WO2026025720A1 - 一种燃气轮机燃烧室出口温度优化调整方法及系统 - Google Patents

一种燃气轮机燃烧室出口温度优化调整方法及系统

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Publication number
WO2026025720A1
WO2026025720A1 PCT/CN2024/132242 CN2024132242W WO2026025720A1 WO 2026025720 A1 WO2026025720 A1 WO 2026025720A1 CN 2024132242 W CN2024132242 W CN 2024132242W WO 2026025720 A1 WO2026025720 A1 WO 2026025720A1
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Prior art keywords
gas turbine
combustion chamber
gas
combustion
turbine
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Pending
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PCT/CN2024/132242
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English (en)
French (fr)
Inventor
肖俊峰
李晓丰
王玮
王峰
高松
夏家兴
郭菡
李乐
于倩倩
李丹
郑俊辉
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Xian Thermal Power Research Institute Co Ltd
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Xian Thermal Power Research Institute Co Ltd
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Publication of WO2026025720A1 publication Critical patent/WO2026025720A1/zh
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Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B13/00—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion
    • G05B13/02—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
    • G05B13/04—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
    • G05B13/042—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators in which a parameter or coefficient is automatically adjusted to optimise the performance

Definitions

  • This invention relates to the field of gas turbine technology, and in particular to a method and system for optimizing and adjusting the outlet temperature of a gas turbine combustion chamber.
  • a gas turbine is a highly efficient thermal energy conversion device that generates high-temperature, high-pressure gas by burning fuel, which then drives a turbine to rotate, converting the gas into mechanical energy.
  • the combustion chamber outlet temperature is a critical parameter in the operation of a gas turbine, significantly impacting the overall system efficiency, safety, lifespan, and pollutant emissions.
  • a higher combustion chamber outlet temperature means more thermal energy can be converted into mechanical energy, thus improving the overall system's energy efficiency.
  • this process is not without limitations, as excessively high temperatures can increase thermal stress on materials, affecting the gas turbine's lifespan.
  • the combustion chamber and turbine components of a gas turbine require materials capable of withstanding high temperatures, such as nickel-based alloys.
  • Controlling the combustion chamber outlet temperature is crucial to ensuring these high-temperature components do not exceed their material heat resistance limits. Furthermore, a uniform distribution of the combustion chamber outlet temperature reduces thermal stress and extends component lifespan. In terms of emissions control, while a higher combustion chamber outlet temperature can promote more complete combustion and reduce the emission of unburned hydrocarbons and carbon dioxide, it conversely increases nitrogen oxide (NOx) emissions because high temperatures promote the reaction of nitrogen and oxygen in the air, generating more NOx.
  • NOx nitrogen oxide
  • controlling the combustion chamber outlet temperature of a gas turbine is crucial for ensuring the high efficiency, safety, environmental friendliness, and economy of the entire system.
  • Precise control of the combustion chamber outlet temperature is essential for guaranteeing the safe operation of the gas turbine.
  • the present invention provides a method for optimizing and adjusting the combustion chamber outlet temperature of a gas turbine, which can solve the problem that traditional gas turbines cannot accurately control the combustion chamber outlet temperature.
  • this invention provides the following technical solution: a method for optimizing and adjusting the outlet temperature of a gas turbine combustor, comprising: establishing a three-dimensional combustion calculation numerical model of the combustor; calculating the flow field characteristic parameters of the combustor under typical load conditions; obtaining the specific heat ratio of the gas at the combustor outlet and the total pressure loss coefficient of the combustor under typical load conditions; fitting and obtaining calculation formulas for the specific heat ratio of the gas and the total pressure loss coefficient of the combustor; establishing a calculation formula for the turbine inlet temperature; and feeding back the calculated turbine inlet temperature and the combustion pressure pulsation data obtained from the gas turbine generator set operating data to the gas turbine control system to adjust the IGV opening and fuel flow rate.
  • the establishment of a three-dimensional combustion numerical model of the combustor includes: using Thermoflow power plant thermal balance analysis software, establishing a Thermoflow gas turbine thermal balance calculation model for the gas turbine model used in the gas-fired power plant; setting the boundary parameters of the calculation model based on historical operating data of the gas turbine; verifying the accuracy of the calculation model using historical operating data of the gas turbine; calculating the inlet and outlet boundary parameters of the combustor from start-up to full-load operation of the gas turbine using the verified Thermoflow gas turbine thermal balance calculation model; then establishing a three-dimensional combustion numerical model of the combustor using fluid numerical simulation software; and setting the inlet and outlet boundary conditions of the combustion numerical model based on the boundary parameters obtained from the Thermoflow gas turbine thermal balance calculation model.
  • the combustion chamber flow field characteristic parameters under typical load conditions include the calculated gas pressure field, temperature field, and velocity field in the gas turbine combustion chamber under typical loads of 50%, 60%, 70%, 80%, 90%, and 100%, respectively.
  • the total pressure loss coefficient of the combustor is expressed as follows: Analysis yields the total inlet pressure P * 2 and total outlet pressure P * 3 of the gas turbine combustor under typical loads of 50%, 60%, 70%, 80%, 90%, and 100%, expressed as follows:
  • ⁇ c represents the total pressure loss coefficient of the combustion chamber.
  • the method for fitting the calculation formulas for the specific heat ratio of the combustion gas and the total pressure loss coefficient of the combustor includes using a curve fitting method. This involves using the calculated total pressure loss coefficient of the combustor and the specific heat ratio of the combustion gas at the combustor outlet, with the relative load as the independent variable, to fit and obtain the calculation formulas for the total pressure loss coefficient of the combustor and the specific heat ratio of the combustion gas at the combustor outlet, respectively.
  • w is the independent variable relative load
  • f(w) is the calculation function of the total pressure loss coefficient of the combustion chamber obtained by fitting
  • g(w) is the calculation function of the specific heat ratio of the combustion chamber outlet gas obtained by fitting.
  • the establishment of the turbine inlet temperature calculation formula includes utilizing the energy change characteristics of the gas energy as it expands and does work within the turbine, to establish the turbine inlet temperature T3 calculation formula as follows:
  • T4 is the gas turbine exhaust temperature
  • P2 is the gas turbine compressor exhaust pressure
  • P4 is the gas turbine exhaust pressure
  • the turbine exhaust temperature T4 , the gas turbine compressor exhaust pressure P2 , and the gas turbine exhaust pressure P4 are obtained from the gas turbine generator set operating data. Combined with the calculation formulas for the total pressure loss coefficient ⁇ c of the combustion chamber and the specific heat ratio ⁇ of the combustion chamber outlet gas, and the calculation formula for the turbine inlet temperature, the turbine inlet temperature T3 is calculated.
  • the calculated turbine inlet temperature T ⁇ sub>3 ⁇ /sub> and the combustion pressure pulsation data obtained from the gas turbine generator set operating data are fed back to the gas turbine control system.
