (9)
(8) Calculating the power consumption N of the compressor according to the formula (10)C；
NC＝G3h3-G2h2+Gbleed1hbleed1+Gbleed2hbleed2+Gbleed3hbleed3 (10)
In the above formulas (1), (2), (5) and (8), f1、f2、f3、f4The air physical property parameter table can be obtained by looking up a related air physical property parameter table, and the air physical property is calculated according to an oversensing and shining formula in a published document.
In the above equations (1) to (10), the temperature is expressed in K, the specific enthalpy is expressed in kJ/kg, the pressure is expressed in kPa, the flow rate is expressed in kg/s, and the power is expressed in kW.
S2 establishing mathematical model of combustion chamber
The combustion chamber model is schematically shown in fig. 2.
In establishing the mathematical model of the combustion chamber, the combustion chamber inlet air flow rate G is calculated31Air temperature T31As an input quantity; energy input quantity Q of combustion chamberfAs an assumed value, the value is finally obtained by iterative calculation; calculating the output as the flow G of the flue gas at the outlet of the combustion chamber4Temperature T4Composition and enthalpy h4And the like,
the principle calculation formula of the combustion chamber model is as follows:
Figure BDA0003545769070000103
in the above formula:
Gfis the fuel flow, kg/s;
hfsensible enthalpy kJ/kg corresponding to the temperature of fuel entering a combustion chamber; fuel enthalpy display adopted markStandard "gas turbine acceptance test" GB/T14100-2016 recommended
Figure BDA0003545769070000104
Calculating a polynomial;
hf0the sensible enthalpy of the fuel at 15 ℃ is kJ/kg;
Qlothe fuel low calorific value is kJ/kg at the temperature of 15 ℃ and normal pressure; the low calorific value of the fuel is calculated from natural gas components according to the standard calculation method for natural gas calorific value, density, relative density and Wobbe index.
G31The air quantity is the inlet air quantity of the combustion chamber, kg/s; if no other flow rate is between the outlet of the compressor and the inlet of the combustion chamber, the inlet air quantity of the combustion chamber is equal to the outlet air quantity G of the compressor3。
h31Is the enthalpy value of the air at the inlet of the combustion chamber, kJ/kg; if no other flow and energy are in or out from the outlet of the compressor to the inlet of the combustion chamber, the enthalpy value of the air at the inlet of the combustion chamber is equal to the enthalpy value h of the air at the outlet of the compressor3；
p31The inlet air pressure, kPa, of the combustion chamber is equal to the outlet air pressure p of the compressor3；
h0airThe enthalpy value of air at a reference temperature (15 ℃) is kJ/kg;
Qfis the energy input of the combustion chamber, kW.
G4The calculation formula is that the combustion chamber outlet gas flow is kg/s:
G4＝G31+Gf (12)
h4is the enthalpy value of the fuel gas at the outlet of the combustion chamber, kJ/kg; the enthalpy value of the fuel gas is equal to the sum of products of the enthalpy values of all components of the fuel gas and the mass fractions of all the components of the fuel gas, the enthalpy values of all the components of the fuel gas can be calculated by looking up a related physical property parameter table, the enthalpy value of all the components of the fuel gas is calculated by adopting a fierce and shining formula in open literature, and the components of the fuel gas are calculated by a combustion chemical reaction equation;
h0gasis the enthalpy value of the fuel gas at the outlet of the combustion chamber at the reference temperature (15 ℃), kJ/kg;
p4is the combustion chamber outlet gas pressure, kPa;
s3 mathematical modeling of turbine cooling air quantity processing
The basic assumptions of the turbine cooling air work cases are: the gas portion returning before the turbine vanes and in the vanes (including internally cooling the vane blades) participates in the stage's work; the gas returning behind the stator blades, in front of the rotor blades and in the rotor blades (including cooling the rotor blades from inside) does not take into account the amount of work done at this stage.
