Test system and test method for determining atomized gas parameters of combustion chamber of gas turbine

Abstract

The invention aims to provide a test system and a test method for determining atomized gas parameters of a combustion chamber of a gas turbine, and belongs to the field of gas turbines. The method comprises the steps that main air and atomization are prepared, liquid fuel ignition and judgment are conducted, if ignition fails, the fuel quantity is increased till ignition succeeds, parameters are adjusted to the target working condition, the initial performance of a combustion chamber is recorded, and atomization gas parameters are adjusted to evaluate the performance of the combustion chamber. The optimal atomizing gas pressure parameter interval intersection with various performances meeting requirements is obtained, the pressure accuracy is automatically verified through a set program, verification is determined to be accurate when the absolute value of the relative deviation of a result is smaller than a certain specified value, other working condition parameters are adjusted to be tested again, and a combustion chamber full-working-condition optimal atomizing gas pressure parameter working zone is formed. The method is wide in applicable parameter range and high in precision, and can be widely applied to multi-type gas turbine combustion chambers such as dual-fuel and low-emission gas turbine combustion chambers using fuel containing liquid fuel.

Description

Technical Field

[0001] The present invention relates to a test system and a test method, in particular to a test system and a test method for a combustion chamber. Background Art

[0002] Liquid fuel gas turbines were developed and applied earlier. With the development of technology and the popularization of gas fuels, gas fuel gas turbines and dual-fuel gas turbines have gradually emerged. At present, the combustion technology of gas turbines containing liquid fuels is still under extensive and in-depth research and exploration. Specific research directions include liquid fuel efficient atomization combustion technology, liquid fuel low-emission combustion technology, and low-emission dual-fuel combustion technology. These advanced technologies still have urgent application needs.

[0003] When using a gas turbine combustion chamber containing liquid fuel, the liquid fuel is often atomized and evaporated by gas-assisted atomization, centrifugal nozzles, and strong swirl design. After the liquid fuel is converted into gas phase, a stable and sufficient combustion reaction is carried out to achieve efficient combustion reaction of the liquid fuel under gas phase conditions. A good liquid fuel atomization process is an important prerequisite for maintaining a continuous and stable combustion flame. Among the liquid fuel atomization technical means, the gas-assisted atomization method can achieve a good combustion effect under the condition that the parameters are fully determined. However, in the actual design process, it is difficult to determine the optimal atomizing gas pressure, flow rate and other parameters. If the actual pressure is too small, the atomization effect cannot be achieved, the combustion efficiency is low, and there is black smoke. If the actual pressure is too large, the liquid fuel may be carried to the tail of the combustion chamber by the high-speed gas, causing failures such as guide vane overheating and flame tube ablation, which may seriously cause major losses. Therefore, the determination of the liquid fuel atomizing gas parameters is a more difficult challenge for new combustion chambers without a prototype, especially for the combustion process that requires the participation of atomizing gas in all working conditions. At present, there is no report on a better atomizing gas parameter determination scheme.

[0004] On the other hand, the combustion process of liquid fuel is extremely complex. Although the current numerical simulation calculation methods can roughly simulate the combustion process, they have certain limitations in simulating the atomization, evaporation and mixing processes of liquid fuel. In particular, it is impossible to truly simulate the corresponding atomization effect for the process of accelerating the breakup of fuel droplets to achieve atomization with auxiliary atomizing gas. Therefore, it is difficult for R&D designers to determine the effect of auxiliary atomization through numerical simulation methods.