  • the gas turbine control system makes the following judgments: when T ⁇ sub>3r ⁇ /sub> - T ⁇ sub> 3 ⁇ /sub> ⁇ ⁇ and the combustion pressure pulsation value is less than the alarm value, it outputs a command to decrease the IGV opening by 1%; when T ⁇ sub>3r ⁇ /sub> - T ⁇ sub> 3 ⁇ /sub> ⁇ ⁇ , but the combustion pressure pulsation value is greater than the alarm value, it outputs a command to increase the fuel flow rate by 0.5%; when T ⁇ sub>3r ⁇ /sub> - T ⁇ sub> 3 ⁇ /sub> ⁇ 0, it outputs a command to increase the IGV opening by 1%.
  • T3r is the turbine inlet temperature limit set in the gas turbine control system
  • ⁇ is the turbine inlet temperature safety threshold set in the gas turbine control system.
  • the adjustment of IGV opening and fuel flow includes: real-time calculation of turbine inlet temperature, and in conjunction with changes in combustion pressure pulsation data, instantaneous generation of new IGV and fuel flow control commands until the turbine inlet temperature T3 first exceeds the value of T3r - ⁇ , so that the turbine inlet temperature T3 approaches the turbine inlet temperature limit T3r under safe conditions, thereby improving the gas turbine power generation thermal efficiency.
  • Another objective of this invention is to provide a gas turbine combustor outlet temperature optimization and adjustment system that improves combustion efficiency, optimizes combustor design, ensures accurate understanding of flow conditions within the combustor, adjusts fuel ratio, reduces pressure loss, improves energy utilization efficiency, enables prediction and optimization of gas turbine operating parameters, enhances system stability, ensures reasonable turbine inlet temperature, and achieves efficient and stable operation of the gas turbine.
  • the gas turbine combustor outlet temperature optimization and adjustment system of the present invention includes: a combustion model establishment module, a flow parameter calculation module, a gas specific heat ratio and combustor pressure loss calculation module, a gas specific heat ratio and combustor pressure loss fitting module, a turbine inlet temperature calculation module, and a data feedback and adjustment module.
  • the combustion model establishment module establishes a three-dimensional numerical model for combustion calculation in the combustion chamber.
  • the flow parameter calculation module calculates the combustion chamber flow field characteristic parameters under typical load conditions.
  • the specific heat ratio of the gas and the pressure loss calculation module of the combustion chamber obtain the specific heat ratio of the gas at the outlet of the combustion chamber and the total pressure loss coefficient of the combustion chamber under typical load conditions.
  • the specific heat ratio of the gas and the pressure loss fitting module of the combustion chamber are used to fit and obtain the calculation formulas for the specific heat ratio of the gas and the total pressure loss coefficient of the combustion chamber.
  • the turbine inlet temperature calculation module establishes a turbine inlet temperature calculation formula and calculates the turbine inlet temperature.
  • the data feedback and adjustment module feeds back the calculated turbine inlet temperature and the combustion pressure pulsation data obtained from the gas turbine generator set operation data to the gas turbine control system; and adjusts the IGV opening and fuel flow.
  • a computer device includes a memory and a processor, the memory storing a computer program, characterized in that the processor executes the computer program to implement the steps of any one of the methods in the method for optimizing and adjusting the outlet temperature of a gas turbine combustion chamber.
  • a computer-readable storage medium having a computer program stored thereon, characterized in that, when the computer program is executed by a processor, it implements the steps of any one of the methods in a gas turbine combustion chamber outlet temperature optimization adjustment method.
  • the beneficial effects of this invention are as follows:
  • the cycle thermal efficiency of a gas turbine is generally positively correlated with the turbine inlet temperature. Increasing the turbine inlet temperature can improve the cycle thermal efficiency. However, since the turbine inlet temperature of a gas turbine is relatively high, it cannot be directly measured.
  • This solution calculates the turbine inlet temperature based on the turbine exhaust temperature, compares and analyzes the distance between the calculated turbine inlet temperature and the turbine inlet temperature limit, and then decreases or increases the IGV opening in real time to control the airflow entering the gas turbine. When the IGV opening is decreased, the airflow entering the gas turbine decreases, and the turbine inlet temperature increases, thereby improving the cycle thermal efficiency of the gas turbine. When the IGV opening is increased, the airflow entering the gas turbine increases, and the turbine inlet temperature decreases, preventing turbine blade burn-out and improving the operational safety of the gas turbine.
  • Figure 1 is a flowchart of a method for optimizing and adjusting the outlet temperature of a gas turbine combustion chamber according to an embodiment of the present invention.
  • Figure 2 is a three-dimensional solid model of the combustion chamber of a gas turbine combustion chamber outlet temperature optimization and adjustment method provided in an embodiment of the present invention.
  • Figure 3 shows a three-dimensional numerical model of the combustion chamber of a gas turbine combustion chamber, according to an embodiment of the present invention, which provides a method for optimizing and adjusting the outlet temperature of the combustion chamber.
  • Figure 4 shows the Thermoflow thermal balance calculation results of a gas turbine under 100% typical load for a gas turbine combustion chamber outlet temperature optimization adjustment method provided by an embodiment of the present invention.
  • Figure 5 shows the pressure field results of the central section of the combustion chamber under 100% typical load for a gas turbine combustion chamber outlet temperature optimization adjustment method provided in an embodiment of the present invention.
  • Figure 6 shows the temperature field results of the central section of the combustion chamber under 100% typical load for a gas turbine combustion chamber outlet temperature optimization adjustment method provided in an embodiment of the present invention.
  • Figure 7 shows the velocity field results of the central section of the combustion chamber under 100% typical load for a gas turbine combustion chamber outlet temperature optimization adjustment method provided in an embodiment of the present invention.
  • Example 1 referring to Figure 1, is the first embodiment of the present invention.
  • This embodiment provides a method for optimizing and adjusting the outlet temperature of a gas turbine combustion chamber, including: the method uses the combustion chamber inlet pressure P2 and the combustion chamber pressure loss coefficient to calculate the turbine inlet pressure, and then calculates the turbine inlet temperature T3 .
  • the method is simple, feasible, and highly efficient.
  • This solution retrieves operating parameters such as combustion chamber inlet pressure P2 , turbine exhaust pressure P4 , and turbine exhaust temperature T4 from the real-time database of the gas turbine generator set. It can then calculate the turbine inlet temperature in real time and compare it with the gas turbine inlet temperature limit. Based on the distance between the comparison result and the safe threshold ⁇ of the turbine inlet temperature, the IGV opening and fuel flow rate are adjusted in real time to increase the gas turbine inlet temperature under partial load, thereby improving the gas turbine cycle thermal efficiency.
  • operating parameters such as combustion chamber inlet pressure P2 , turbine exhaust pressure P4 , and turbine exhaust temperature T4 from the real-time database of the gas turbine generator set. It can then calculate the turbine inlet temperature in real time and compare it with the gas turbine inlet temperature limit. Based on the distance between the comparison result and the safe threshold ⁇ of the turbine inlet temperature, the IGV opening and fuel flow rate are adjusted in real time to increase the gas turbine inlet temperature under partial load, thereby improving the gas turbine cycle thermal efficiency.
