Forward design method of low calorific value gas turbine based on performance knowledge graph

Abstract

The present invention discloses a forward design method for a low calorific value gas turbine based on a performance knowledge graph. According to the forward design task, the design input parameters of the low calorific value fuel are determined, and the design target is set; the characteristic parameters are determined, and the performance knowledge graph of the low calorific value gas turbine is established, and a dynamic balance iterative optimization design is performed to obtain the performance knowledge graph parameters with the best efficiency; the dynamic balance iterative optimization design is performed under variable operating conditions of the coal gas flow, and the performance knowledge graph parameters with the best efficiency within the variable operating range are obtained. The present invention realizes forward design throughout the life cycle, improves the operating economy of the low calorific value gas turbine, and can effectively deal with the problems of large variation range of low calorific value fuel flow generated in the process flow, inability to fully utilize, low efficiency and poor flexibility of the low calorific value gas turbine designed by reverse modification.

Description

Technical Field

[0001] The present invention relates to a gas turbine design method in the field of low calorific value gas turbines, and in particular to a low calorific value gas turbine forward design method based on a performance knowledge graph. Background Art

[0002] Low calorific value gas turbines can use low-grade energy in the process flow, which plays an important role in the cascade utilization of comprehensive energy, multi-energy complementarity, and climate change response. Gas turbines are called the crown jewel of high-end equipment manufacturing. They have the characteristics of high temperature, high pressure, and high speed. In particular, the strong nonlinear dynamic matching of the three major components of the air compressor, combustion chamber, and turbine is a difficulty in forward design. Low calorific value gas turbines have added a gas compressor to the same shaft system, which further increases the difficulty of forward design.

[0003] Traditional low calorific value gas turbines are mainly based on the reverse modification design of natural gas gas turbines. Affected by the limitations of the compressor, combustion chamber, turbine structure and performance parameters of the parent natural gas gas turbine, the process gas flow rate varies greatly, and the process gas cannot be fully utilized. The low calorific value gas turbine with reverse modification design has low efficiency, low reliability and poor design flexibility.

[0004] Forward design of high-efficiency, high-reliability and high-flexibility low calorific value gas turbines under a wide range of fluctuations in process parameters is an urgent need for the comprehensive and efficient utilization of low calorific value gas. Summary of the invention

[0005] In order to solve the problems existing in the background technology, the present invention provides a forward design method for a low calorific value gas turbine based on a performance knowledge graph, establishes a performance knowledge graph of the relationship between the node pressure, temperature, flow, and enthalpy of the low calorific value gas turbine, establishes a coupling relationship between the efficiency of the low calorific value gas turbine and the gas bypass flow ratio and conventional design parameters, improves the utilization rate of the process gas, and forward designs a low calorific value gas turbine with high efficiency, high reliability, and high flexibility under large changes in process parameters.

[0006] To achieve the above purpose, the technical solution adopted by the present invention to solve the technical problem is:

[0007] Step 1: According to the forward design task of the low calorific value gas turbine, determine the design input parameters of the low calorific value fuel in the process and set the design target of the low calorific value gas turbine;

[0008] Step 2: Determine the characteristic parameters such as the pressure ratio and efficiency of the gas compressor, the pressure ratio and efficiency of the air compressor, the pressure loss and efficiency of the combustion chamber, the expansion ratio and efficiency of the turbine, and the secondary air ratio, and establish a performance knowledge graph of the low calorific value gas turbine. The performance knowledge graph includes the node relationship of the components of the low calorific value gas turbine.

[0009] Step 3: Perform dynamic balance iterative optimization design based on the performance knowledge graph of the low calorific value gas turbine to obtain the performance knowledge graph parameters with the best efficiency of the low calorific value gas turbine;

[0010] Step 4: Perform dynamic balance iterative optimization design under variable gas flow conditions, obtain the performance knowledge graph parameters with the best efficiency within the variable operating range, and complete the forward design and finalization of the low calorific value gas turbine performance parameters.

[0011] The forward design task is a process of obtaining characteristic parameters of a gas turbine by giving design parameters according to user requirements.

[0012] The low calorific value mentioned in the present invention refers to the fuel calorific value of 2.5-4.5MJ / Nm 3 scope.