According to the hypothesis, the principle that the mass conservation and the work done in the turbine are equal of the cooling air flow of each strand is converted into the total equivalent flow, and the total equivalent flow consists of two parts: one part of the cooling air flows in from the inlet of the turbine stationary blade and then participates in work, and the work amount of the cooling air is equal to the work amount of the cooling air which flows in from each part; the other part flows in from the turbine outlet, does not participate in work, and only reduces the temperature of the gas at the turbine outlet, and the basic equation is as follows:
the calculation formula of the equivalent flow at the inlet of the turbine is as follows:
GTein＝GTin+Gein (13)
the turbine outlet flow is:
GTout＝GTin+Gein+Geout (14)
in the formula, GTinIs the turbine inlet gas flow, kg/s, if no other flow enters or exits between the combustion chamber outlet and the turbine inlet, the turbine inlet gas flow is equal to the combustion chamber outlet gas flow G4；
GeinThe equivalent cooling air flow rate of a turbine inlet participating in work is kg/s;
Geoutthe equivalent cooling air flow rate at the outlet of the turbine which does not participate in work is kg/s.
GToutThe gas flow at the outlet of the turbine is kg/s;
on the basis of the formula calculation, the components, enthalpy value and temperature of the mixed flue gas can be calculated according to the basic principles of the mass and energy conservation in the flue gas mixing process.
S4 establishing a turbine mathematical model
Establishing a turbine model on the basis of the equivalent processing model of the turbine cooling air quantity, and setting the inlet flue gas flow G of the turbine as shown in figure 341Temperature T41Enthalpy value h41Pressure p41The flue gas pressure p at the turbine outlet5As an input quantity; efficiency of turbine etatAs an assumed value, the value is finally obtained by iterative calculation; calculating the flow G of the flue gas at the outlet of the turbine6Temperature T6Enthalpy value h6Work done by turbine NT。
The principle calculation formula of the turbine model is as follows:
(1) calculating the relative pressure ratio of each gas component at the inlet of the turbine:
Figure BDA0003545769070000121
in the formula, the lower subscript i represents each smoke component. f. of5According to the expression of the historical shining inquired in the open literature;
(2) calculating the gas relative pressure ratio of the turbine inlet;
Figure BDA0003545769070000131
in the formula: pig,T41Is the relative pressure ratio of the flue gas,
Figure BDA0003545769070000132
is a mole fraction;
(3) calculating the expansion ratio epsilon of the turbinetIsentropic relative pressure ratio pi of turbine outletg,T5S；
Figure BDA0003545769070000133
Figure BDA0003545769070000134
(4) Calculating turbine outlet isentropic temperature T5SAnd enthalpy value hg,T5S；
Figure BDA0003545769070000135
Figure BDA0003545769070000136
(5) Calculating the actual specific enthalpy h of the gas at the turbine outletg,T5；
Figure BDA0003545769070000137
(6) Calculating the actual temperature T of the turbine outlet5
Figure BDA0003545769070000138
(7) Calculating the working power N of the turbineT
Figure BDA0003545769070000139
(8) Calculating the turbine outlet temperature T mixed with the cooling amount from the mass and energy balance5And enthalpy value hg,T6。
In the above equations (15) to (23), the temperature is expressed in K, the specific enthalpy is expressed in kJ/kg, the pressure is expressed in kPa, the flow rate is expressed in kg/s, and the power is expressed in kW.
S5, establishing an overall mathematical model for soft measurement of efficiency parameters of key parts of heavy-duty gas turbine
A schematic diagram of a gas turbine key component performance parameter analysis model is shown in FIG. 4, where the inputs to the model include: compressor inlet air temperature T2Pressure p2Flow rate G2Outlet pressure p3Turbine exhaust pressure p5. There are three unknowns as iteration parameters, namely: etac、Qf、ηtcAnd the final iteration results of the three unknown quantities enable the deviation of three output results of the outlet temperature of the gas compressor, the outlet temperature of the turbine and the output power of the gas turbine generator set from the measured value to be smaller than the set residual value.
S6 integral mathematical model for solving soft measurement of efficiency parameters of key parts of heavy-duty gas turbine
According to the overall mathematical model for the efficiency parameter analysis of the key parts of the heavy-duty gas turbine, due to the fact that the unknown number is equal to the number of the equations, the equation set has a unique solution, and according to the least square principle, a Newton-Raphson numerical iteration solution is adopted for solving.