  • This solution overcomes the limitation that the turbine inlet temperature of a gas turbine cannot be directly measured, enabling more precise control of the turbine inlet temperature. Under low load conditions, it can improve the thermal efficiency of the gas turbine cycle, and under high load conditions, it can increase the IGV opening, increase the airflow into the gas turbine, reduce the turbine inlet temperature, prevent turbine blade burn-out, and improve the operational safety of the gas turbine.
  • Thermoflow power plant thermal balance analysis software was used to establish a Thermoflow gas turbine thermal balance calculation model for the gas turbine model used in the gas-fired power plant.
  • the boundary parameters of the calculation model were set based on the historical operating data of the gas turbine, and the accuracy of the calculation model was verified using the historical operating data of the gas turbine.
  • the verified Thermoflow gas turbine thermal balance calculation model was used to calculate the combustion chamber inlet and outlet boundary parameters of the gas turbine from start-up to full-load operation. Considering that pollutant emissions may exceed standards when the gas turbine is running at low load, gas turbine generator sets generally operate within the 50% to 100% load range. Therefore, the above method is mainly used to calculate the boundary parameters such as the inlet air and fuel mass flow rate, temperature, and outlet pressure of the gas turbine combustor under typical loads of 50%, 60%, 70%, 80%, 90%, and 100%. Typical loads can be selected and determined based on the frequently operating load points of the gas turbine power plant.
  • the inlet and outlet boundary parameters of the combustor obtained in step 2 are set to calculate the gas pressure field, temperature field, and velocity field inside the gas turbine combustor under typical loads of 50%, 60%, 70%, 80%, 90%, and 100%.
  • step 3 Based on the calculation results in step 2, analyze and obtain the total inlet pressure P2 *, total outlet pressure P3 *, and specific heat ratio ⁇ of the gas turbine combustor under typical loads of 50%, 60%, 70%, 80%, 90%, and 100%. Then, use the formula... The total pressure loss coefficient ⁇ c of the combustion chamber is calculated.
  • the total pressure loss coefficient ⁇ c of the combustion chamber and the specific heat ratio of the combustion chamber outlet gas ⁇ obtained in step 3 are used as independent variables to fit the calculation formulas of the total pressure loss coefficient ⁇ c of the combustion chamber and the specific heat ratio of the combustion chamber outlet gas ⁇ .
  • w is the independent variable relative load
  • f(w) is the calculation function of the total pressure loss coefficient of the combustion chamber obtained by fitting
  • g(w) is the calculation function of the specific heat ratio of the combustion chamber outlet gas obtained by fitting.
  • T4 is the exhaust temperature of the gas turbine
  • P2 is the exhaust pressure of the gas turbine compressor
  • P4 is the exhaust pressure of the gas turbine.
  • the calculated turbine inlet temperature T3 and the combustion pressure pulsation data obtained from the gas turbine generator set operation data are fed back to the gas turbine control system.
  • the gas turbine control system makes the following judgments: 1. When T3r - T3 ⁇ ⁇ ( T3r is the turbine inlet temperature limit set in the gas turbine control system, and ⁇ is the turbine inlet temperature safety threshold set in the gas turbine control system), and the combustion pressure pulsation value is less than the alarm value, then an instruction to reduce the IGV opening by 1% is output; 2. When T3r - T3 ⁇ ⁇ , but the combustion pressure pulsation value is greater than the alarm value, then an instruction to increase the fuel flow rate by 0.5% is output; 3. When T3r - T3 ⁇ 0, then an instruction to increase the IGV opening by 1% is output.
  • step 7 After executing the control command issued by the gas turbine control system in step 7, calculate the turbine inlet temperature in real time, and combine it with the changes in combustion pressure pulsation data to generate new IGV and fuel flow control commands in real time until the turbine inlet temperature T3 is higher than the T3r - ⁇ value for the first time, so that the turbine inlet temperature T3 is as close as possible to the turbine inlet temperature limit T3r under safe conditions, thereby improving the thermal efficiency of gas turbine power generation.
  • the above is a schematic scheme of a gas turbine combustor outlet temperature optimization and adjustment method according to this embodiment.
  • the technical solution of this gas turbine combustor outlet temperature optimization and adjustment method system belongs to the same concept as the technical solution of the gas turbine combustor outlet temperature optimization and adjustment method described above. Details not described in detail in the technical solution of the gas turbine combustor outlet temperature optimization and adjustment method system in this embodiment can be found in the description of the technical solution of the gas turbine combustor outlet temperature optimization and adjustment method described above.
  • the gas turbine combustor outlet temperature optimization and adjustment system in this embodiment includes a combustion model establishment module, a flow parameter calculation module, a gas specific heat ratio and combustor pressure loss calculation module, a gas specific heat ratio and combustor pressure loss fitting module, a turbine inlet temperature calculation module, and a data feedback and adjustment module.
  • the combustion model establishment module establishes a three-dimensional numerical model for combustion calculation in the combustion chamber.
  • the flow parameter calculation module calculates the combustion chamber flow field characteristic parameters under typical load conditions.
  • the specific heat ratio of the gas and the pressure loss calculation module of the combustion chamber obtain the specific heat ratio of the gas at the outlet of the combustion chamber and the total pressure loss coefficient of the combustion chamber under typical load conditions.
  • the specific heat ratio of the gas and the pressure loss fitting module of the combustion chamber are used to fit and obtain the calculation formulas for the specific heat ratio of the gas and the total pressure loss coefficient of the combustion chamber.
  • the turbine inlet temperature calculation module establishes a turbine inlet temperature calculation formula and calculates the turbine inlet temperature.
  • the data feedback and adjustment module feeds back the calculated turbine inlet temperature and the combustion pressure pulsation data obtained from the gas turbine generator set operation data to the gas turbine control system; and adjusts the IGV opening and fuel flow.
  • This embodiment also provides a computing device applicable to a method for optimizing and adjusting the outlet temperature of a gas turbine combustion chamber, including:
  • the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium.
  • the technical solution of the present invention, or the part that contributes to the prior art, or a part of the technical solution can be embodied in the form of a software product.
  • This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention.
  • the aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.
  • Computer-readable media include: electrical connections (electronic devices) having one or more wires, portable computer disk drives (magnetic devices), random access memory (RAM), read-only memory (ROM), erasable and editable read-only memory (EPROM or flash memory), fiber optic devices, and portable optical disc read-only memory (CDROM).
  • electrical connections electronic devices
  • portable computer disk drives magnetic devices
  • RAM random access memory
  • ROM read-only memory
  • EPROM or flash memory erasable and editable read-only memory
  • CDROM portable optical disc read-only memory
  • computer-readable media can even be paper or other suitable media on which the program can be printed, because the program can be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, interpreting, or otherwise processing as necessary, and then stored in computer memory.
  • Example 2 referring to Figures 2-7, is the second embodiment of the present invention, which provides a method for optimizing and adjusting the outlet temperature of a gas turbine combustion chamber.
  • scientific demonstration is carried out through experiments.
  • a gas-fired power plant uses a 9FA gas turbine.