[0013] In the step 1, the design input parameters of the low calorific value fuel in the process include gas composition, gas flow, design point gas flow, and gas bypass flow, wherein the gas composition and gas flow are obtained through on-site measurement;

[0014] The gas flow at the design point is calculated using the following formula:

[0015] mgd=mg ratio1 *mg max

[0016] mg max is the maximum gas flow rate generated by the process, mgd is the design point gas flow rate entering the combustion chamber of the low calorific value gas turbine, mg ratio1 The design point gas flow ratio for low calorific value gas turbines is in the range of 0.9 to 1.0;

[0017] The gas bypass flow rate is calculated based on the gas bypass flow ratio according to the following formula:

[0018] mg bypass =(mg ratio2 -1)*mg

[0019] Among them, mg ratio2 is the gas bypass flow ratio, the design value range is 1.0~1.2, mg is the gas flow rate generated by the process that changes with time, mg bypass is the gas bypass flow;

[0020] The design targets include the load, efficiency and maximum temperature of the low calorific value gas turbine, among which the load design target is 20-50MW, the efficiency design target is 25-35%, and the maximum temperature design target is 1100-1300℃.

[0021] In the specific implementation, among the design parameters of the low calorific value gas turbine, the design range of the gas compressor pressure ratio is 16-18, the design range of the gas compressor efficiency is 86-88%, the design range of the air compressor pressure ratio is 15-17, the design range of the air compressor efficiency is 87-89%, the design range of the combustion chamber pressure loss is 3-4%, and the design range of the combustion chamber efficiency is 99.7-99.9%. The design range of the turbine expansion ratio is 12-15, and the design range of the turbine efficiency is 88-90%. The design range of the secondary air ratio for cooling the turbine stator blades is 4-6%, and the design range of the secondary air ratio for cooling the turbine rotor is 6-7%.

[0022] The step three is specifically: performing an iterative design of gas flow balance on the low calorific value gas turbine performance knowledge graph, and establishing a coupling relationship f1 between the efficiency of the low calorific value gas turbine and the design parameters:

[0023] η GT =f1(mg ratio1 ,π c ,η c ,π gc ,η gc ,d p ,η cb ,π T ,η T ,SAS V ,SAS R )

[0024] Among them, η GT The efficiency of low calorific value gas turbine, conventional design parameters include design point gas flow ratio mg ratio1 , the pressure ratio of the gas compressor π gc and efficiency η gc 、Compression ratio of air compressor π c and efficiency η c , Combustion chamber pressure loss d p and efficiency η cb 、Turbine expansion ratio π T and efficiency η T , Turbine stator cooling secondary air ratio SAS V , Turbine rotor cooling secondary air ratio SAS R ,The particle swarm optimization algorithm is used to obtain the optimal design parameter combination for the efficiency of low calorific value gas turbine.

[0025] The step 4 is specifically: performing dynamic balance iterative design on the gas flow variable working condition, and establishing a coupling relationship f2 between the efficiency of the low calorific value gas turbine and the gas bypass flow ratio and conventional design parameters:

[0026] η GT =f2(mg ratio2 ,mgratio1 ,π c ,η c ,π gc ,η gc ,d p ,η cb ,π T ,η T ,SAS V ,SAS R )

[0027] Among them, mg ratio2 Indicates the gas bypass flow ratio;

[0028] The particle swarm optimization algorithm is used to obtain the performance knowledge graph parameters with the best efficiency of the low calorific value gas turbine under variable operating conditions. The performance knowledge graph parameters include the gas bypass flow ratio mg ratio2 , Design point gas flow ratio mg ratio1 , the pressure ratio of the gas compressor π gc and efficiency η gc 、Compression ratio of air compressor π c and efficiency η c , Combustion chamber pressure loss d p and efficiency η cb 、Turbine expansion ratio π T and efficiency η T , Turbine stator cooling secondary air ratio SAS V , Turbine rotor cooling secondary air ratio SAS R , gas turbine efficiency η GT , load P, heat consumption He, and the thermodynamic parameters of the relationship between the low calorific value gas turbine inlet chamber, air compressor, gas compressor, combustion chamber, turbine inlet and outlet nodes, including pressure p, temperature T, flow rate m, enthalpy value H, to complete the forward design and finalization of the low calorific value gas turbine performance parameters.

[0029] During the specific implementation, the knowledge graph of low calorific value gas turbine performance is also updated in real time and dynamically to realize the full life cycle forward design of low calorific value gas turbines.