[0005] Combining the above two aspects, in the current design process of new combustion chambers, when choosing the technical route, R&D personnel generally avoid the gas-assisted atomization method and choose the multi-channel method of main and auxiliary oil circuits with small nozzles. This makes the liquid fuel supply system structure and control logic much more complicated. Especially for the R&D and design of dual-fuel combustion chambers that use fuels including gas fuel, the complexity of the fuel system composed of multiple fuel supplies and the control logic including the fuel switching process often results in the overall economic benefits not outweighing the costs, and the overall cost and risk of operational failures are also significantly increased, and it is very easy to increase the risk of failure in the development of the gas turbine as a whole. Summary of the invention

[0006] The purpose of the present invention is to provide a test system and test method for determining the atomizing gas parameters of a gas turbine combustion chamber, which can accurately and reliably determine the atomizing gas parameters of liquid fuel under all operating conditions during the design process of combustion chamber components, simplify the structure of the combustion chamber and related auxiliary systems, save costs for the development of gas turbine complete machines and reduce the risk of development failure.

[0007] The object of the present invention is achieved in that:

[0008] The present invention provides a test system for determining the atomized gas parameters of a gas turbine combustion chamber, which is characterized by comprising a test shell, a flame tube, a fuel nozzle, an igniter, a pressure pulsation sensor, a total temperature probe, a sampling probe, a flue gas analyzer, a central control computer, a liquid fuel system, a main air system, and an atomized gas system. The flame tube is installed inside the test shell, the fuel nozzle is plugged into the flame tube head and fixed on the nozzle installation inclined surface of the test shell, the liquid fuel inlet of the fuel nozzle is connected to the liquid fuel system, the atomized gas inlet of the fuel nozzle is connected to the atomized gas system, the igniter is plugged into the flame starter tube inlet of the flame tube, the probe of the pressure pulsation sensor is coaxial with the central axis of the main combustion hole position of the flame tube, the igniter and the pressure pulsation sensor are both fixed on the upper cover plate surface of the test shell, the exhaust section of the test shell is installed with a total temperature probe and a sampling probe, the sampling probe is connected to the flue gas analyzer, the air intake section of the test shell is connected to the main air system, and the igniter, the pressure pulsation sensor, the total temperature probe, the flue gas analyzer, the liquid fuel system, the main air system, and the atomized gas system are connected to the central control computer.

[0009] The test system for determining the atomizing gas parameters of a gas turbine combustion chamber of the present invention may also include:

[0010] 1. The liquid fuel system comprises a liquid fuel path, on which a liquid fuel source, a booster pump, a liquid filter, a liquid regulating valve, a liquid shut-off valve, a liquid mass flow meter, and a liquid check valve are sequentially arranged, a liquid bypass path is provided between the liquid check valve and the liquid mass flow meter, and a liquid bypass valve is installed on the liquid bypass path.

[0011] 2. The main air system includes a main air circuit, on which a main air source, a heater, an air regulating valve, an air shut-off valve, an air mass flow meter, and an air check valve are sequentially arranged. An air bypass circuit is provided between the air check valve and the air mass flow meter, and an air bypass valve is installed on the air bypass circuit.

[0012] 3. The atomizing gas system comprises an atomizing gas main circuit, a first atomizing gas branch circuit, a second atomizing gas branch circuit and a third atomizing gas branch circuit. The first atomizing gas branch circuit, the second atomizing gas branch circuit and the third atomizing gas branch circuit are connected in parallel and then connected to the atomizing gas main circuit. An atomizing gas source, a main atomizing shut-off valve, an atomizing filter and a water bath heater are sequentially arranged on the atomizing gas main circuit. An atomizing bypass circuit is provided between the water bath heater and the atomizing filter, and an atomizing bypass valve is installed on the atomizing bypass circuit. A first atomizing regulating valve, a first atomizing shut-off valve, a small-range mass flowmeter and a first atomizing check valve are sequentially arranged on the first atomizing gas branch circuit. A second atomizing regulating valve, a second atomizing shut-off valve, a medium-range mass flowmeter and a second atomizing check valve are sequentially arranged on the second atomizing gas branch circuit. A third atomizing regulating valve, a third atomizing shut-off valve, a large-range mass flowmeter and a third atomizing check valve are sequentially arranged on the third atomizing gas branch circuit.