  • a three-dimensional solid model of the gas turbine combustion chamber is established using UG modeling software, as shown in Figure 2.
  • the solid model established by UG is meshed using ANSYS commercial software to build a three-dimensional numerical model of the combustion chamber, as shown in Figure 3.
  • Thermoflow Using Thermoflow, a professional software for power plant thermal balance analysis, a thermal balance calculation model for a 9FA gas turbine was established. Based on historical operating data of the gas turbine, the inlet atmospheric pressure of the calculation model was set to 1.001 bar, the atmospheric temperature to 21.49°C, the relative humidity to 79%, and the load to 100%. The calculation results are shown in Figure 4.
  • the operating data of the power plant's gas turbine shows that the combustion chamber inlet air pressure is 15.5 bar and the temperature is 400°C.
  • the pressure and temperature results calculated by Thermoflow are 15.46 bar and 399.8°C, respectively, verifying the accuracy of the established Thermoflow gas turbine thermal balance calculation model.
  • the frequently operating load points of the gas turbine in a certain gas-fired power plant are 50%, 65%, 80%, 95%, and 100%, these loads were used as typical loads.
  • the verified Thermoflow gas turbine thermal balance calculation model was used to calculate the inlet and outlet boundary parameters of the combustion chamber under these typical loads.
  • the combustion chamber inlet air temperature is 358°C
  • the flow rate is 341.6 kg/s
  • the combustion chamber inlet fuel temperature is 185°C
  • the flow rate is 9.054 kg/s
  • the combustion chamber outlet pressure is 10.12 bar.
  • the combustion chamber inlet air temperature is 374°C
  • the flow rate is 385 kg/s
  • the combustion chamber inlet fuel temperature is 185°C
  • the flow rate is 10.674 kg/s
  • the combustion chamber outlet pressure is 11.59 bar.
  • the combustion chamber inlet air temperature is 385°C
  • the flow rate is 436.4 kg/s
  • the combustion chamber inlet fuel temperature is 185°C
  • the flow rate is 12.168 kg/s
  • the combustion chamber outlet pressure is 13.18 bar.
  • the combustion chamber inlet air temperature is 392°C
  • the flow rate is 490.4 kg/s
  • the combustion chamber inlet fuel temperature is 185°C
  • the flow rate is 13.608 kg/s
  • the combustion chamber outlet pressure is 14.79 bar.
  • the combustion chamber inlet air temperature is 399.8°C
  • the flow rate is 493 kg/s
  • the combustion chamber inlet fuel temperature is 185°C
  • the flow rate is 13.77 kg/s
  • the combustion chamber outlet pressure is 14.88 bar.
  • step 3 Based on the combustion chamber inlet and outlet boundary parameters obtained in step 2, the three-dimensional numerical model of the combustion chamber established in step 1 was used to calculate the flow field parameters such as pressure, temperature, and velocity of the gas turbine combustion chamber under typical loads of 50%, 65%, 80%, 95%, and 100%. Some results are shown in Figures 5 to 7. The total pressure at the combustion chamber inlet, P2 *, and the total pressure at the combustion chamber outlet, P3 *, were read from the numerical calculation results and used the formula... The total pressure loss coefficient ⁇ c of the combustion chamber under typical loads of 50%, 65%, 80%, 95%, and 100% was calculated to be 0.038, 0.0386, 0.0392, 0.0398, and 0.04, respectively.
  • the specific heat ratio ⁇ of the combustion chamber outlet gas under typical loads of 50%, 65%, 80%, 95%, and 100% was obtained from the numerical calculation results to be 1.33087, 1.31899, 1.28342, 1.28386, and 1.28393, respectively.
  • the total pressure loss coefficient ⁇ c of the combustion chamber and the specific heat ratio of the combustion chamber outlet gas ⁇ obtained in step 3 are used as independent variables to fit the calculation formulas of the total pressure loss coefficient ⁇ c of the combustion chamber and the specific heat ratio of the combustion chamber outlet gas ⁇ .
  • ⁇ c 0.004w+0.036 0.5 ⁇ w ⁇ 1.0 (3)
  • T4 is the exhaust temperature of the gas turbine
  • P2 is the exhaust pressure of the gas turbine compressor
  • P4 is the exhaust pressure of the gas turbine.
  • the real-time database of a certain power plant's F-class gas turbine generator set shows that when the generator set is at 90% load, the combustion chamber inlet pressure P2 is 1.56 MPa, the turbine exhaust pressure P4 is 0.105357 MPa, and the turbine exhaust temperature T4 is 860 K.
  • the total pressure loss coefficient ⁇ c of the combustion chamber is 0.0396 and the specific heat ratio ⁇ of the combustion chamber outlet gas is 1.283698.
  • the turbine inlet temperature T3 is calculated to be 1546.3 K.
  • the turbine inlet temperature T3 is calculated in real time to be 1568.2K, and the maximum amplitude of combustion pressure pulsation is 0.65kPa.
  • the gas turbine control system continues to output the command to reduce the IGV opening by 1%.
  • the turbine inlet temperature T3 is calculated again to be 1612.2K, and the maximum amplitude of combustion pressure pulsation is 0.66kPa.
  • the turbine inlet temperature T3 is higher than T3r - ⁇ for the first time, indicating that the turbine inlet temperature has reached the optimal value.