[0030] Acquire real-time low calorific value gas turbine operation data, dynamically update the performance knowledge graph of low calorific value gas turbines, realize forward design throughout the life cycle from the conceptual design stage to the operation and maintenance design stage, and improve the operation economy of low calorific value gas turbines.

[0031] The present invention realizes forward design throughout the entire life cycle, improves the operating economy of the low calorific value gas turbine, and can effectively address the problems of large variation range of low calorific value fuel flow generated in the process flow, inability to fully utilize, low efficiency and poor flexibility of the low calorific value gas turbine with reverse modification design.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] The present invention can flexibly and forwardly design a low calorific value gas turbine according to the process parameters of the low calorific value coal gas, without relying on a natural gas gas turbine of a related load level as a design prototype.

[0034] The low calorific value gas turbine designed forward under a wide range of process gas parameter changes has high efficiency, high reliability and high flexibility.

[0035] The present invention realizes forward design throughout the entire life cycle, from the conceptual design stage to the operation and maintenance design stage. It can dynamically update the low calorific value gas turbine performance knowledge map according to changes in process flow parameters, improve the operating economy of the low calorific value gas turbine, and control it to operate at a higher efficiency level within the dynamic variable operating conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a flow chart of the forward design method of low calorific value gas turbine based on performance knowledge graph.

[0037] Figure 2 It is the overall block diagram of the thermodynamic structure of a low calorific value gas turbine.

[0038] Figure 3 It is a schematic diagram of the parameters of the knowledge graph of low calorific value gas turbine performance.

[0039] Figure 4 It is a schematic diagram of the process flow and calorific value changing with time.

[0040] Figure 5 This is a schematic diagram of the change of load and speed of a low calorific value gas turbine over time.

[0041] Figure 6 This is a schematic diagram of the changes in gas bypass flow and gas turbine efficiency over time. DETAILED DESCRIPTION

[0042] The present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that the described embodiments are only intended to facilitate the understanding of the present invention and do not have any limiting effect on the present invention.

[0043] like Figure 2As shown, the gas turbine specifically implemented includes a radial air inlet chamber 1, an air compressor 2, a combustion chamber 3, a turbine 4, a generator 5 and a blast furnace gas compressor 6; the outlet of the radial air inlet chamber 1 is connected to the inlet of the air compressor 2, the outlet of the air compressor 2 is respectively connected to the inlet of the combustion chamber 3 and the air inlet of the turbine 4, the rotating shafts of the air compressor 2, the turbine 4, the rotating shafts of the generator 5, and the rotating shafts of the blast furnace gas compressor 6 are synchronously connected, the outlet of the blast furnace gas compressor 6 is connected to the inlet of the combustion chamber 3, the outlet of the combustion chamber 3 is connected to the air inlet of the turbine 4, and the outlet of the blast furnace gas compressor 6 is simultaneously connected to the inlet of the blast furnace gas compressor 6 through a gas bypass valve 9. By adjusting the opening of the gas bypass valve 9, the gas flow rate entering the combustion chamber 3 from the outlet of the blast furnace gas compressor 6 can be controlled. The inlet of the blast furnace gas compressor is connected to a blast furnace gas boiler 11 through a gas control valve 10. When the blast furnace gas flow rate generated in the process is greater than the maximum gas consumption of the gas turbine, the excess blast furnace gas is burned in the gas boiler 11 to prevent direct discharge into the atmosphere to pollute the environment.

[0044] The blast furnace gas compressor 6 inputs low calorific value blast furnace gas at the inlet, and the low calorific value gas is compressed by the blast furnace gas compressor 6 and then input into the combustion chamber 3. The medium calorific value coke oven gas 7 is input into the combustion chamber 3 when the combustion chamber 3 is ignited. Air is input into the radial air inlet chamber 1 inlet, and the air enters the air compressor 2 through the radial air inlet chamber 1. The air is compressed by the air compressor 2 and then outputs high-pressure air. The high-pressure air is divided into two paths, one path is directly input into the combustion chamber 3 as the main combustion air, and the high-temperature gas is output by the combustion chamber 3, and the other path is input into the turbine 4 together with the high-temperature gas output by the combustion chamber 3 as the secondary air 8. The turbine 4 works with the high-temperature gas and is cooled by the secondary air 8, and exhausts gas at the outlet of the turbine 4.

