A method and system for real-time calculation of gas turbine combustor outlet temperature

Abstract

The application belongs to the field of aero-engine design, and is a gas turbine combustor outlet temperature real-time calculation method and system. By analyzing the oil-gas ratio calculation formula, the corresponding relationship between the combustor outlet temperature and the currently measurable parameters during the whole machine test is obtained, the combustor outlet temperature is realized in real time online evaluation, the inlet temperature change and component performance of the high-pressure turbine component can be evaluated in real time; by combining the application of the power turbine inlet exhaust gas temperature test measurement value and the combustor outlet temperature calculation value in the control system, the problem of the delay of the single use of the power turbine inlet exhaust gas temperature limit in the transition state process of the current various gas turbines can be solved, the delay time of the transition state process over-temperature control can be obviously shortened, thereby the working life of the hot end component is improved, and the problems of inaccurate grasp of the existing low-emission gas turbine combustion mode switching point, poor generality of the calculation method and poor effectiveness are solved.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to a method and system for real-time calculation of the outlet temperature of a gas turbine combustor. Background Technology

[0002] The combustion chamber outlet temperature of a gas turbine is a crucial cycle parameter to consider during the design phase and a key performance parameter to monitor during system testing. To meet the requirements of long service life and high reliability, the combustion chamber outlet temperature needs to be limited to ensure that the gas temperature experienced by the hot-end components remains within the design range. However, due to the high combustion chamber outlet temperature T4 (which has reached as high as 1600℃ in foreign heavy-duty gas turbines), there is currently no effective means to directly monitor it for long periods during system testing. Typically, exhaust temperature monitoring is performed at the turbine inlet location (for single-rotor gas turbines, the turbine outlet temperature is generally monitored) where the gas temperature is lower. By setting an over-temperature protection logic for the turbine inlet in the control system, the combustion chamber outlet temperature can be indirectly controlled.

[0003] While existing solutions that monitor the exhaust temperature at the turbine inlet can meet the requirements for maximum operating limits and over-temperature protection of gas turbines, they also have some drawbacks, mainly including:

[0004] 1) The exhaust temperature time constant is large during the transition process, the monitoring response time is long, and it also takes a certain amount of time for the gas to be transferred from the high-pressure turbine to the power turbine inlet, resulting in poor real-time and accurate control of the combustion chamber outlet temperature limit;

[0005] 2) The exhaust temperature at the inlet of the power turbine is generally selected based on the average value measured by each temperature sensor for state limitation and over-temperature protection. When the temperature field suddenly becomes uneven due to other factors, the average value of the measured gas temperature may be too low, affecting the overall life and safety of the machine.

[0006] 3) When gas is suddenly released at the compressor outlet under high operating conditions (e.g., during load shedding), improper instantaneous control of the oil-gas ratio can cause a sudden rise in the combustion chamber outlet temperature. At this time, the exhaust temperature at the power turbine inlet may not be obvious, and the control system may not make an over-temperature limit in time, which will affect the life of the high-pressure turbine and the overall operational safety.

[0007] 4) In order to meet the emission control requirements of low-emission gas turbines, the combustion mode needs to be switched according to the combustion chamber outlet temperature. The current solution cannot obtain the combustion chamber outlet temperature online in real time during the test, which affects the emission control of the whole machine.

[0008] Therefore, how to more efficiently control the outlet temperature of the gas turbine combustion chamber is a problem that needs to be solved. Summary of the Invention

[0009] The purpose of this application is to provide a method and system for real-time calculation of gas turbine combustor outlet temperature, so as to solve the problems of poor real-time acquisition of gas turbine combustor outlet temperature, which affects the service life and safety of the whole machine.

[0010] The technical solution of this application is: a method for real-time calculation of the outlet temperature of a gas turbine combustion chamber, comprising:

[0011] The relationship between the air-fuel ratio and the enthalpy of the air at the combustion chamber inlet temperature was established based on the isothermal enthalpy difference method. Combustion chamber outlet temperature and air enthalpy Based on the corresponding relationship, the enthalpy value of the air at the combustion chamber inlet temperature is selected. Combustion chamber outlet temperature and air enthalpy The range of variation is then determined, and the correspondence between the inlet and outlet air enthalpy values ​​and the inlet and outlet temperatures is obtained based on the air-fuel isothermal enthalpy difference table. The combustion chamber outlet temperature is then obtained through iterative calculation. With combustion chamber inlet temperature Relationship with the change of oil-gas ratio f;