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Abstract

本发明涉及燃气轮机技术领域，尤其涉及一种燃气轮机燃烧室出口温度优化调整方法及系统，包括，建立燃烧室三维燃烧计算数值模型，计算典型负荷工况下燃烧室流场特性参数；获得典型负荷工况下燃烧室出口的燃气比热比及燃烧室的总压损失系数；拟合获得燃气比热比和燃烧室总压损失系数的计算公式；建立透平入口温度计算公式，计算透平入口温度；将计算获得的透平入口温度以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，调节IGV开度和燃料流量。本发明通过精确调整燃烧室出口温度，可提升燃气轮机循环热效率和燃气轮机的运行安全性。

Description

一种燃气轮机燃烧室出口温度优化调整方法及系统 技术领域
本发明涉及燃气轮机技术领域，尤其涉及一种燃气轮机燃烧室出口温度优化调整方法及系统。
背景技术
燃气轮机是一种高效的热能转换设备，它通过燃烧燃料产生高温高压气体，进而推动涡轮旋转，转换为机械能。燃烧室出口温度是燃气轮机运行过程中的关键参数，对整个系统的效率、安全性和寿命、污染物排放等有着至关重要的影响。在效率方面，燃烧室出口温度越高，意味着更多的热能可以转化为机械能，从而提高整个系统的能效，然而，这一过程并非无限制，因为过高的燃烧室出口温度可能会导致材料的热应力增大，影响燃气轮机的寿命。在安全性和寿命方面，燃气轮机的燃烧室和涡轮部分需要使用能够承受高温的材料，如镍基合金，燃烧室出口温度的控制对于确保这些高温部件不超出其材料的耐热极限至关重要，此外，燃烧室出口温度的均匀分布可以减少热应力，延长部件的使用寿命。在排放控制方面，较高的燃烧室出口温度虽然可以促进更完全的燃烧，减少未燃尽的碳氢化合物和二氧化碳的排放，但相反会增加氮氧化物(NOx)排放，因为高温可以促进空气中的氮和氧发生反应，生成更多的氮氧化物。
综上所述，燃气轮机燃烧室出口温度的控制对于确保整个系统的高效率、安全性、环保性以及经济性至关重要。精确控制燃烧室出口温度对于保障燃气轮机的安全运行至关重要。通过精确控制燃烧室出口温度，不仅可保障燃气轮机的安全运行，还可有效延长燃气轮机的维护周期和使用寿命，减少了燃气轮机的维护成本，提高燃气轮机的经济效益。
发明内容
鉴于上述现有技术中存在的问题，提出了本发明。
因此，本发明提供了一种燃气轮机燃烧室出口温度优化调整方法，能够解决传统燃气轮机无法精确控制燃烧室出口温度的问题。
为解决上述技术问题，本发明提供如下技术方案，一种燃气轮机燃烧室出口温度优化调整方法，包括：建立燃烧室三维燃烧计算数值模型，计算典型负荷工况下燃烧室流场特性参数；获得典型负荷工况下燃烧室出口的燃气比热比及燃烧室的总压损失系数；拟合获得燃气比热比和燃烧室总压损失系数的计算公式；建立透平入口温度计算公式，计算透平入口温度；将计算获得的透平入口温度以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，调节IGV开度和燃料流量。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整方法的一种优选方案，其中：所述建立燃烧室三维燃烧计算数值模型包括，利用Thermoflow电厂热平衡分析软件，针对燃气发电厂采用的燃气轮机型号，建立Thermoflow燃气轮机热平衡计算模型，根据燃气轮机历史运行数据设定计算模型的边界参数，并利用燃气轮机历史运行数据对计算模型的准确性进行验证，采用经验证后的Thermoflow燃气轮机热平衡计算模型计算获得燃气轮机从启机至满负荷运行下燃烧室进出口边界参数，再利用流体数值仿真软件建立燃烧室三维燃烧数值模型，并根据Thermoflow燃气轮机热平衡计算模型计算获得的边界参数设定燃烧数值模型的进出口边界条件；
所述算典型负荷工况下燃烧室流场特性参数包括，分别计算获得50％、60％、70％、80％、90％和100％典型负荷下燃气轮机燃烧室内燃气压力场、温度场、速度场。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整方法的一种优选方案，其中：所述燃烧室总压损失系数表示为，分析获得50％、60％、70％、80％、90％和100％典型负荷下燃气轮机燃烧室进口总压P* 2、燃烧室出口总压P* 3，表示为，
其中，σc表示为燃烧室的总压损失系数。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整方法的一种优选方案，其中：所述拟合获得燃气比热比和燃烧室总压损失系数的计算公式包括，采用曲线拟合方法，利用计算获得的燃烧室总压损失系数和燃烧室出口燃气比热比，以相对负荷为自变量，分别拟合获得燃烧室总压损失系数和燃烧室出口燃气比热比的计算公式，
σc＝f(w)
γ＝g(w)
其中，w为自变量相对负荷，f(w)为拟合获得的燃烧室总压损失系数的计算函数，g(w)为拟合获得的燃烧室出口燃气比热比的计算函数。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整方法的一种优选方案，其中：所述建立透平入口温度计算公式包括，利用高温高压燃气在透平内膨胀做功的燃气能量变化特性，建立透平入口温度T3的计算公式表示为，
其中，T4为燃气轮机透平排气温度；P2为燃气轮机压气机排气压力；P4为燃气轮机透平排气压力；
从燃气轮机发电机组运行数据中获取燃气轮机透平排气温度T4、燃气轮机压气机排气压力P2、燃气轮机透平排气压力P4，结合燃烧室总压损失系数σc和燃烧室出口燃气比热比γ的计算公式和透平入口温度的计算公式计算获得透平入口温度T3。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整方法的一种优选方案，其中：将计算获得的透平入口温度T3以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，燃气轮机控制系统进行判断：当T3r-T3≥α，且燃烧压力脉动数值小于报警值，则输出IGV开度减小1％的指令；当T3r-T3≥α，但燃烧压力脉动数值大于报警值，则输出燃料流量增大0.5％的指令；当T3r-T3<0，则输出IGV开度增大1％的指令；
其中，T3r为燃气轮机控制系统中设定的透平入口温度限值，α为燃气轮机控制系统中设定的透平入口温度安全阈值。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整方法的一种优选方案，其中：所述调节IGV开度和燃料流量包括，实时计算透平入口温度，并结合燃烧压力脉动数据变化情况，即时生成新的IGV和燃料流量控制指令，直至透平入口温度T3第一次高于T3r－α值，使透平入口温度T3在安全条件下接近透平入口温度限值T3r，提高燃气轮机发电热效率。
本发明的另外一个目的是提供一种燃气轮机燃烧室出口温度优化调整系统，提高燃烧效率、优化燃烧室设计、确保准确了解燃烧室内流动情况、调整燃料比例、降低压损、提高能源利用效率、实现燃气轮机运行参数的预测与优化、提升系统稳定性、确保透平入口温度合理以及实现燃气轮机的高效、稳定运行。
作为本发明所述的一种燃气轮机燃烧室出口温度优化调整系统的一种优选方案，其中：包括，燃烧模型建立模块、流动参数计算模块、燃气比热比与燃烧室压损计算模块、燃气比热比与燃烧室压损拟合模块、透平入口温度计算模块、数据反馈与调节模块；
所述燃烧模型建立模块，建立燃烧室三维燃烧计算数值模型；