[0045] The gas turbine includes four major rotating parts: an air compressor 2, a turbine 4, a generator 5 and a blast furnace gas compressor 6. Figure 2 In the figure, the dotted lines represent the thermodynamic flow process of air and fuel, and the solid lines represent the rotor shaft connection.

[0046] like Figure 1 As shown, the embodiments of the present invention and their implementation process are as follows:

[0047] Step 1: According to the forward design task of the low calorific value gas turbine, determine the design input parameters of the low calorific value fuel in the process and set the design target of the low calorific value gas turbine;

[0048] Step 2: Determine the characteristic parameters such as the pressure ratio and efficiency of the gas compressor, the pressure ratio and efficiency of the air compressor, the pressure loss and efficiency of the combustion chamber, the expansion ratio and efficiency of the turbine, and the secondary air ratio, and establish a performance knowledge graph of the low calorific value gas turbine. The performance knowledge graph includes the node relationship of the components of the low calorific value gas turbine.

[0049] Step 3: Perform dynamic balance iterative optimization design based on the performance knowledge graph of the low calorific value gas turbine to obtain the performance knowledge graph parameters with the best efficiency of the low calorific value gas turbine;

[0050] Step 4: Perform dynamic balance iterative optimization design under variable gas flow conditions, obtain the performance knowledge graph parameters with the best efficiency within the variable operating range, and complete the forward design and finalization of the low calorific value gas turbine performance parameters.

[0051] Further: in said step 1,

[0052] The design input parameters of low calorific value fuel in the process include gas composition, gas flow, design point gas flow, and gas bypass flow, among which the gas composition and gas flow are obtained through on-site measurement.

[0053] The gas flow at the design point is calculated using the following formula:

[0054] mgd=mg ratio1 *mg max

[0055] mg max is the maximum gas flow rate generated by the process, mgd is the design point gas flow rate entering the combustion chamber of the low calorific value gas turbine, mg ratio1 The design point gas flow ratio for low calorific value gas turbines has a design value range of 0.9 to 1.0.

[0056] The gas bypass flow rate is calculated based on the gas bypass flow ratio according to the following formula:

[0057] mg bypass =(mg ratio2 -1)*mg

[0058] Among them, mg ratio2 is the gas bypass flow ratio, the design value range is 1.0~1.2, mg is the gas flow rate generated by the process that changes with time, mg bypass is the gas bypass flow;

[0059] The design targets include the load, efficiency and maximum temperature of the low calorific value gas turbine, among which the load design target is 20-50MW, the efficiency design target is 25-35%, and the maximum temperature design target is 1100-1300℃.

[0060] Further: in said step 2,

[0061] Based on the conservation of pressure, load, flow conservation and the value range of design parameters among the nodes of the four major components of the low calorific value gas turbine, a performance knowledge graph of the relationship between pressure, temperature and flow of the low calorific value gas turbine nodes is established, and the design criteria for the value range of the characteristic variable correlation relationship are established. The four major components of the low calorific value gas turbine include air compressor, gas compressor, combustion chamber and turbine.

[0062] Among the design parameters of low calorific value gas turbine, the design range of gas compressor pressure ratio is 16-18, the design range of gas compressor efficiency is 86-88%, the design range of air compressor pressure ratio is 15-17, the design range of air compressor efficiency is 87-89%, the design range of combustion chamber pressure loss is 3-4%, and the design range of combustion chamber efficiency is 99.7-99.9%. The design range of turbine expansion ratio is 12-15%, and the design range of turbine efficiency is 88-90%. The design range of secondary air ratio for turbine stator cooling is 4-6%, and the design range of secondary air ratio for turbine rotor cooling is 6-7%.

[0063] Further: in said step three,

[0064] The gas flow balance is iteratively designed for the low calorific value gas turbine performance knowledge graph, and the coupling relationship between the efficiency and design parameters of the low calorific value gas turbine is established:

[0065] η GT =f1(mg ratio1 ,π c ,η c ,π gc ,η gc ,d p ,η cb ,π T ,η T ,SAS V ,SAS R )

[0066] Among them, η GT The efficiency of low calorific value gas turbine, conventional design parameters include design point gas flow ratio mg ratio1 , the pressure ratio of the gas compressor π gc and efficiency η gc 、Compression ratio of air compressor π c and efficiency η c , Combustion chamber pressure loss d p and efficiency η cb 、Turbine expansion ratio π T and efficiency η T , Turbine stator cooling secondary air ratio SAS V , Turbine rotor cooling secondary air ratio SAS R,The particle swarm optimization algorithm is used to obtain the optimal design parameter combination for the efficiency of low calorific value gas turbine.

