Gas turbine fuel regulation and condition protection control device and control method

Abstract

This invention relates to the field of gas turbine technology and discloses a gas turbine fuel regulation and condition protection control device, including a gas turbine unit and a fuel controller. The gas turbine unit includes a gas generator and a power turbine. The gas generator includes a compressor. The output end of the gas turbine unit is connected to the input end of the fuel controller. The output end of the fuel controller is connected to both the input end of the gas turbine unit and the input end of the fuel controller. The fuel controller includes an over-temperature protection limiting module, an over-pressure protection limiting module, an over-speed protection limiting module, a fuel quantity boundary limiting module, a transition state boundary limiting module, a fuel main control module, and an optimal selection logic module. The invention also discloses a gas turbine fuel regulation and condition protection control method. This invention can adapt to the full operating conditions of gas turbines and achieve precise fuel quantity regulation and multiple protections, providing a guarantee for the safe and efficient operation of gas turbines throughout their entire life cycle.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and in particular to a gas turbine fuel regulation and condition protection control device and control method. Background Technology

[0002] With the rapid development of modern engineering thermophysics and industry, the application scenarios of gas turbines are constantly expanding. Fields such as pipeline compression stations, marine power, industrial drives, and power generation are placing increasingly stringent demands on the safety, reliability, and operational efficiency of gas turbines. As the "brain" of the gas turbine, the control system must not only ensure the unit operates efficiently and stably under normal conditions, but also, through precise control measures, avoid catastrophic consequences, minimize losses, and protect the lives and property of personnel under various faults or severe operating conditions. Among the various control components of a gas turbine, fuel control is the core, and a reasonable fuel supply is paramount for the safe and stable operation of the unit. Gas turbines have complex internal structures, and the operating environments of their components vary greatly. Key components such as the combustion chamber and turbine need to operate under high temperature and high pressure conditions for extended periods. This places extremely high demands on fuel quantity control technology: on the one hand, it is necessary to accurately match the fuel supply with the unit's operating conditions to avoid overheating and overpressure of components due to excessive fuel, or insufficient unit output due to insufficient fuel; on the other hand, it is necessary to fully utilize the gas turbine's performance while ensuring component safety, taking into account both operational stability and high efficiency; furthermore, transient control and protection are also important components of fuel quantity control, such as the drastic changes in fuel quantity during gas turbine start-up and acceleration.

[0003] Currently, existing gas turbine fuel quantity control has some important pressure and temperature protection limits, which are generally fixed constant values; and existing fuel quantity control technology takes into account the physical limitations of the fuel nozzle and the situations of low fuel level shutdown and fuel oversaturation during the transient state.

[0004] The existing technology has at least the following problems: First, the fixed protection limit is not suitable for limiting the process of changing operating conditions, and cannot dynamically adjust the protection limit value under various environmental conditions. Second, it only has some important parameter limits and cannot fully protect the safety of various components of the gas turbine under extreme operating conditions.

[0005] Secondly, the transition state lacks acceleration limitations, and only a simple rate limit is applied to the fuel output. Such a control strategy is too crude and cannot effectively protect the gas turbine in the transition state, which will affect the service life of the gas turbine.

[0006] Third, gas turbines often face the problem of insufficient fuel regulation precision during start-up and shutdown transitions, load fluctuations, and extreme operating conditions: improper fuel control during start-up and shutdown can easily lead to flameout or component impact; during normal operation, if the fuel quantity cannot respond quickly to changes in speed, it may cause fluctuations in unit operation; when faced with abnormal conditions such as over-temperature and over-pressure, the existing fuel limiting logic often fails to balance safety and response speed, posing safety hazards. Summary of the Invention

[0007] To address the shortcomings of existing technologies, this invention develops a fuel regulation and condition protection control device and method for gas turbines. This invention can adapt to the fuel quantity control scheme required by gas turbines under all operating conditions, and can also achieve precise regulation and multiple protections of fuel quantity, thus providing a guarantee for the safe and efficient operation of gas turbines throughout their entire life cycle.