By utilizing the soft measurement model for the efficiency parameters of the key parts of the heavy-duty gas turbine, the identification and analysis of the part efficiency are carried out on the actual operation data (1940 groups of data are screened through stable working conditions, and the load rate range of the gas turbine is 85% -100%) of a certain F-level gas turbine, and the comprehensive efficiency indexes or parameters of the gas turbine parts such as the efficiency of a gas compressor, the turbine efficiency, the outlet temperature of a combustion chamber and the like are obtained, as shown by solid lines in fig. 5-7; meanwhile, the gas turbine component performance parameter (gas turbine load factor of 100%) in the new state of the F-class gas turbine is shown in fig. 5 to 7 as a dotted line.
The main conclusions from the analysis of FIGS. 5 to 7 can be drawn as follows:
(1) compared with a new engine state, the efficiency of both a compressor and a turbine of a certain F-level gas turbine is degraded to different degrees. The reduction amplitude of the turbine efficiency is larger than that of the compressor efficiency, which is related to the operation mode of the unit with annual peak regulation operation and frequent start and stop, and the efficiency degradation degree of high-temperature components such as a turbine is more serious compared with that of cold-end components such as the compressor due to frequent start and stop; the variation trend of the parameters conforms to the actual operation condition of the unit.
(2) Compared with a new machine state, the outlet temperature of the combustion chamber of a certain F-grade gas turbine is reduced to a certain degree, which is related to the adjustment of operation control parameters in consideration of operation safety after the unit operates for many years;
(3) additionally, combustion reference temperature data (identified by delta) in the gas turbine control system, which is data derived by the control system, is given in FIG. 7. In the embodiment, the change rule of the outlet temperature of the combustion chamber calculated by the soft measurement model of the efficiency parameter of the key component of the gas turbine and the combustion reference temperature has better consistency, and the maximum relative error is 2.2%.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express one embodiment of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.

Claims (8)

1. A soft measurement method for efficiency parameters of key components of a heavy-duty gas turbine is characterized by comprising the following steps:
s1, establishing a compressor mathematical model, wherein the calculated output quantity is used as the known input quantity provided by the establishment of the combustion chamber mathematical model in the step S2;
s2, establishing a combustion chamber mathematical model, wherein the calculated output quantity of the combustion chamber mathematical model is used as the known input quantity provided by the establishment of the turbine mathematical model in the step S4;
s3, establishing a mathematical model for processing the turbine cooling air quantity;
s4, establishing a turbine mathematical model on the basis of the S3 turbine cooling air quantity processing mathematical model;
and S5, establishing an overall mathematical model for soft measurement of the performance parameters of the key parts of the heavy-duty gas turbine after calculating the connection between the input quantity and the output quantity in the steps S1, S2, S3 and S4.
2. The method for soft measurement of the efficiency parameters of the key components of the heavy-duty gas turbine as claimed in claim 1, wherein in step S1, the total inlet temperature T is determined when the mathematical model of the compressor is established2Total pressure p2Flow rate G2Air extraction flow and air extraction enthalpy value hbleed1、hbleed2、hbleed3Total pressure p at the outlet3As an input quantity, the isentropic efficiency eta of the compressorcAs an assumed value, the value is finally obtained by iterative calculation; calculating the output as the total temperature T of the outlet of the compressor3Outlet flow rate G3Gas compressor power consumption Nc；
The basic calculation formula of the compressor mathematical model is as follows:
(1) according to the formula (1) and the formula (2), the total temperature T of the inlet of the compressor is determined2Calculating the air inlet relative pressure ratio pi of the compressor2And specific enthalpy ha,T2；
lgπ2＝f1(T2) (1)
Figure FDA0003545769060000011
(2) Calculating the relative pressure ratio pi of the outlet of the compressor according to the formula (3) and the formula (4)3；
Figure FDA0003545769060000012
π3＝πc×π2 (4)
(3) Calculating the isentropic temperature T of the outlet of the compressor according to the formula (5)3S；
T3S＝f3[lg(π3)] (5)
(4) According to equation (6), from T3SCalculating the isentropic specific enthalpy h of air at the outlet of the compressora,T3S；
Figure FDA0003545769060000021
(5) According to the formula (7), calculating the actual specific enthalpy h of the air at the outlet of the compressora,T3；
Figure FDA0003545769060000022
(6) According to the formula (8), the air temperature at the outlet of the air compressor is obtained
Figure FDA0003545769060000023
(7) Calculating the compressor outlet air flow G according to the formula (9)3；
G3＝G2-Gbleed1-Gbleed2-Gbleed3 (9)
(8) Calculating the power consumption N of the compressor according to the formula (10)C；
NC＝G3h3-G2h2+Gbleed1hbleed1+Gbleed2hbleed2+Gbleed3hbleed3 (10)
In the above formulas (1), (2), (5) and (8), f1、f2、f3、f4Obtaining the air physical property by looking up a related air physical property parameter table;
in the above equations (1) to (10), the temperature is expressed in K, the specific enthalpy is expressed in kJ/kg, the pressure is expressed in kPa, the flow rate is expressed in kg/s, and the power is expressed in kW.