[0012] Combustion chamber outlet temperature In the relationship between inlet temperature and gas-fuel ratio, combustion efficiency and fuel calorific value correction factors C1 and model correction factor C are set respectively. 2模型 and experimental correction factor C 3试验 The relationship between the combustion chamber outlet temperature and the given equation is: In the formula, η b For combustion efficiency; H u It is a fuel with a low calorific value; fuel with a low calorific value H u Given a constant value, the combustion efficiency η is then obtained separately. b Combustion chamber inlet temperature Oil-to-gas ratio f, combustion efficiency and fuel calorific value correction factor C1, model correction factor C 2模型 and experimental correction factor C 3试验 The real-time combustion chamber outlet temperature under different conditions was obtained.

[0013] Receive the total temperature T at the inlet of the power turbine *48 Set limits for the total inlet temperature of the power turbine and the total outlet temperature of the combustion chamber, and perform logical judgments. If the total inlet temperature T of the power turbine is... *48 Meets the total temperature limit at the turbine inlet or the total temperature T at the combustion chamber outlet. *4 If the total temperature limit at the combustion chamber outlet is met, temperature control will be implemented.

[0014] Preferably, the combustion chamber outlet temperature With combustion chamber inlet temperature The calculation method for the relationship between the oil-gas ratio f and the change is as follows:

[0015] Assuming the fuel has a low calorific value H u and combustion efficiency η b These are fixed values, and then based on the selected combustion chamber inlet temperature and air enthalpy value. Combustion chamber outlet temperature and air enthalpy The variation range is set with step sizes, and the combustion chamber outlet temperature is obtained by iterative calculation according to the step size. With combustion chamber inlet temperature The relationship with the change of the oil-gas ratio f.

[0016] Preferably, the model correction coefficient C 2模型 The combustion chamber outlet temperature under intermediate operating conditions was calculated using a non-design point calculation program. Divide by the combustion chamber outlet temperature when increasing combustion efficiency and fuel calorific value correction factor C1. get.

[0017] Preferably, the test correction factor C3 is the combustion chamber outlet temperature evaluated under intermediate operating conditions based on the whole engine test results. Divide by the combustion chamber outlet temperature under intermediate operating conditions get.

[0018] Preferably, the air-fuel ratio f is determined by measuring the inlet air flow rate W1 of the low-pressure compressor, and the inlet air flow rate W of the combustion chamber is derived according to the ratio of bleed air and exhaust air under different conditions. 31 And the characteristics of the fuel regulating valve to obtain the fuel flow rate W f ; Calculate the combustion chamber inlet air flow rate W3 and fuel flow rate W f The ratio of oil to gas is called the oil-to-gas ratio f.

[0019] Preferably, the combustion efficiency η b The setting method is as follows: first, check the air flow rate W at the combustion chamber inlet. 31 The combustion load Ω is calculated using the following formula:

[0020]

[0021] In the formula, V is the combustion chamber volume, and P3 is the compressor outlet pressure;

[0022] Then, based on the combined combustion load Ω and combustion design efficiency η des Calculate combustion efficiency η b The formula is:

[0023]

[0024] As one specific implementation, a real-time calculation system for the outlet temperature of a gas turbine combustion chamber includes:

[0025] The testing system is used to arrange test sensors at various sections of the gas turbine to collect data on the low-pressure compressor inlet air flow rate W1 and the combustion chamber inlet temperature. Compressor outlet pressure P3, high-pressure rotor speed n2, fuel flow rate W f Total temperature at the inlet of the power turbine (T) * 48 The rotational speed n3 of the power turbine rotor is converted and transmitted to the control system and combustion efficiency calculation module;

[0026] The combustion efficiency calculation module is used to calculate the combustion efficiency and transmit the combustion efficiency to the combustion chamber outlet total temperature calculation module;

[0027] The combustion chamber outlet total temperature calculation module is used to calculate the combustion chamber outlet temperature in real time.

[0028] The control system receives the total temperature T at the power turbine inlet. *48 and combustion chamber outlet temperature An internal temperature protection and limiting module is installed, which sets limits for the total temperature at the turbine inlet and the total temperature at the combustion chamber outlet. This module is used for logical judgment; if the total temperature at the turbine inlet T... *48 Meets the total temperature limit at the turbine inlet or the total temperature T at the combustion chamber outlet. *4 If the total temperature limit at the combustion chamber outlet is met, the control system will perform temperature control.