[0008] The technical solution to the technical problem solved by the present invention is as follows: On the one hand, embodiments of the present invention provide a gas turbine fuel regulation and state protection control device, including a gas turbine unit and a fuel controller. The gas turbine unit includes a gas generator and a power turbine. The gas generator includes a compressor. The output end of the gas turbine unit is connected to the input end of the fuel controller. The output end of the fuel controller is connected to both the input end of the gas turbine unit and the input end of the fuel controller. The fuel controller includes an over-temperature protection limiting module, an over-pressure protection limiting module, an over-speed protection limiting module, a fuel quantity boundary limiting module, a transition state boundary limiting module, a fuel main control module, and an optimal selection logic module.

[0009] On the other hand, embodiments of the present invention provide a gas turbine fuel regulation and condition protection control method, applied to the aforementioned gas turbine fuel regulation and condition protection control device, comprising the following steps:

[0010] S1. The fuel controller calculates the maximum compressor inlet temperature protection limit, the maximum power turbine inlet temperature protection limit, the maximum compressor inlet pressure protection limit, the maximum gas generator speed protection limit, the gas generator acceleration rate fuel quantity limit, the power turbine acceleration rate fuel quantity limit, the gas generator speed fuel quantity control output, and the power turbine speed fuel quantity control output, and takes the minimum value among them.

[0011] S2. The fuel controller calculates the minimum fuel quantity limit and the fuel quantity limit of the gas generator deceleration rate, respectively, and compares them with the minimum value obtained in step S1, and takes the maximum value among the three.

[0012] S3. The fuel controller calculates the maximum fuel limit and compares it with the maximum value obtained in step S2. The minimum value between the two is taken as the optimal selection output.

[0013] S4. The fuel controller calculates the fuel flow demand for the current operating cycle and outputs it to the input terminals of the gas turbine unit and the fuel controller.

[0014] S5. The gas turbine unit feeds back the operating status values ​​of each component to the fuel controller, and at the same time feeds back the fuel flow demand and optimal selection output to the fuel controller, which then performs the calculation for the next cycle.

[0015] As an optimization, in step S1, the over-temperature protection limiting module selects the power turbine inlet temperature and the compressor outlet temperature as calculation conditions, and calculates the maximum compressor inlet temperature protection limit and the maximum power turbine inlet temperature protection limit according to the calculation formula of the over-temperature protection limiting module. The calculation formula of the over-temperature protection limiting module is as follows:

[0016]

[0017] In the formula: Output is limited by maximum temperature protection. This is the maximum tolerable temperature value. This is the current temperature value. The proportional gain parameter is limited by over-temperature protection. The optimal output should be selected. The integral gain parameter is limited by over-temperature protection. This is the intermediate value for integral regulation to limit over-temperature protection.

[0018] As an optimization, in step S1, the overpressure protection limiting module selects the compressor outlet pressure value as the calculation condition, and calculates the maximum compressor inlet pressure protection limit according to the calculation formula of the overpressure protection limiting module. The calculation formula of the overpressure protection limiting module is as follows:

[0019]

[0020] In the formula: Output is limited by the maximum compressor outlet pressure protection. The maximum withstandable compressor outlet pressure value, This is the current compressor outlet pressure value. The proportional gain parameter is for overpressure protection limits. The optimal output should be selected. The integral gain parameter is limited by overpressure protection. The integral adjustment intermediate value is used to limit overpressure protection.

[0021] As an optimization, in step S1, the overspeed protection limit module selects the gas generator speed as the calculation condition, and calculates the maximum gas generator speed protection limit according to the calculation formula of the overspeed protection limit module. The calculation formula of the overspeed protection limit module is as follows:

[0022]

[0023] In the formula: Output is limited to protect the maximum gas generator speed. The maximum speed that the gas generator can withstand. This is the current gas generator speed value. The proportional gain parameter is for overspeed protection limits. The optimal output should be selected. The integral gain parameter is the overspeed protection limit. This is the intermediate value for integral adjustment to limit over-rev protection.