3. The method of claim 2, wherein in step S2, the combustor inlet air flow G is determined during the establishment of the combustor mathematical model31Air temperature T31As an input quantity; input quantity Q of combustion chamber energyfAs an assumed value, the value is finally obtained by iterative calculation; calculating the output as the flow G of the flue gas at the outlet of the combustion chamber4Temperature T4Composition and enthalpy h4；
The principle calculation formula of the combustion chamber model is as follows:
Figure FDA0003545769060000024
in the above formula:
Gfis the fuel flow, kg/s;
hfsensible enthalpy kJ/kg corresponding to the temperature of fuel entering a combustion chamber; the enthalpy display of the fuel adopts Landolt-
Figure FDA0003545769060000031
Calculating a polynomial;
hf0the sensible enthalpy of the fuel at 15 ℃ is kJ/kg;
Qlothe fuel low calorific value is kJ/kg at the temperature of 15 ℃ and normal pressure; the low calorific value of the fuel is obtained by calculating the components of natural gas according to the standard calculation method of natural gas calorific value, density, relative density and Wobbe index;
G31the inlet air quantity of the combustion chamber is kg/s; if no other flow rate is between the outlet of the compressor and the inlet of the combustion chamber, the inlet air quantity of the combustion chamber is equal to the outlet air quantity G of the compressor3；
h31Is the enthalpy value of the air at the inlet of the combustion chamber, kJ/kg; if no other flow and energy are in or out from the outlet of the compressor to the inlet of the combustion chamber, the enthalpy value of the air at the inlet of the combustion chamber is equal to the enthalpy value h of the air at the outlet of the compressor3；
p31The inlet air pressure, kPa, of the combustion chamber is equal to the outlet air pressure p of the compressor3；
h0airThe enthalpy value of air at a reference temperature (15 ℃) is kJ/kg;
Qfis a combustion chamberEnergy input, kW;
G4the calculation formula is that the combustion chamber outlet gas flow is kg/s:
G4＝G31+Gf (12)
h4is the enthalpy value of the fuel gas at the outlet of the combustion chamber, kJ/kg; the enthalpy value of the fuel gas is equal to the sum of products of the enthalpy values of all components of the fuel gas and the mass fractions of all the components of the fuel gas, the enthalpy values of all the components of the fuel gas can be calculated by looking up a related physical property parameter table, the enthalpy value of all the components of the fuel gas is calculated by adopting a fierce and shining formula in open literature, and the components of the fuel gas are calculated by a combustion chemical reaction equation;
h0gasis the enthalpy value of the fuel gas at the outlet of the combustion chamber at the reference temperature (15 ℃), kJ/kg;
p4is the combustion chamber outlet gas pressure, kPa.
4. The method for soft measurement of performance parameters of key components of heavy duty gas turbine as claimed in claim 3, wherein h is0airIs the enthalpy of air at a reference temperature, wherein the reference temperature is taken to be 15 ℃.