[0029] This application discloses a method and system for real-time calculation of the combustion chamber outlet temperature of a gas turbine. By analyzing the oil-gas ratio calculation formula, the correspondence between the combustion chamber outlet temperature and the measurable parameters during current whole-machine testing is obtained, enabling real-time online evaluation of the combustion chamber outlet temperature. This allows for real-time assessment of the inlet temperature changes and component performance of the high-pressure turbine components. By combining the experimental measurement value of the power turbine inlet exhaust temperature and the calculated value of the combustion chamber outlet temperature in the control system, the method solves the problem of delay caused by the current method of using only the power turbine inlet exhaust temperature for temperature limiting in the transient process of various types of gas turbines. This significantly shortens the delay time of over-temperature control in the transient process, thereby improving the service life of hot-end components. Attached Figure Description

[0030] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0031] Figure 1 This is a schematic diagram of the overall process of this application;

[0032] Figure 2This is a schematic diagram showing the relationship between the air-fuel ratio and the inlet and outlet temperatures of the combustion chamber in this application.

[0033] Figure 3 This is a schematic diagram of the temperature control system of this application. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] A method for real-time calculation of gas turbine combustion chamber outlet temperature, such as... Figure 1 As shown, it includes the following steps:

[0036] Step S100: Establish the air-fuel ratio and the air enthalpy value at the combustion chamber inlet temperature based on the isothermal enthalpy difference method. Combustion chamber outlet temperature and air enthalpy The corresponding relationship; the isothermal enthalpy difference is the enthalpy difference between the pure gas produced by the complete combustion of 1kg fuel oil and L0kg air and L0kg pure air at the same temperature. The calculation is relatively simple, as shown in formula (1). The enthalpy value and isothermal enthalpy difference at different temperatures can be found in Table 1.

[0037]

[0038] In the formula η b For combustion efficiency; H u It is a fuel with a low calorific value; for The isothermal enthalpy difference at each time point can be found in Table 1.

[0039] Table 1. Isothermal Enthalpy Difference between Air and Gas

[0040]

[0041]

[0042]

[0043]

[0044] Select the air enthalpy value at the combustion chamber inlet temperature Combustion chamber outlet temperature and air enthalpy The range of variation is then determined, and the correspondence between the inlet and outlet air enthalpy values ​​and the inlet and outlet temperatures is obtained based on the air-fuel isothermal enthalpy difference table. The combustion chamber outlet temperature is then obtained through iterative calculation. With combustion chamber inlet temperature The relationship with the change of the oil-gas ratio f.

[0045] Preferably, the combustion chamber outlet temperature With combustion chamber inlet temperature The specific calculation method for the relationship between the oil-gas ratio f and the change is as follows:

[0046] Assuming the fuel has a low calorific value H u and combustion efficiency η b These are fixed values, and then based on the selected combustion chamber inlet temperature and air enthalpy value. Combustion chamber outlet temperature and air enthalpy The variation range is set with step sizes, and the combustion chamber outlet temperature is obtained by iterative calculation according to the step size. With combustion chamber inlet temperature The relationship with the change of the oil-gas ratio f.

[0047] In one specific embodiment, the method is designed as follows:

[0048] 1) Assume η b H is 0.97. u It is 42900 kJ / kg;

[0049] 2) Select The range is [300 900]K, the step size is 100K, and the selected range is [300 900]K. The range is [1000 1800]K, with a step size of 200K;

[0050] 3) Calculate according to formula (1) respectively For 300K, The curve showing the change over [1000 1800] K; calculate For 400K, The curve showing the change over [1000 1800] K...;

[0051] 4) List the above data in Table 2:

[0052] Table 2. Calculation of Combustion Chamber Inlet and Outlet Temperatures and Air-fuel Ratio

[0053]

[0054]

[0055] 5) Plot the relationship between the air-fuel ratio f and the combustion chamber inlet temperature. Combustion chamber outlet temperature Relationship curves, such as Figure 2 As shown, the curves from top to bottom represent the relationship between 300K and 900K.

[0056] 6) To Figure 2 Multivariate fitting calculations were performed on the data to obtain the relationship between the air-fuel ratio f and the combustion chamber inlet temperature. Combustion chamber outlet temperature The calculation formula is shown in formula (2).

[0057]

[0058] 7) Add a combustion efficiency and fuel calorific value correction coefficient C1 to formula (2) to convert it into actual combustion efficiency and calorific value, see formula (3), and then get the result after adding the correction coefficient, see formula (4).