[0024] As an optimization, in step S2, the fuel quantity boundary limit module selects the minimum fuel limit as the calculation condition and calculates the minimum fuel quantity limit according to the calculation formula of the fuel quantity boundary limit module. In step S3, the fuel quantity boundary limit module selects the maximum fuel limit as the calculation condition and calculates the maximum fuel quantity limit according to the calculation formula of the fuel quantity boundary limit module. The calculation formula of the fuel quantity boundary limit module is as follows:

[0025]

[0026] In the formula: To limit output for fuel boundary protection, This is the maximum tolerable fuel boundary value. For fuel flow requirements, The proportional gain parameter is used to limit the fuel quantity boundary.

[0027] As an optimization, in step S1, the transition state boundary constraint module selects the gas generator speed acceleration rate constraint and the power turbine speed acceleration rate constraint as calculation conditions, and calculates the gas generator acceleration rate fuel quantity constraint and the power turbine acceleration rate fuel quantity constraint according to the calculation formula of the transition state boundary constraint module; in step S2, the transition state boundary constraint module selects the gas generator speed deceleration rate fuel quantity constraint as calculation condition, and calculates the gas generator deceleration rate fuel quantity constraint according to the calculation formula of the transition state boundary constraint module. The calculation formula of the transition state boundary constraint module is:

[0028]

[0029] In the formula: Output is limited for speed protection. This is the maximum tolerable speed value. This is the current rotational speed value. The proportional gain parameter is the boundary constraint of the transition state. The optimal output should be selected. The integral gain parameter is constrained by the transition state boundary. This is an intermediate quantity used for integral adjustment to constrain the transition state boundary.

[0030] As an optimization, in step S1, the fuel main control module selects the gas generator speed and the power turbine speed as calculation conditions, and calculates the fuel quantity control output for the gas generator speed and the fuel quantity control output for the power turbine speed according to the calculation formula of the fuel main control module. The calculation formula of the fuel main control module is as follows:

[0031]

[0032] In the formula: This is the main control output for fuel quantity. For the target speed value, This is the current rotational speed value. The proportional gain parameter for the main fuel control. The optimal output should be selected. The integral gain parameter for the main fuel control. This is the intermediate quantity for integral regulation of the main fuel control.

[0033] As an optimization, in step S4, the optimal selection logic module selects the optimal selection output from step S3 and the fuel flow demand from the previous operation cycle, and calculates the fuel flow demand for the current operation cycle according to the fuel flow demand calculation formula. The fuel flow demand calculation formula is as follows:

[0034]

[0035] In the formula: The fuel flow requirement for the current computing cycle. The optimal output for the current computation cycle. This represents the fuel flow requirement for the previous operating cycle.

[0036] Compared with the prior art, the present invention has the following beneficial effects:

[0037] This invention calculates the required fuel quantity for the current operating condition based on the gas generator speed and the power turbine speed. It then limits and protects the fuel quantity based on the temperature and pressure the gas turbine can withstand. Furthermore, it considers the gas turbine's acceleration limitations, low fuel level causing flameout, and fuel oversaturation, achieving comprehensive protection. During normal operation, the fuel quantity can be controlled according to the speed to ensure stable gas turbine operation. It also ensures safe operation of the gas turbine during start-up / shutdown transitions and when the turbine experiences over-temperature or over-pressure conditions. This invention allows for dynamic adaptation to different operating conditions by selecting different relevant parameters. It also allows for adjusting the parameters input to the relevant protection and limiting modules and the main control parameters according to different gas turbine models, making it applicable to various turbine types. Protection and limiting modules can be easily added or removed without affecting the main control framework. Attached Figure Description

[0038] Figure 1 This is a schematic diagram of the gas turbine fuel regulation and condition protection control device and control method of the present invention.

[0039] Figure 2 This is a schematic diagram of the selection logic of the optimal selection logic module in the gas turbine fuel regulation and condition protection control device of the present invention. Detailed Implementation

[0040] To clearly illustrate the technical features of this solution, the invention will be described in detail below through specific implementation methods and in conjunction with the accompanying drawings.