[0067] Further: in the step 4,

[0068] The dynamic balance iteration design is carried out for the variable gas flow conditions, and the coupling relationship f2 between the efficiency of the low calorific value gas turbine and the gas bypass flow ratio and conventional design parameters is established:

[0069] η GT =f2(mg ratio2 ,mg ratio1 ,π c ,η c ,π gc ,η gc ,d p ,η cb ,π T ,η T ,SAS V ,SAS R )

[0070] Among them, mg ratio2 Indicates the gas bypass flow ratio;

[0071] The particle swarm optimization algorithm is used to obtain the performance knowledge graph parameters with the best efficiency of the low calorific value gas turbine under variable operating conditions. The performance knowledge graph parameters include the gas bypass flow ratio mg ratio2 , Design point gas flow ratio mg ratio1 , the pressure ratio of the gas compressor π gc and efficiency η gc 、Compression ratio of air compressor π c and efficiency η c , Combustion chamber pressure loss d p and efficiency η cb 、Turbine expansion ratio π T and efficiency η T , Turbine stator cooling secondary air ratio SAS V , Turbine rotor cooling secondary air ratio SAS R , gas turbine efficiency η GT , load P, heat consumption He, and the thermodynamic parameters of the relationship between the low calorific value gas turbine inlet chamber, air compressor, gas compressor, combustion chamber, turbine inlet and outlet nodes, including pressure p, temperature T, flow rate m, enthalpy value H, to complete the forward design and finalization of the low calorific value gas turbine performance parameters.

[0072] like Figure 3As shown in the figure, in the parameters of the low calorific value gas turbine performance knowledge map, m represents flow, p represents pressure, T represents temperature, and H represents enthalpy. The maximum flow rate of coal gas generated by the process is 57.1 kg / s, and the calorific value of coal gas is 3.142 MJ / Nm 3 The calorific value of the gas is obtained by measuring and converting the gas components. At this time, the design point flow rate of the low calorific value gas turbine gas is 56kg / s, the design point gas flow ratio is 0.98, the gas compressor inlet flow rate is 56.5kg / s, the gas bypass flow rate is 0.5kg / s, the gas bypass flow ratio is 1.01, the overall efficiency of the low calorific value gas turbine is 30.5%, the load is 40MW, the maximum temperature is 1200℃, and the heat consumption is 11803kJ / kwh.

[0073] When the gas flow rate generated by the process exceeds the design point flow rate of the low calorific value gas turbine of 56 kg / s, the excess gas enters the blast furnace gas boiler 11 through the gas control valve 10 for combustion; when the gas flow rate generated by the process is less than the design point flow rate of the low calorific value gas turbine of 56 kg / s, the gas control valve 10 is closed, and all the gas generated by the process enters the gas turbine combustion chamber 3 for combustion. At this time, the gas bypass volume of the gas bypass valve 9 is 0.5 kg / s, which is used as a benchmark for dynamic balance control of the flow rate when the low calorific value gas turbine changes operating conditions.

[0074] Further:

[0075] like Figure 4 As shown in the figure, over a period of time, the gas flow rate generated by the process varies from 40.7 to 57.1 kg / s, and the gas calorific value varies from 3.05 to 3.24 MJ / Nm 3 .

[0076] like Figure 5 As shown, during a period of time, the gas turbine load changes in the range of 45-100%, and the speed operates stably near the full speed range of 100%.

[0077] like Figure 6 As shown, within a period of time, the coal gas bypass flow ratio varies from 1.01 to 1.09, and the gas turbine efficiency varies from 21.2 to 30.5%.

[0078] Acquire the existing low calorific value gas turbine operating data, dynamically update the low calorific value gas turbine performance knowledge map, realize the forward design of the entire life cycle from the conceptual design stage to the operation and maintenance design stage, and improve the operating economy of the low calorific value gas turbine.