[0059]

[0060]

[0061] 8) In formula (4), C1, f, Treat it as the independent variable. Identify the dependent variable and solve the equation to obtain the result. The calculation formula is shown in (5);

[0062]

[0063] 9) For a specific type of gas turbine, to improve the calculation accuracy, a model correction coefficient can be added to formula (5), denoted as C. 2模型 The value is generally taken as 0.985 to 1, in order to calculate C. 2模型 The specific model can be calculated based on the intermediate operating conditions using the non-design point calculation program. Divide it by the formula (5) C can then be calculated. 2模型 Increase the model correction coefficient C. 2模型 After The calculation formula is shown in formula (6).

[0064]

[0065] 10) After a certain type of gas turbine has completed its overall performance evaluation, in order to improve the calculation accuracy, an experimental correction factor is added, denoted as C. 3试验 The value is generally taken as 0.99 to 1, in order to calculate C. 3试验 It can be evaluated based on the intermediate operating conditions of the whole machine test results. Divide it by the formula (6) C can then be calculated. 3试验 Increase the experimental correction factor C. 3试验 After The calculation formula is shown in formula (7).

[0066]

[0067] By establishing the relationship between the combustion chamber outlet temperature and the air-fuel ratio and combustion chamber inlet temperature, the combustion chamber outlet temperature can be calculated without directly collecting the data. Only the air-fuel ratio and combustion chamber inlet temperature are needed. Since the air-fuel ratio and combustion chamber inlet temperature can be accurately obtained, the combustion chamber outlet temperature value can be obtained efficiently. This is achieved by setting correction coefficients C1 for combustion efficiency and fuel calorific value, and model correction coefficients C... 2模型 and experimental correction factor C 3试验 The calculated combustion chamber outlet temperature value is corrected to obtain a more accurate combustion chamber outlet temperature value.

[0068] In actual data acquisition, the combustion chamber inlet temperature is equal to the compressor outlet temperature. Therefore, the combustion chamber inlet temperature can be obtained by collecting the compressor outlet temperature, which is more convenient and efficient.

[0069] Step S200, at the combustion chamber outlet temperature In the relationship between inlet temperature and gas-fuel ratio, combustion efficiency and fuel calorific value correction factors C1 and model correction factor C are set respectively. 2模型 and experimental correction factor C 3试验 The relationship between the combustion chamber outlet temperature and the given equation is:

[0070]

[0071] Low calorific value fuel H u Given a constant value, the combustion efficiency η is then obtained separately. b Combustion chamber inlet temperature Oil-to-gas ratio f, combustion efficiency and fuel calorific value correction factor C1, model correction factor C 2模型 and experimental correction factor C 3试验 The real-time combustion chamber outlet temperature under different conditions was obtained.

[0072] The parameters are obtained as follows:

[0073] 1) Compressor outlet total temperature

[0074] That is, the combustion chamber inlet temperature, which can be directly measured by placing temperature measuring points at the outlet temperature of the high-pressure compressor.

[0075] 2) Oil-gas ratio f

[0076] Set up flow measurement points on the low-pressure compressor to measure the inlet air flow rate W1 of the low-pressure compressor. Determine the inlet air flow rate W of the combustion chamber based on the bleed air and exhaust air ratios under different conditions. 31 The fuel flow rate W is obtained based on the characteristics of the fuel regulating valve.f Thus, fuel flow rate W f (kg / s) and W 31 The ratio of (kg / s) is the oil-gas ratio f.

[0077] 3) Combustion efficiency η b

[0078] First, calculate the combustion load Ω according to formula (8), where W 31 The combustion chamber inlet air flow rate (kg / s) can be obtained from 2) above. The compressor outlet total temperature (K) can be obtained from 1) above, and V is the combustion chamber volume (m³). 3 The P3 compressor outlet pressure can be determined when the combustion chamber design is completed, based on the following reference. Figure 3 Measured. Formula (9) is the combustion efficiency, where η des For combustion design efficiency, Ω can be determined when the combustion chamber design is completed. des The combustion load under design conditions is determined in the same way as Ω. a is the combustion chamber load constant, which is taken as 1 to 1.9, and is generally taken as 1.6. The specific value can be determined according to the slow-speed combustion efficiency.

[0079]

[0080]

[0081] 4) Correction factor C1

[0082] The correction factor C1 is given by formula (3), where the combustion efficiency η b See 3) above, fuel with low calorific value H u It is a constant, which can be determined once a certain fuel is used.