[0041] Figure 1 As one embodiment of the present invention, such as Figure 1 As shown, this invention discloses a gas turbine fuel regulation and condition protection control device, including a gas turbine unit and a fuel controller. The gas turbine unit includes a gas generator and a power turbine. The gas generator includes a compressor. The output terminal of the gas turbine unit is connected to the input terminal of the fuel controller. The output terminal of the fuel controller is connected to both the input terminal of the gas turbine unit and the input terminal of the fuel controller. The fuel controller includes an over-temperature protection limiting module, an over-pressure protection limiting module, an over-speed protection limiting module, a fuel quantity boundary limiting module, a transition state boundary limiting module, a fuel main control module, and an optimal selection logic module.

[0042] Among them, the over-temperature protection limit module is used to calculate the maximum compressor inlet temperature protection limit and the maximum power turbine inlet temperature protection limit;

[0043] The overpressure protection limit module is used to calculate the maximum compressor inlet pressure protection limit;

[0044] The overspeed protection limit module is used to calculate the maximum gas generator speed protection limit;

[0045] The fuel quantity boundary limit module is used to calculate the minimum fuel quantity limit and the maximum fuel quantity limit;

[0046] The transition state boundary limit module is used to calculate the fuel quantity limit for the gas generator acceleration rate, the fuel quantity limit for the gas generator deceleration rate, and the fuel quantity limit for the power turbine acceleration rate.

[0047] The main fuel control module is used to calculate the fuel quantity control output of the gas generator speed and the fuel quantity control output of the power turbine speed;

[0048] The optimal selection logic module is used to calculate the optimal selection output.

[0049] like Figure 1 and Figure 2 As shown, the present invention also discloses a gas turbine fuel regulation and condition protection control method, applied to the aforementioned gas turbine fuel regulation and condition protection control device, comprising the following steps:

[0050] S1, the over-temperature protection limit module calculates the maximum compressor inlet temperature protection limit and the maximum power turbine inlet temperature protection limit respectively; the over-pressure protection limit module calculates the maximum compressor inlet pressure protection limit; the over-speed protection limit module calculates the maximum gas generator speed protection limit; the transition state boundary limit module calculates the gas generator acceleration rate fuel quantity limit and the power turbine acceleration rate fuel quantity limit respectively; the fuel main control module calculates the gas generator speed fuel quantity control output and the power turbine speed fuel quantity control output respectively; and then the optimal selection logic module extracts the minimum value among them.

[0051] S2. The fuel quantity boundary limit module calculates the minimum fuel quantity limit, the transition state boundary limit module calculates the fuel quantity limit of the gas generator deceleration rate, and the optimal selection logic module compares the minimum fuel quantity limit and the fuel quantity limit of the gas generator deceleration rate with the minimum value taken in step S1, and then takes the maximum value among the three.

[0052] S3. The fuel quantity boundary limit module calculates the maximum fuel quantity limit. The optimal selection logic module compares the maximum fuel quantity limit with the maximum value taken in step S2, and then takes the minimum value between the two. This minimum value is the optimal selection output, which is the deviation value of the fuel flow demand.

[0053] S4. The optimal selection logic module calculates the fuel flow requirement for the current operation cycle and outputs it to the input terminals of the gas turbine unit and the fuel controller.

[0054] S5. The gas turbine unit feeds back the operating status values ​​of the gas generator and power turbine to the fuel controller, and at the same time feeds back the fuel flow demand and optimal selection output to the fuel controller, which then performs the calculation for the next cycle.

[0055] In step S1, the over-temperature protection limiting module selects the power turbine inlet temperature and the compressor outlet temperature as calculation conditions, and calculates the maximum compressor inlet temperature protection limit and the maximum power turbine inlet temperature protection limit according to the calculation formula of the over-temperature protection limiting module. The calculation formula of the over-temperature protection limiting module is as follows:

[0056]

[0057] In the formula: Output is limited by maximum temperature protection. This is the maximum tolerable temperature value. This is the current temperature value. The proportional gain parameter is limited by over-temperature protection. The optimal output should be selected. The integral gain parameter is limited by over-temperature protection. The intermediate value for integral regulation to limit over-temperature protection;

[0058] in, The calculation formula is:

[0059]

[0060] In the formula: For the current calculation cycle, For the previous operation cycle, The optimal output should be selected. The integral gain parameter is limited by over-temperature protection.