[0013] The present invention provides a test method for determining the parameters of atomized gas in a gas turbine combustion chamber, characterized in that: using the test system for determining the parameters of atomized gas in a gas turbine combustion chamber as claimed in claim 1, the method comprises the following steps:

[0014] (1) Prepare the main air and atomizing gas: start the main air system, adjust the main air temperature, pressure and flow rate to the values ​​Ta0, Pa0 and Ga0 required for ignition conditions and keep them stable; start the atomizing gas system, select the atomizing gas branch, adjust the atomizing gas temperature, pressure and flow rate to the initial values ​​Tw0, Pw0 and Gw0 and keep them stable;

[0015] (2) Liquid fuel ignition: Open the liquid fuel supply system, start the booster pump, adjust the liquid fuel regulating valve to the target opening corresponding to the initial ignition flow Gl0A, and after the initial ignition flow Gl0A is ready to be supplied, turn on the igniter through the central control computer. After Δt s, open the liquid fuel cut-off valve to start the ignition process of liquid fuel entering the fuel nozzle and the flame tube;

[0016] (3) The central control computer performs logical judgment: if the ignition is successful, the main air and liquid fuel parameters are adjusted to the target operating condition 1 parameters, so that the temperature, pressure and flow rate of the main air are adjusted to Ta1, Pa1 and Ga1, and the liquid fuel flow rate is adjusted to the target operating condition value Gl1, and the atomizing gas parameters are stably and continuously supplied according to the initial value; if the ignition fails, the liquid fuel supply is stopped, and after the main air is purged for 3 minutes, the initial ignition flow rate is adjusted to increase to Gl0B and steps (2) and (3) are re-executed until the ignition is successful;

[0017] (4) The central control computer records the initial performance of the combustion chamber: Under target operating condition 1, the central control computer calculates the combustion efficiency η0 according to the flue gas components obtained by the flue gas analyzer according to the set program, calculates the average pressure pulsation δ0 according to the sampling data of the pressure pulsation sensor, and calculates the maximum non-uniformity OT0 and the maximum radial non-uniformity RT0 of the combustion chamber outlet temperature according to the temperature measurement results of the total temperature probe at the flame tube outlet;

[0018] (5) Adjust the atomizing gas parameters to further evaluate the combustion chamber performance: Under the above combustion chamber initial performance conditions, adjust the atomizing gas pressure parameters to evaluate the combustion efficiency η, the maximum non-uniformity OT and the maximum radial non-uniformity RT of the combustion chamber outlet temperature, the combustion chamber pressure pulsation δ and other performance parameters. The corresponding atomizing gas pressure parameters are the best working parameters: When the atomizing gas pressure changes from Pw1 to Pw2, the combustion efficiency satisfies η≥η min The requirements of combustion efficiency η, the optimal atomizing gas pressure parameter interval corresponding to the combustion efficiency η is [Pw1, Pw2], the maximum unevenness OT and the maximum radial unevenness RT of the combustion chamber outlet temperature, the upper limit index OT of the combustion chamber pressure pulsation δ max , RT max and δ max The corresponding optimal atomizing gas pressure parameter intervals are [Pw3, Pw4], [Pw5, Pw6] and [Pw7, Pw8] respectively. The central control computer performs intersection calculation on the four atomizing gas pressure parameter working intervals according to the set logic program to obtain the optimal atomizing gas pressure parameter interval that meets the requirements of the four performances.

[0019] (6) The central control computer verifies the atomizing gas pressure parameter and performs a logical judgment: if the optimal atomizing gas pressure parameter interval is [Pw5, Pw6], the central control computer verifies the atomizing gas pressure parameter according to the measured flow rates corresponding to the collected atomizing gas pressures Pw5 and Pw6, that is, the flow rate values ​​collected by the mass flow meter, where the pressure Pw5 corresponds to the measured atomizing gas flow rate Gw5, and the pressure Pw6 corresponds to the measured atomizing gas flow rate Gw6;