[0083] 5)C 2模型

[0084] C 2模型 The correction factor for the calculation model is generally taken as 0.985 to 1. For specific models, the intermediate working condition can be calculated using the non-design point calculation program. Its calculation with formula (5) The ratio is C. 2模型 .

[0085] 6)C 3试验

[0086] C 3试验 The correction factor is typically taken as 0.99 to 1, used to calculate C. 3试验 It can be evaluated based on the intermediate operating conditions of the whole machine test results. Its calculation with formula (6) The ratio is C.3试验 .

[0087] Step S300, receive the total temperature T at the power turbine inlet. *48 Set limits for the total inlet temperature of the power turbine and the total outlet temperature of the combustion chamber, and perform logical judgments. If the total inlet temperature T of the power turbine is... *48 Meets the total temperature limit at the turbine inlet or the total temperature T at the combustion chamber outlet. *4 If the total temperature limit at the combustion chamber outlet is met, temperature control will be implemented.

[0088] This application analyzes the oil-gas ratio calculation formula to obtain the correspondence between the combustion chamber outlet temperature and the measurable parameters during current whole-machine testing, thereby enabling real-time online evaluation of the combustion chamber outlet temperature and real-time assessment of the inlet temperature changes and component performance of the high-pressure turbine components.

[0089] By combining the experimentally measured exhaust temperature at the turbine inlet and the calculated exhaust temperature at the combustion chamber outlet in the control system, the problem of delay inherent in the current method of using only the turbine inlet exhaust temperature for temperature limiting during the transient process in various types of gas turbines can be solved. Furthermore, it addresses the issue of uneven exhaust temperature field at the turbine inlet caused by sudden conditions or changes in the outlet airflow angle. In such cases, the average measured exhaust temperature will be lower than the actual value, and continued control based on the average value would negatively impact the overall lifespan and safety of the turbine. This significantly shortens the delay time for over-temperature control during the transient process, thereby improving the service life of hot-end components.

[0090] The technical problems that can be solved also include the problem of switching combustion modes for low emissions. Since this application is based on a theoretical formula to derive the calculation relationship of combustion chamber outlet temperature, and the formula is easy to apply, has high versatility and calculation accuracy, and is applicable to different models and units of gas turbines, by obtaining an accurate combustion chamber outlet temperature, it can solve the problems of inaccurate determination of combustion mode switching points, poor versatility of calculation methods, and poor effectiveness of existing low-emission gas turbines, thereby helping to reduce exhaust pollutants.

[0091] As one specific implementation, it also includes a real-time calculation system for the gas turbine combustion chamber outlet temperature, such as... Figure 3 As shown, it specifically includes:

[0092] The testing system is used to arrange test sensors at various sections of the gas turbine to collect data on the low-pressure compressor inlet air flow rate W1 and the combustion chamber inlet temperature. Compressor outlet pressure P3, high-pressure rotor speed n2, fuel flow rate W f Total temperature at the inlet of the power turbine (T) * 48 The rotational speed n3 of the power turbine rotor is converted and transmitted to the control system and combustion efficiency calculation module;

[0093] The combustion efficiency calculation module is used to calculate the combustion efficiency and transmit the combustion efficiency to the combustion chamber outlet total temperature calculation module;

[0094] The combustion chamber outlet total temperature calculation module is used to calculate the combustion chamber outlet temperature in real time.

[0095] The control system receives the total temperature T at the power turbine inlet. *48 and combustion chamber outlet temperature An internal temperature protection and limiting module is installed, which sets limits for the total temperature at the turbine inlet and the total temperature at the combustion chamber outlet. This module is used for logical judgment; if the total temperature at the turbine inlet T... *48 Meets the total temperature limit at the turbine inlet or the total temperature T at the combustion chamber outlet. *4 If the total temperature limit at the combustion chamber outlet is met, the control system will perform temperature control.

[0096] Through the cooperation of various modules, efficient temperature control of the gas turbine can be achieved.

[0097] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change.