[0061] In step S1, the overpressure protection limiting module selects the compressor outlet pressure value as the calculation condition and calculates the maximum compressor inlet pressure protection limit according to the calculation formula of the overpressure protection limiting module. The calculation formula of the overpressure protection limiting module is as follows:

[0062]

[0063] In the formula: Output is limited by the maximum compressor outlet pressure protection. The maximum withstandable compressor outlet pressure value, This is the current compressor outlet pressure value. The proportional gain parameter is for overpressure protection limits. The optimal output should be selected. The integral gain parameter is limited by overpressure protection. The intermediate value of integral adjustment for overpressure protection limit;

[0064] in, The calculation formula is:

[0065]

[0066] In the formula: For the current calculation cycle, For the previous operation cycle, The optimal output should be selected. The integral gain parameter is used to limit overpressure protection.

[0067] In step S1, the overspeed protection limit module selects the gas generator speed as the calculation condition and calculates the maximum gas generator speed protection limit according to the calculation formula of the overspeed protection limit module. The calculation formula of the overspeed protection limit module is as follows:

[0068]

[0069] In the formula: Output is limited to protect the maximum gas generator speed. The maximum speed that the gas generator can withstand. This is the current gas generator speed value. The proportional gain parameter is for overspeed protection limits. The optimal output should be selected. The integral gain parameter is the overspeed protection limit. The integral adjustment intermediate value for over-rev protection limit;

[0070] in, The calculation formula is:

[0071]

[0072] In the formula: For the current calculation cycle, For the previous operation cycle, The optimal output should be selected. The integral gain parameter is used to limit overspeed protection.

[0073] In step S2, the fuel quantity boundary limit module selects the minimum fuel limit as the calculation condition and calculates the minimum fuel quantity limit according to the calculation formula of the fuel quantity boundary limit module.

[0074] In step S3, the fuel quantity boundary limit module selects the maximum fuel limit as the calculation condition and calculates the maximum fuel quantity limit according to the calculation formula of the fuel quantity boundary limit module. The calculation formula of the fuel quantity boundary limit module is as follows:

[0075]

[0076] In the formula: To limit output for fuel boundary protection, This is the maximum tolerable fuel boundary value. For fuel flow requirements, The proportional gain parameter is used to limit the fuel quantity boundary.

[0077] In step S1, the transition state boundary limit module selects the gas generator speed acceleration rate limit and the power turbine speed acceleration rate limit as calculation conditions, and calculates the gas generator acceleration rate fuel quantity limit and the power turbine acceleration rate fuel quantity limit according to the calculation formula of the transition state boundary limit module.

[0078] In step S2, the transition state boundary constraint module selects the gas generator speed reduction rate and fuel quantity limit as the calculation condition, and calculates the gas generator speed reduction rate and fuel quantity limit according to the calculation formula of the transition state boundary constraint module. The calculation formula of the transition state boundary constraint module is as follows:

[0079]

[0080] In the formula: Output is limited for speed protection. This is the maximum tolerable speed value. This is the current rotational speed value. The proportional gain parameter is the boundary constraint of the transition state. The optimal output should be selected. The integral gain parameter is constrained by the transition state boundary. The intermediate quantity for integral adjustment of the transition state boundary constraint;

[0081] in, The calculation formula is:

[0082]

[0083] In the formula: For the current calculation cycle, For the previous operation cycle, The optimal output should be selected. The integral gain parameter is constrained by the transition state boundary.

[0084] In step S1, the fuel main control module selects the gas generator speed and the power turbine speed as calculation conditions, and calculates the fuel quantity control output for the gas generator speed and the fuel quantity control output for the power turbine speed according to the calculation formula of the fuel main control module. The calculation formula of the fuel main control module is as follows:

[0085]

[0086] In the formula: This is the main control output for fuel quantity. For the target speed value, This is the current rotational speed value. The proportional gain parameter for the main fuel control. The optimal output should be selected. The integral gain parameter for the main fuel control. This is the intermediate quantity for the integral regulation of the main fuel control.