所述流动参数计算模块，计算典型负荷工况下燃烧室流场特性参数；
所述燃气比热比与燃烧室压损计算模块，获得典型负荷工况下燃烧室出口的燃气比热比及燃烧室的总压损失系数；
所述燃气比热比与燃烧室压损拟合模块，拟合获得燃气比热比和燃烧室总压损失系数的计算公式；
所述透平入口温度计算模块，建立透平入口温度计算公式，计算透平入口温度；
所述数据反馈与调节模块，将计算获得的透平入口温度以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统；调节IGV开度和燃料流量。
一种计算机设备，包括存储器和处理器，所述存储器存储有计算机程序，其特征在于，所述处理器执行所述计算机程序时实现一种燃气轮机燃烧室出口温度优化调整方法中任一项所述的方法的步骤。
一种计算机可读存储介质，其上存储有计算机程序，其特征在于，所述计算机程序被处理器执行时实现一种燃气轮机燃烧室出口温度优化调整方法中任一项所述的方法的步骤。
本发明的有益效果：燃气轮机的循环热效率一般与透平入口温度呈正相关关系，提高透平入口温度可以提升循环热效率，但由于燃气轮机透平入口温度较高，无法直接测量，本方案根据透平排气温度计算透平入口温度，对比分析透平入口温度计算值与透平入口温度限值之间的距离，实时减小或增大IGV开度，进而控制进入燃气轮机的空气流量，当减小IGV开度时，进入燃气轮机的空气流量减小，透平入口温度就会提高，进而提升燃气轮机的循环热效率；当增大IGV开度时，进入燃气轮机的空气流量会增加，透平入口温度就会降低，防止透平叶片被烧损，提升燃气轮机的运行安全性。
附图说明
为了更清楚地说明本发明实施例的技术方案，下面将对实施例描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其它的附图。
图1为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的流程图。
图2为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的燃烧室三维实体模型。
图3为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的燃烧室三维数值模型。
图4为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的100％典型负荷下thermoflow燃气轮机热平衡计算结果。
图5为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的100％典型负荷下燃烧室中心截面压力场结果。
图6为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的100％典型负荷下燃烧室中心截面温度场结果。
图7为本发明一个实施例提供的一种燃气轮机燃烧室出口温度优化调整方法的100％典型负荷下燃烧室中心截面速度场结果。
具体实施方式
为使本发明的上述目的、特征和优点能够更加明显易懂，下面结合说明书附图对本发明的具体实施方式做详细的说明，显然所描述的实施例是本发明的一部分实施例，而不是全部实施例。基于本发明中的实施例，本领域普通人员在没有做出创造性劳动前提下所获得的所有其他实施例，都应当属于本发明的保护的范围。
实施例1，参照图1，为本发明的第一个实施例，该实施例提供了一种燃气轮机燃烧室出口温度优化调整方法，包括：本方案利用燃烧室入口压力P2并结合燃烧室压力损失系数计算获得透平入口压力，进而计算透平入口温度T3，方法简单可行，实施效率高。
本方案无需通过实验，仅通过建立燃气轮机热平衡计算模型和燃气轮机燃烧室数值模型，采用曲线拟合方法，即可获得不同负荷下燃气轮机燃烧室的总压损失系数σc和燃烧室出口燃气比热比γ，提高了透平入口温度的计算准确度。
本方案通过调取燃气轮机发电机组实时数据库中燃烧室入口压力P2、透平排气压力P4、透平排气温度T4等运行参数，即可实时计算获得透平入口温度，并与燃气轮机透平入口温度限值实时比较，根据比较结果与透平入口温度安全阈值α的距离，实时调整IGV开度和燃料流量，实现部分负荷下提高燃气轮机透平入口温度，进而提升燃气轮机循环热效率。
本方案弥补了燃气轮机透平入口温度不能直接测量的缺陷，使燃气轮机透平入口温度控制更加精准，在低负荷下可以提升燃气轮机循环热效率，在高负荷时可以增加IGV开度，增加进入燃气轮机的空气流量，降低透平入口温度，防止透平叶片烧损，提升燃气轮机运行安全性。
1)、建立燃气轮机燃烧室三维燃烧计算数值模型。
2)、因燃气轮机燃烧室出口燃气温度高，一般无测点直接测量燃烧室出口燃气的压力和温度，为获得燃气轮机燃烧室三维燃烧计算数值模型分析时所需的燃烧室进出口边界参数，利用Thermoflow电厂热平衡分析专业软件，针对燃气发电厂采用的燃气轮机型号，建立Thermoflow燃气轮机热平衡计算模型，根据燃气轮机历史运行数据设定计算模型的边界参数，并利用燃气轮机历史运行数据对计算模型的准确性进行验证。采用经验证后的Thermoflow燃气轮机热平衡计算模型计算获得燃气轮机从启机至满负荷运行下燃烧室进出口边界参数。考虑到燃气轮机在低负荷运行时，污染物排放会超标，燃气轮机发电机组一般工作在50％至100％负荷区间内。因此利用上述方法主要计算获得50％、60％、70％、80％、90％和100％等典型负荷下燃气轮机燃烧室进口空气和燃料质量流量、温度以及燃烧室出口压力等边界参数，典型负荷可根据燃机电厂经常运行负荷点进行选择确定。在第1步建立的燃气轮机燃烧室三维燃烧计算数值模型中，按第2步计算获得的燃烧室进出口边界参数进行设定，计算获得50％、60％、70％、80％、90％和100％等典型负荷下燃气轮机燃烧室内燃气压力场、温度场、速度场的分别。
3)、根据第2步计算结果，分析获得50％、60％、70％、80％、90％和100％等典型负荷下燃气轮机燃烧室进口总压P2*、燃烧室出口总压P3*和燃烧室出口燃气比热比γ，利用公式计算获得燃烧室的总压损失系数σc。
4)、采用曲线拟合方法，利用第3步计算获得的燃烧室总压损失系数σc和燃烧室出口燃气比热比γ，以相对负荷为自变量，分别拟合获得燃烧室总压损失系数σc和燃烧室出口燃气比热比γ的计算公式。
σc＝f(w)
γ＝g(w)         (1)
式中w为自变量相对负荷，f(w)为拟合获得的燃烧室总压损失系数的计算函数，g(w)为拟合获得的燃烧室出口燃气比热比的计算函数。
5)、利用高温高压燃气在透平内膨胀做功的燃气能量变化特性，建立透平入口温度T3(即燃烧室出口温度)的计算公式：
式中T4为燃气轮机透平排气温度；P2为燃气轮机压气机排气压力；P4为燃气轮机透平排气压力。
6)、从燃气轮机发电机组运行数据中获取燃气轮机透平排气温度T4、燃气轮机压气机排气压力P2、燃气轮机透平排气压力P4，结合公式(1)和公式(2)计算获得透平入口温度T3。
7)、将计算获得的透平入口温度T3以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，燃气轮机控制系统进行如下判断：1、当T3r-T3≥α(T3r为燃气轮机控制系统中设定的透平入口温度限值，α为燃气轮机控制系统中设定的透平入口温度安全阈值)，且燃烧压力脉动数值小于报警值，则输出IGV开度减小1％的指令；2、当T3r-T3≥α，但燃烧压力脉动数值大于报警值，则输出燃料流量增大0.5％的指令；3、当T3r-T3<0，则输出IGV开度增大1％的指令。