[0098] Secondly: The accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0099] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for real-time calculation of the outlet temperature of a gas turbine combustion chamber, characterized in that, include: The relationship between the air-fuel ratio and the enthalpy of the air at the combustion chamber inlet temperature was established based on the isothermal enthalpy difference method. Combustion chamber outlet temperature and air enthalpy Based on the corresponding relationship, the enthalpy value of the air at the combustion chamber inlet temperature is selected. Combustion chamber outlet temperature and air enthalpy The range of variation is then determined, and the correspondence between the inlet and outlet air enthalpy values ​​and the inlet and outlet temperatures is obtained based on the air-fuel isothermal enthalpy difference table. The combustion chamber outlet temperature is then obtained through iterative calculation. With combustion chamber inlet temperature Compared to oil and gas The changing relationship; Combustion chamber outlet temperature In the relationship between inlet temperature and gas-fuel ratio, combustion efficiency and fuel calorific value correction factors C1 and model correction factor C are set respectively. 2模型 and experimental correction factor C 3试验 The relationship between the combustion chamber outlet temperature and the given equation is: In the formula, For combustion efficiency; Low calorific value fuel; low calorific value fuel Given a constant value, the combustion efficiency is then obtained separately. Combustion chamber inlet temperature Oil-to-gas ratio Combustion efficiency and fuel calorific value correction factor C1, model correction factor C 2模型 and experimental correction factor C 3试验 The real-time combustion chamber outlet temperature under different conditions was obtained. ; Receive the total temperature T at the inlet of the power turbine * 48 Set limits for the total inlet temperature of the power turbine and the total outlet temperature of the combustion chamber, and perform logical judgments. If the total inlet temperature T of the power turbine is... * 48 Meets the total temperature limit at the turbine inlet or the total temperature T at the combustion chamber outlet. * 4. If the total temperature limit at the combustion chamber outlet is met, then temperature control will be implemented; The combustion chamber outlet temperature With combustion chamber inlet temperature Compared to oil and gas The calculation method for the relationship of change is as follows: Assuming the fuel has a low calorific value and combustion efficiency These are fixed values, and then based on the selected combustion chamber inlet temperature and air enthalpy value. Combustion chamber outlet temperature and air enthalpy The variation range is set with step sizes, and the combustion chamber outlet temperature is obtained by iterative calculation according to the step size. With combustion chamber inlet temperature Compared to oil and gas The changing relationship; The model correction coefficient C 2模型 The combustion chamber outlet temperature under intermediate operating conditions was calculated using a non-design point calculation program. And divided by the combustion chamber outlet temperature when increasing combustion efficiency and fuel calorific value correction factor C1. get; The test correction factor C 3试验 Combustion chamber outlet temperature evaluated under intermediate operating conditions based on whole-engine test results. Divide by the combustion chamber outlet temperature under intermediate operating conditions get; The combustion efficiency The setting method is as follows: first, check the air flow rate W at the combustion chamber inlet. 31 Calculate the combustion load The calculation formula is: ； In the formula, P3 is the combustion chamber volume, and P3 is the compressor outlet pressure. Then, based on the combined combustion load and combustion design efficiency Calculate combustion efficiency The formula is: ； in, For combustion design load, This is the combustion chamber load constant.

2. The method for real-time calculation of gas turbine combustion chamber outlet temperature as described in claim 1, characterized in that: The oil-gas ratio By measuring the inlet air flow rate W1 of the low-pressure compressor, the inlet air flow rate W of the combustion chamber can be determined based on the bleed air and exhaust air ratios under different conditions. 31 And the characteristics of the fuel regulating valve to obtain the fuel flow rate W f ; Calculate the inlet air flow rate W of the combustion chamber. 31 With fuel flow W f The ratio is the oil-gas ratio. .

3. A real-time calculation system for the outlet temperature of a gas turbine combustion chamber, employing the method described in any one of claims 1-2, characterized in that, include: The testing system is used to arrange test sensors at various sections of the gas turbine to collect data on the low-pressure compressor inlet air flow rate W1 and the combustion chamber inlet temperature. Compressor outlet pressure P3, high-pressure rotor speed n2, fuel flow rate W f Total temperature at the inlet of the power turbine (T) * 48 The rotational speed n3 of the power turbine rotor is converted and transmitted to the control system and combustion efficiency calculation module; The combustion efficiency calculation module is used to calculate the combustion efficiency and transmit the combustion efficiency to the combustion chamber outlet total temperature calculation module; The combustion chamber outlet total temperature calculation module is used to calculate the combustion chamber outlet temperature in real time. ; The control system receives the total temperature T at the power turbine inlet. * 48 and combustion chamber outlet temperature It is internally equipped with a temperature protection and limiting module, which sets limits for the total temperature at the turbine inlet and the total temperature at the combustion chamber outlet. This module is used for logical judgment; if the total temperature at the turbine inlet T... * 48 Meets the total temperature limit at the turbine inlet or the total temperature T at the combustion chamber outlet. * 4. If the total temperature limit at the combustion chamber outlet is met, the control system will perform temperature control.

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