[0087] in, The calculation formula is:

[0088]

[0089] In the formula: For the current calculation cycle, For the previous operation cycle, The optimal output should be selected. This refers to the integral gain parameter for the main fuel control.

[0090] In step S4, the optimal selection logic module selects the optimal selection output from step S3 and the fuel flow requirement from the previous operation cycle, and calculates the fuel flow requirement for the current operation cycle according to the fuel flow requirement calculation formula. The fuel flow requirement calculation formula is as follows:

[0091]

[0092] In the formula: The fuel flow requirement for the current computing cycle. The optimal output for the current computation cycle. This represents the fuel flow requirement for the previous operating cycle.

[0093] This invention calculates the required fuel quantity for the current operating condition based on the gas generator speed and the power turbine speed. It then limits and protects the fuel quantity based on the temperature and pressure the gas turbine can withstand. Furthermore, it considers the gas turbine's acceleration limitations, low fuel level causing flameout, and fuel oversaturation, achieving comprehensive protection. During normal operation, the fuel quantity can be controlled according to the speed to ensure stable gas turbine operation. It also ensures safe operation of the gas turbine during start-up / shutdown transitions and when the turbine experiences over-temperature or over-pressure conditions. This invention allows for dynamic adaptation to different operating conditions by selecting different relevant parameters. It also allows for adjusting the parameters input to the relevant protection and limiting modules and the main control parameters according to different gas turbine models, making it applicable to various turbine types. Protection and limiting modules can be easily added or removed without affecting the main control framework.

[0094] The various component embodiments of the present invention can be implemented in hardware, or as software modules running on one or more processors, or a combination thereof. Those skilled in the art will understand that microprocessors or distributed controllers can be used in practice to implement some or all of the functions of some or all of the components in the device of the embodiments of the present invention. The present invention can also be implemented as a device or apparatus program that performs some or all of the methods described herein.

Claims

1. A gas turbine fuel regulation and condition protection control method applied to a gas turbine fuel regulation and condition protection control device, the gas turbine fuel regulation and condition protection control device comprising a gas turbine unit and a fuel controller, the gas turbine unit comprising a gas generator and a power turbine, the gas generator comprising a compressor, an output end of the gas turbine unit being connected with an input end of the fuel controller, an output end of the fuel controller being connected with an input end of the gas turbine unit and an input end of the fuel controller respectively, the fuel controller comprising an over-temperature protection limiting module, an over-pressure protection limiting module, an over-speed protection limiting module, a fuel quantity boundary limiting module, a transition state boundary limiting module, a fuel main control module and an optimal selection logic module, characterized in that, Includes the following steps: S1. The fuel controller calculates the maximum compressor inlet temperature protection limit, the maximum power turbine inlet temperature protection limit, the maximum compressor inlet pressure protection limit, the maximum gas generator speed protection limit, the gas generator acceleration rate fuel quantity limit, the power turbine acceleration rate fuel quantity limit, the gas generator speed fuel quantity control output, and the power turbine speed fuel quantity control output, and then takes out the minimum value among them. S2. The fuel controller calculates the minimum fuel quantity limit and the fuel quantity limit of the gas generator deceleration rate, respectively. The minimum fuel quantity limit and the fuel quantity limit of the gas generator deceleration rate are compared with the minimum value obtained in step S1, and the maximum value among the three is obtained. S3. The fuel controller calculates the maximum fuel limit, compares the maximum fuel limit with the maximum value obtained in step S2, and takes the minimum value between the two. This minimum value is the optimal selection output. S4. The optimal selection logic module calculates the fuel flow requirement for the current operation cycle and outputs it to the input terminals of the gas turbine unit and the fuel controller. S5. The gas turbine unit feeds back the operating status values ​​of the gas generator and power turbine to the fuel controller, and at the same time feeds back the fuel flow demand and optimal selection output to the fuel controller, which then performs the calculation for the next cycle.

2. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S1, the over-temperature protection limiting module selects the power turbine inlet temperature and the compressor outlet temperature as calculation conditions, and calculates the maximum compressor inlet temperature protection limit and the maximum power turbine inlet temperature protection limit according to the calculation formula of the over-temperature protection limiting module. The calculation formula of the over-temperature protection limiting module is as follows: In the formula: Output is limited to maximum temperature protection. This is the maximum tolerable temperature value. This is the current temperature value. The proportional gain parameter is limited by over-temperature protection. The optimal output should be selected. The integral gain parameter is limited by over-temperature protection. The integral adjustment intermediate value is used for over-temperature protection limits.

3. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S1, the overpressure protection limiting module selects the compressor outlet pressure value as the calculation condition and calculates the maximum compressor inlet pressure protection limit according to the calculation formula of the overpressure protection limiting module. The calculation formula of the overpressure protection limiting module is as follows: In the formula: Output is limited by the maximum compressor outlet pressure protection. The maximum withstandable compressor outlet pressure value, This is the current compressor outlet pressure value. The proportional gain parameter is for overpressure protection limits. The optimal output should be selected. The integral gain parameter is limited by overpressure protection. The integral adjustment intermediate value is used to limit overpressure protection.

4. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S1, the overspeed protection limit module selects the gas generator speed as the calculation condition and calculates the maximum gas generator speed protection limit according to the calculation formula of the overspeed protection limit module. The calculation formula of the overspeed protection limit module is as follows: In the formula: Output is limited to protect the maximum gas generator speed. The maximum speed that the gas generator can withstand. This is the current gas generator speed value. The proportional gain parameter is for overspeed protection limits. The optimal output should be selected. The integral gain parameter is the overspeed protection limit. This is the intermediate value for integral adjustment to limit over-rev protection.

5. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S2, the fuel quantity boundary limit module selects the minimum fuel limit as the calculation condition and calculates the minimum fuel quantity limit according to the calculation formula of the fuel quantity boundary limit module. In step S3, the fuel quantity boundary limit module selects the maximum fuel limit as the calculation condition and calculates the maximum fuel quantity limit according to the calculation formula of the fuel quantity boundary limit module. The calculation formula of the fuel quantity boundary limit module is as follows: In the formula: To limit output for fuel boundary protection, This is the maximum tolerable fuel boundary value. For fuel flow requirements, The proportional gain parameter is used to limit the fuel quantity boundary.

6. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S1, the transition state boundary limit module selects the gas generator speed acceleration rate limit and the power turbine speed acceleration rate limit as calculation conditions, and calculates the gas generator acceleration rate fuel quantity limit and the power turbine acceleration rate fuel quantity limit according to the calculation formula of the transition state boundary limit module. In step S2, the transition state boundary constraint module selects the gas generator speed reduction rate and fuel quantity limit as the calculation condition, and calculates the gas generator speed reduction rate and fuel quantity limit according to the calculation formula of the transition state boundary constraint module. The calculation formula of the transition state boundary constraint module is as follows: In the formula: Output is limited for speed protection. This is the maximum tolerable speed value. This is the current rotational speed value. The proportional gain parameter is the boundary constraint of the transition state. The optimal output should be selected. The integral gain parameter is constrained by the transition state boundary. This is an intermediate quantity used for integral adjustment to constrain the transition state boundary.

7. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S1, the fuel main control module selects the gas generator speed and the power turbine speed as calculation conditions, and calculates the fuel quantity control output for the gas generator speed and the fuel quantity control output for the power turbine speed according to the calculation formula of the fuel main control module. The calculation formula of the fuel main control module is as follows: In the formula: This is the main control output for fuel quantity. For the target speed value, This is the current rotational speed value. The proportional gain parameter for the main fuel control. The optimal output should be selected. The integral gain parameter for the main fuel control. This is the intermediate quantity for integral regulation of the main fuel control.

8. The gas turbine fuel regulation and condition protection control method according to claim 1, characterized in that, In step S4, the optimal selection logic module selects the optimal selection output from step S3 and the fuel flow requirement from the previous operation cycle, and calculates the fuel flow requirement for the current operation cycle according to the fuel flow requirement calculation formula. The fuel flow requirement calculation formula is as follows: In the formula: The fuel flow requirement for the current computing cycle. The optimal output for the current computation cycle. This represents the fuel flow requirement for the previous operating cycle.

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