8)、执行第7步燃气轮机控制系统发出的控制指令后，实时计算透平入口温度，并结合燃烧压力脉动数据变化情况，即时生成新的IGV和燃料流量控制指令，直至透平入口温度T3第一次高于T3r-α值，使透平入口温度T3在安全条件下尽可能接近透平入口温度限值T3r，提高燃气轮机发电热效率。
上述为本实施例的一种燃气轮机燃烧室出口温度优化调整方法的示意性方案。需要说明的是，该一种燃气轮机燃烧室出口温度优化调整方法的系统的技术方案与上述的一种燃气轮机燃烧室出口温度优化调整方法的技术方案属于同一构思，本实施例中一种燃气轮机燃烧室出口温度优化调整方法的系统的技术方案未详细描述的细节内容，均可以参见上述一种燃气轮机燃烧室出口温度优化调整方法的技术方案的描述。
本实施例中种燃气轮机燃烧室出口温度优化调整系统，包括，燃烧模型建立模块、流动参数计算模块、燃气比热比与燃烧室压损计算模块、燃气比热比与燃烧室压损拟合模块、透平入口温度计算模块、数据反馈与调节模块；
所述燃烧模型建立模块，建立燃烧室三维燃烧计算数值模型；
所述流动参数计算模块，计算典型负荷工况下燃烧室流场特性参数；
所述燃气比热比与燃烧室压损计算模块，获得典型负荷工况下燃烧室出口的燃气比热比及燃烧室的总压损失系数；
所述燃气比热比与燃烧室压损拟合模块，拟合获得燃气比热比和燃烧室总压损失系数的计算公式；
所述透平入口温度计算模块，建立透平入口温度计算公式，计算透平入口温度；
所述数据反馈与调节模块，将计算获得的透平入口温度以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统；调节IGV开度和燃料流量。
本实施例还提供一种计算设备，适用于一种燃气轮机燃烧室出口温度优化调整方法的情况，包括：
所述功能如果以软件功能单元的形式实现并作为独立的产品销售或使用时，可以存储在一个计算机可读取存储介质中。基于这样的理解，本发明的技术方案本质上或者说对现有技术做出贡献的部分或者该技术方案的部分可以以软件产品的形式体现出来，该计算机软件产品存储在一个存储介质中，包括若干指令用以使得一台计算机设备(可以是个人计算机，服务器，或者网络设备等)执行本发明各个实施例所述方法的全部或部分步骤。而前述的存储介质包括：U盘、移动硬盘、只读存储器(ROM，Read-OnlyMemory)、随机存取存储器(RAM，Random Access Memory)、磁碟或者光盘等各种可以存储程序代码的介质。
在流程图中表示或在此以其他方式描述的逻辑和/或步骤，例如，可以被认为是用于实现逻辑功能的可执行指令的定序列表，可以具体实现在任何计算机可读介质中，以供指令执行系统、装置或设备(如基于计算机的系统、包括处理器的系统或其他可以从指令执行系统、装置或设备取指令并执行指令的系统)使用，或结合这些指令执行系统、装置或设备而使用。就本说明书而言，“计算机可读介质”可以是任何可以包含、存储、通信、传播或传输程序以供指令执行系统、装置或设备或结合这些指令执行系统、装置或设备而使用的装置。
计算机可读介质的更具体的示例(非穷尽性列表)包括以下：具有一个或多个布线的电连接部(电子装置)、便携式计算机盘盒(磁装置)、随机存取存储器(RAM)、只读存储器(ROM)、可擦除可编辑只读存储器(EPROM或闪速存储器)、光纤装置以及便携式光盘只读存储器(CDROM)。另外，计算机可读介质甚至可以是可在其上打印所述程序的纸或其他合适的介质，因为可以例如通过对纸或其他介质进行光学扫描，接着进行编辑、解译或必要时以其他合适方式进行处理来以电子方式获得所述程序，然后将其存储在计算机存储器中。
应当理解，本发明的各部分可以用硬件、软件、固件或它们的组合来实现。在上述实施方式中，多个步骤或方法可以用存储在存储器中且由合适的指令执行系统执行的软件或固件来实现。例如，如果用硬件来实现，和在另一实施方式中一样，可用本领域公知的下列技术中的任一项或他们的组合来实现：具有用于对数据信号实现逻辑功能的逻辑门电路的离散逻辑电路，具有合适的组合逻辑门电路的专用集成电路，可编程门阵列(PGA)，现场可编程门阵列(FPGA)等。
实施例2，参考图2-图7，为本发明的第二个实施例，提供了一种燃气轮机燃烧室出口温度优化调整方法，为了验证本发明的有益效果，通过实验进行科学论证。
1)、某燃气发电厂采用了9FA型燃气轮机，利用UG建模软件建立燃气轮机燃烧室三维实体模型，见图2，利用ANSYS商用软件对UG建立的实体模型进行网格划分，建成燃烧室三维数值模型，见图3。
2)、利用Thermoflow电厂热平衡分析专业软件，建立9FA型燃气轮机热平衡计算模型，根据燃气轮机历史运行数据设定计算模型入口大气压力为1.001bar，大气温度为21.49℃，相对湿度为79％，负荷设定为100％，计算结果见图4，电厂燃气轮机运行数据表明燃烧室入口空气压力为15.5bar，温度为400℃，Thermoflow计算的压力和温度结果分别为15.46bar和399.8℃，验证了所建立的Thermoflow燃气轮机热平衡计算模型的准确性。鉴于某燃气发电厂燃气轮机的经常运行负荷点为50％、65％、80％、95％和100％，因此将上述负荷作为典型负荷，采用验证后的Thermoflow燃气轮机热平衡计算模型计算获得上述典型负荷下燃烧室的进出口边界参数。在50％负荷下，燃烧室入口空气温度为358℃，流量为341.6kg/s，燃烧室入口燃料温度为185℃，流量为9.054kg/s，燃烧室出口压力为10.12bar。在65％负荷下，燃烧室入口空气温度为374℃，流量为385kg/s，燃烧室入口燃料温度为185℃，流量为10.674kg/s，燃烧室出口压力为11.59bar。在80％负荷下，燃烧室入口空气温度为385℃，流量为436.4kg/s，燃烧室入口燃料温度为185℃，流量为12.168kg/s，燃烧室出口压力为13.18bar。在95％负荷下，燃烧室入口空气温度为392℃，流量为490.4kg/s，燃烧室入口燃料温度为185℃，流量为13.608kg/s，燃烧室出口压力为14.79bar。在100％负荷下，燃烧室入口空气温度为399.8℃，流量为493kg/s，燃烧室入口燃料温度为185℃，流量为13.77kg/s，燃烧室出口压力为14.88bar。
3)、根据第2步计算获得的燃烧室进出口边界参数，采用第1步建立的燃烧室三维数值模型，分别计算获得50％、65％、80％、95％和100％等典型负荷下燃气轮机燃烧室的压力、温度、速度等流场参数，部分结果见图5至图7，从数值计算结果中分别读取燃烧室进口总压P2*、燃烧室出口总压P3*，利用公式分别计算获得50％、65％、80％、95％和100％等典型负荷下燃烧室的总压损失系数σc为0.038、0.0386、0.0392、0.0398、0.04，从数值计算结果中分别读取获得50％、65％、80％、95％和100％等典型负荷下燃烧室出口燃气比热比γ为1.33087、1.31899、1.28342、1.28386和1.28393。
4)、采用曲线拟合方法，利用第3步计算获得的燃烧室总压损失系数σc和燃烧室出口燃气比热比γ，以相对负荷为自变量，分别拟合获得燃烧室总压损失系数σc和燃烧室出口燃气比热比γ的计算公式。
σc＝0.004w+0.036 0.5≤w≤1.0       (3)
其中，w为自变量相对负荷。
5)、建立透平入口温度T3(即燃烧室出口温度)的计算公式：
其中，T4为燃气轮机透平排气温度；P2为燃气轮机压气机排气压力；P4为燃气轮机透平排气压力。