[0020] (7) Adjust the operating conditions and determine the atomizing gas pressure parameters for other operating conditions: Based on step (6), keep the atomizing air parameters within the optimal range [Pw5, Pw6] and adjust the target operating condition to operating condition 2, that is, adjust the temperature, pressure and flow rate of the main air to Ta2, Pa2 and Ga2, so that the liquid fuel flow rate is adjusted to the target operating condition value Gl2 and remains stable. Repeat steps (4), (5) and (6) to obtain the optimal range [Pw5, Pw6] of the optimal atomizing gas pressure parameters under operating condition 2. Similarly, the optimal atomizing gas pressure parameter working band under all operating conditions of this type of combustion chamber is finally obtained, the atomizing gas parameters are determined, and the test is ended.

[0021] The test method for determining the atomizing gas parameters of a gas turbine combustion chamber of the present invention may further include:

[0022] 1. In step (6), the atomizing gas pressure parameters are calibrated and calculated according to the following calculation procedure: Under the condition that the current pressure is Pw5, the theoretical calculated flow rate of the atomizing gas path of the fuel nozzle is calculated according to the following formula:

[0023]

[0024] The meanings of the parameters are as follows:

[0025] k is the adiabatic index, Rg is the gas constant; Pw5 is the fuel nozzle atomizing gas inlet pressure, Tw5 is the fuel nozzle atomizing gas inlet temperature, Pb is the combustion chamber inlet pressure, nozzle atomizing gas outlet pressure Pw(out)=Pb*(1-σ), where σ is the total pressure loss coefficient after the combustion chamber inlet passes through the combustion chamber inlet expansion section and the flame tube; Aw is the throttling area of ​​the fuel nozzle atomizing gas path, and α is the fuel nozzle atomizing gas path flow coefficient;

[0026] After obtaining the Gw5 (calculated) value, check it:

[0027] When the absolute value of the relative deviation of the result |(Gw5(calculated)-Gw5) / Gw5|≤β%, the logic judges that the data is reliable under the current conditions and is an accurate atomizing gas pressure parameter. Similarly, the data is accurate when the atomizing pressure is Pw6, and finally the accurate optimal atomizing gas pressure parameter interval [Pw5, Pw6] is obtained;

[0028] When the relative deviation of the result is greater than β%, the engine is turned off, relevant equipment is checked, the cause is analyzed and corrected, and the process of steps S1-S6 is repeated until the deviation is ≤ β%.

[0029] 2. The igniter start time Δt∈[10s, 15s] described in step (2) ensures reliable ignition.

[0030] 3. The combustion efficiency η described in step (5) min =99.9%, the maximum unevenness OT and maximum radial unevenness RT of the combustion chamber outlet temperature, and the upper limit index of the combustion chamber pressure pulsation δ are OT max =20%, RT max =10% and δ max =4kPa.

[0031] 4. The total pressure loss coefficient σ∈[4.9%, 5%] at the combustion chamber inlet after passing through the combustion chamber inlet diffuser section and the flame tube in step (6), the fuel nozzle atomization gas path flow coefficient α∈[0.95, 0.96], and the absolute value of the relative deviation |(Gw5(calculated)-Gw5) / Gw5|∈[0, 2%].

[0032] The advantages of the present invention are:

[0033] 1. By setting the fuel nozzle and flame tube in an independent test shell, and configuring the test system consisting of an igniter, a pressure pulsation sensor, a total temperature probe, a sampling probe, a flue gas analyzer, a liquid fuel system, a main air system and an atomizing gas system, combined with the central control computer, the optimal atomizing gas parameters under each working condition are automatically obtained under the condition of accurate atomizing parameter verification, and the accurate and reliable optimal atomizing gas pressure parameter working band of this type of combustion chamber under all working conditions is obtained. Under the condition of relatively small working input, high-precision parameter numerical results of all working conditions within a wide parameter range can be obtained, which greatly reduces the development investment and test cost of the combustion chamber and shortens the development cycle. At the same time, the verification results are reliable, effectively avoiding the risk of failure in the development of the combustion chamber, and the engineering practicability is strong and the promotion is good.