Claims

1. A forward design method for a low calorific value gas turbine based on a performance knowledge graph, characterized in that: The method comprises the following steps: Step 1: According to the forward design task of the low calorific value gas turbine, determine the design input parameters of the low calorific value fuel in the process and set the design target of the low calorific value gas turbine; Step 2: Determine the gas compressor pressure ratio and efficiency, air compressor pressure ratio and efficiency, combustion chamber pressure loss and efficiency, turbine expansion ratio and efficiency, and secondary air ratio characteristic parameters, and establish a performance knowledge map of the low calorific value gas turbine; Step 3: Perform dynamic balance iterative optimization design based on the performance knowledge graph of the low calorific value gas turbine to obtain the performance knowledge graph parameters with the best efficiency of the low calorific value gas turbine; Step 4: Perform dynamic balance iterative optimization design under variable gas flow conditions, obtain the performance knowledge graph parameters with the best efficiency within the variable operating range, and complete the forward design finalization of the low calorific value gas turbine performance parameters; The step three is specifically: performing an iterative design of gas flow balance on the low calorific value gas turbine performance knowledge graph, and establishing a coupling relationship f1 between the efficiency of the low calorific value gas turbine and the design parameters: h GT =f1(mg ratio1 ,π c ,h c ,π gc ,h gc ,d p ,h cb ,π T ,h T ,SAS V ,SAS R ) Among them, h GT The efficiency of low calorific value gas turbine, conventional design parameters include design point gas flow ratio mg ratio1 , the pressure ratio of the gas compressor π gc and efficiency h gc 、Compression ratio of air compressor π c and efficiency h c , Combustion chamber pressure loss d p and efficiency h cb 、Turbine expansion ratio π T and efficiency h T , Turbine stator cooling secondary air ratio SAS V , Turbine rotor cooling secondary air ratio SAS R , using particle swarm optimization algorithm to obtain the optimal design parameter combination for the efficiency of low calorific value gas turbine; The step 4 is specifically: performing dynamic balance iterative design on the gas flow variable working condition, and establishing a coupling relationship f2 between the efficiency of the low calorific value gas turbine and the gas bypass flow ratio and conventional design parameters: h GT =f2(mg ratio2 ,mg ratio1 ,π c ,h c ,π gc ,h gc ,d p ,h cb ,π T ,h T ,SAS V ,SAS R ) Among them, mg ratio2 Indicates the gas bypass flow ratio; The particle swarm optimization algorithm is used to obtain the performance knowledge graph parameters with the best efficiency of the low calorific value gas turbine under variable operating conditions. The performance knowledge graph parameters include the gas bypass flow ratio mg ratio2 , Design point gas flow ratio mg ratio1 , the pressure ratio of the gas compressor π gc and efficiency h gc 、Compression ratio of air compressor π c and efficiency h c , Combustion chamber pressure loss d p and efficiency h cb 、Turbine expansion ratio π T and efficiency h T , Turbine stator cooling secondary air ratio SAS V , Turbine rotor cooling secondary air ratio SAS R , gas turbine efficiency h GT , load P, heat consumption He, and the thermodynamic parameters of the relationship between the low calorific value gas turbine inlet chamber, air compressor, gas compressor, combustion chamber, turbine inlet and outlet nodes, including pressure p, temperature T, flow rate m, enthalpy value H, to complete the forward design and finalization of the low calorific value gas turbine performance parameters.

2. The low calorific value gas turbine forward design method based on performance knowledge graph according to claim 1 is characterized in that: In the step 1, the design input parameters of the low calorific value fuel in the process include gas composition, gas flow, design point gas flow, and gas bypass flow, wherein the gas composition and gas flow are obtained through on-site measurement; The gas flow at the design point is calculated using the following formula: mgd=mg ratio1 *mg max mg max is the maximum gas flow rate generated by the process, mgd is the design point gas flow rate entering the combustion chamber of the low calorific value gas turbine, mg ratio1 Design point gas flow ratio for low calorific value gas turbine; The gas bypass flow rate is calculated based on the gas bypass flow ratio according to the following formula: mg bypass =(mg ratio2 -1)*mg Among them, mg ratio2 is the gas bypass flow rate ratio, mg is the gas flow rate generated by the process that varies with time, mg bypass is the gas bypass flow; Design objectives include load, efficiency and maximum temperature of the LCV gas turbine.

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