6)、从某电厂F级燃气轮机发电机组实时数据库中获取得在发电机组功率为90％负荷时，燃烧室入口压力P2为1.56MPa、透平排气压力P4为0.105357MPa、透平排气温度T4为860K，利用公式(3)和公式(4)分别计算获得燃烧室总压损失系数σc为0.0396、燃烧室出口燃气比热比γ为1.283698，再利用公式(5)计算获得透平入口温度T3为1546.3K。
7)、从某电厂F级燃气轮机发电机组实时数据库中获取得此时燃烧压力脉动最高幅值为0.67kPa，分析燃气轮机控制系统获得燃气轮机透平入口温度限值T3r设定为1620K，透平入口温度安全阈值α设定为10K，压力脉动报警值设定为2.5kPa。将计算获得的透平入口温度T3以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，燃气轮机控制系统实时计算判断：1620-1546.3＝73.7>α，且燃烧压力脉动数值小于报警值，则输出IGV开度减小1％的指令。
8)、执行第7步燃气轮机控制系统发出的控制指令后，实时计算透平入口温度T3为1568.2K，燃烧压力脉动最高幅值为0.65kPa，燃机控制系统继续输出IGV开度减小1％的指令，调整后再次计算透平入口温度T3为1612.2K，燃烧压力脉动最高幅值为0.66kPa，燃气轮机控制系统实时计算判断：1620-1612.2＝7.8<α，透平入口温度T3第一次高于T3r-α值，说明透平入口温度已达到最优值。

Claims (10)

  1. 一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：包括，
    建立燃烧室三维燃烧计算数值模型，计算典型负荷工况下燃烧室流场特性参数；
    获得典型负荷工况下燃烧室出口的燃气比热比及燃烧室的总压损失系数；
    拟合获得燃气比热比和燃烧室总压损失系数的计算公式；
    建立透平入口温度计算公式，计算透平入口温度；
    将计算获得的透平入口温度以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，调节IGV开度和燃料流量。
  2. 如权利要求1所述的一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：所述建立燃烧室三维燃烧计算数值模型包括，利用Thermoflow电厂热平衡分析软件，针对燃气发电厂采用的燃气轮机型号，建立Thermoflow燃气轮机热平衡计算模型，根据燃气轮机历史运行数据设定计算模型的边界参数，并利用燃气轮机历史运行数据对计算模型的准确性进行验证，采用经验证后的Thermoflow燃气轮机热平衡计算模型计算获得燃气轮机从启机至满负荷运行下燃烧室进出口边界参数，再利用流体数值仿真软件建立燃烧室三维燃烧数值模型，并根据Thermoflow燃气轮机热平衡计算模型计算获得的边界参数设定燃烧数值模型的进出口边界条件；
    所述算典型负荷工况下燃烧室流场特性参数包括，分别计算获得50％、60％、70％、80％、90％和100％典型负荷下燃气轮机燃烧室内燃气压力场、温度场、速度场。
  3. 如权利要求2所述的一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：所述总压损失系数表示为，分析获得50％、60％、70％、80％、90％和100％典型负荷下燃气轮机燃烧室进口总压P* 2、燃烧室出口总压P* 3，表示为，
    其中，σc表示为燃烧室的总压损失系数。
  4. 如权利要求3所述的一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：所述拟合获得燃气比热比和燃烧室总压损失系数的计算公式包括，采用曲线拟合方法，利用计算获得的燃烧室总压损失系数和燃烧室出口燃气比热比，以相对负荷为自变量，分别拟合获得燃烧室总压损失系数和燃烧室出口燃气比热比γ的计算公式，
    σc＝f(w)
    γ＝g(w)
    其中，w为自变量相对负荷，f(w)为拟合获得的燃烧室总压损失系数的计算函数，g(w)为拟合获得的燃烧室出口燃气比热比的计算函数。
  5. 如权利要求4所述的一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：所述建立透平入口温度计算公式包括，利用高温高压燃气在透平内膨胀做功的燃气能量变化特性，建立透平入口温度T3的计算公式表示为，
    其中，T4为燃气轮机透平排气温度；P2为燃气轮机压气机排气压力；P4为燃气轮机透平排气压力；
    从燃气轮机发电机组运行数据中获取燃气轮机透平排气温度T4、燃气轮机压气机排气压力P2、燃气轮机透平排气压力P4，结合燃烧室总压损失系数σc和燃烧室出口燃气比热比γ的计算公式和透平入口温度的计算公式计算获得透平入口温度T3。
  6. 如权利要求5所述的一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：将计算获得的透平入口温度T3以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统，燃气轮机控制系统进行判断：当T3r-T3≥α，且燃烧压力脉动数值小于报警值，则输出IGV开度减小1％的指令；当T3r-T3≥α，但燃烧压力脉动数值大于报警值，则输出燃料流量增大0.5％的指令；当T3r-T3<0，则输出IGV开度增大1％的指令；
    其中，T3r为燃气轮机控制系统中设定的透平入口温度限值，α为燃气轮机控制系统中设定的透平入口温度安全阈值。
  7. 如权利要求6所述的一种燃气轮机燃烧室出口温度优化调整方法，其特征在于：所述调节IGV开度和燃料流量包括，实时计算透平入口温度，并结合燃烧压力脉动数据变化情况，即时生成新的IGV和燃料流量控制指令，直至透平入口温度T3第一次高于T3r－α值，使透平入口温度T3在安全条件下接近透平入口温度限值T3r，提高燃气轮机发电热效率。
  8. 一种基于权利要求1-7任一所述的一种燃气轮机燃烧室出口温度优化调整方法的系统，其特征在于：包括，燃烧模型建立模块、流动参数计算模块、燃气比热比与燃烧室压损计算模块、燃气比热比与燃烧室压损拟合模块、透平入口温度计算模块、数据反馈与调节模块；
    所述燃烧模型建立模块，建立燃烧室三维燃烧计算数值模型；
    所述流动参数计算模块，计算典型负荷工况下燃烧室流场特性参数；
    所述燃气比热比与燃烧室压损计算模块，获得典型负荷工况下燃烧室出口的燃气比热比及燃烧室的总压损失系数；
    所述燃气比热比与燃烧室压损拟合模块，拟合获得燃气比热比和燃烧室总压损失系数的计算公式；
    所述透平入口温度计算模块，建立透平入口温度计算公式，计算透平入口温度；
    所述数据反馈与调节模块，将计算获得的透平入口温度以及从燃气轮机发电机组运行数据中获得的燃烧压力脉动数据反馈给燃气轮机控制系统；调节IGV开度和燃料流量。
  9. 一种计算机设备，包括存储器和处理器，所述存储器存储有计算机程序，其特征在于，所述处理器执行所述计算机程序时实现权利要求1至7中任一项所述的方法的步骤。
  10. 一种计算机可读存储介质，其上存储有计算机程序，其特征在于，所述计算机程序被处理器执行时实现权利要求1至7中任一项所述的方法的步骤。
PCT/CN2024/132242 2024-08-01 2024-11-15 一种燃气轮机燃烧室出口温度优化调整方法及系统 Pending WO2026025720A1 (zh)

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