5. The method for soft measurement of the efficiency parameters of the key components of the heavy-duty gas turbine as claimed in claim 3, wherein in step S3, the cooling air flows are converted into the total equivalent flow according to the principle that the mass conservation and the work done in the turbine are equal, and the total equivalent flow consists of two parts: one part of the cooling air flows in from the inlet of the turbine stationary blade and then participates in work, and the work amount of the cooling air is equal to the work amount of the cooling air which flows in from each part; the other part flows in from the turbine outlet, does not participate in work, and only reduces the temperature of the gas at the turbine outlet, and the basic equation is as follows:
the calculation formula of the equivalent flow at the inlet of the turbine is as follows:
GTein＝GTin+Gein (13)
the turbine outlet flow is:
GTout＝GTin+Gein+Geout (14)
in the formula, GTinIs the turbine inlet gas flow, kg/s, if no other flow enters or exits between the combustion chamber outlet and the turbine inlet, the turbine inlet gas flow is equal to the combustion chamber outlet gas flow G4；
GeinThe equivalent cooling air flow rate of a turbine inlet participating in work is kg/s;
Geoutthe flow rate of equivalent cooling air at the outlet of the turbine which does not participate in work is kg/s;
GToutthe gas flow at the outlet of the turbine is kg/s;
on the basis of the formula calculation, the components, enthalpy value and temperature of the mixed flue gas can be calculated according to the basic principles of the mass and energy conservation in the flue gas mixing process.
6. The method for soft measurement of the efficiency parameters of the key components of the heavy-duty gas turbine as claimed in claim 5, wherein in step S4, a turbine model is established on the basis of the equivalent processing model of the turbine cooling air quantity, and the turbine inlet flue gas flow G is measured41Temperature T41Enthalpy value h41Pressure p41The flue gas pressure p at the turbine outlet5As an input quantity; efficiency of turbine etatAs an assumed value, the value is finally obtained by iterative calculation; calculating the flow G of the flue gas at the outlet of the turbine6Temperature T6Enthalpy value h6Work done by turbine NT；
The principle calculation formula of the turbine model is as follows:
(1) calculating the relative pressure ratio of each gas component at the inlet of the turbine:
Figure FDA0003545769060000051
in the formula, the lower subscript i represents each smoke component, f5According to the expression of the historical shining inquired in the open literature;
(2) calculating the gas relative pressure ratio of the turbine inlet;
Figure FDA0003545769060000052
in the formula: pig,T41Is the relative pressure ratio of the flue gas,
Figure FDA0003545769060000053
is a mole fraction;
(3) calculating the expansion ratio epsilon of the turbinetIsentropic relative pressure ratio pi of turbine outletg,T5S；
Figure FDA0003545769060000054
Figure FDA0003545769060000055
(4) Calculating turbine outlet isentropic temperature T5SAnd enthalpy value hg,T5S；
Figure FDA0003545769060000056
Figure FDA0003545769060000057
(5) Calculating the actual specific enthalpy h of the gas at the turbine outletg,T5；
Figure FDA0003545769060000058
(6) Calculating the actual temperature T of the turbine outlet5
Figure FDA0003545769060000059
(7) Computer transparentFlat work power NT
Figure FDA00035457690600000510
(8) Calculating the turbine outlet temperature T mixed with the cooling amount from the mass and energy balance5And enthalpy value hg,T6；
In the above equations (15) to (23), the temperature is expressed in K, the specific enthalpy is expressed in kJ/kg, the pressure is expressed in kPa, the flow rate is expressed in kg/s, and the power is expressed in kW.
7. The method for soft measurement of the performance parameters of the key components of the heavy duty gas turbine as claimed in claim 6, wherein in step S5, the input variables in the analysis model of the performance parameters of the key components of the gas turbine include: compressor inlet air temperature T2Pressure p2Flow rate G2Outlet pressure p3Turbine exhaust pressure p5(ii) a There are three unknowns as iteration parameters, namely: etac、Qf、ηtcAnd the final iteration results of the three unknown quantities enable the deviation of three output results of the outlet temperature of the gas compressor, the outlet temperature of the turbine and the output power of the gas turbine generator set from the measured value to be smaller than the set residual value.
8. The method for soft measurement of the performance parameters of the key components of the heavy duty gas turbine as claimed in claim 7, wherein in step S6, the system of equations has a unique solution because the unknowns and the number of equations are equal in the overall mathematical model for the performance parameter analysis of the key components of the heavy duty gas turbine, and the solution is performed by using a newton-raphson numerical iteration solution according to the least square principle.
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