[0034] 2. The present invention fully considers the wide range and high precision accuracy of determining the atomizing gas parameters, broadens the working range of the atomizing gas parameters through multiple atomizing gas branches, determines the accuracy of the atomizing gas parameters through an automatic verification program, solves the difficulties in determining the atomizing gas parameters of the gas turbine combustion chamber and the current research and development difficulties of no effective technical solutions, greatly alleviates the shortcomings of high risk and high investment in whole machine testing, has low testing costs, and is very suitable for engineering design applications. At the same time, the testing method is simple, has a wide range of applications, a high degree of automation, reduces interference from human factors, improves testing efficiency, and has good economy.

[0035] 3. The parameter determination method of the present invention is simple and very suitable for actual engineering design applications. It can be widely used in the determination of atomizing gas parameters of conventional liquid fuel combustion chambers, staged combustion chambers, dual-fuel combustion chambers, liquid fuel low-emission combustion chambers and dual-fuel low-emission combustion chambers that use liquid fuel and are used in gas turbines or aircraft engines. It can provide strong technical support for the design and finalization of gas turbine combustion chambers, especially new combustion chambers, and has high practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a structural schematic diagram of the present invention;

[0037] Figure 2 It is a schematic diagram of the curve of combustion efficiency changing with atomizing gas pressure under a certain working condition;

[0038] Figure 3 The maximum non-uniformity OT of the combustion chamber outlet temperature under a certain working condition changes with the atomizing gas pressure.

[0039] Figure 4 It is a schematic diagram of the curve of the maximum radial non-uniformity RT of the combustion chamber outlet temperature changing with the atomizing gas pressure under a certain working condition;

[0040] Figure 5 It is a schematic diagram of the curve of the combustion chamber pressure pulsation δ changing with the atomizing gas pressure under a certain working condition;

[0041] Figure 6 is a flow chart of the present invention;

[0042] Figure 7 The test results of the embodiment are as follows: the curve of atomizing gas pressure under all working conditions changing with working conditions (including the working range of the best atomizing gas parameters).

[0043] Reference numerals in the figures:

[0044] 1: Test housing 1-3: Fuel nozzle mounting slope

[0045] 1-5: Upper cover 1-6: Air intake section

[0046] 1-6A: Air inlet 1-7: Exhaust section

[0047] 1-7A: Gas outlet 2: Flame tube

[0048] 3: Fuel nozzle

[0049] 3-1: Liquid fuel inlet 3-2: Atomizing gas inlet

[0050] 4: Ignition 5: Pressure pulsation sensor

[0051] 6: Total temperature probe 7: Sampling probe

[0052] 8: Flue gas analyzer 9: Central control computer

[0053] A: Liquid fuel system A0: Liquid fuel line

[0054] A1: Liquid fuel source A2: Booster pump

[0055] A3: Filter A4: Regulating valve

[0056] A5: Shut-off valve A6: Mass flow meter

[0057] A7: Bypass valve A8: Check valve

[0058] B: Main air system B0: Main air circuit

[0059] B1: Main air source B2: Heater

[0060] B4: Regulating valve

[0061] B5: Shut-off valve B6: Mass flow meter

[0062] B7: Bypass valve B8: Check valve

[0063] B9: Pressure sensor B10: Temperature sensor

[0064] C: Atomizing gas system C0: Atomizing gas main circuit

[0065] C0-1: Atomizing gas 1 branch C0-2: Atomizing gas 2 branch

[0066] C0-3: Atomizing gas 3 branches

[0067] C1: Atomizing gas source C2: Water bath heater

[0068] C3: Filter C4-1 / C4-2 / C4-3: Regulating valve

[0069] C5 / C5-1 / C5-2 / C5-3: Shut-off valve C6-1: Small range mass flow meter

[0070] C6-2: Medium range mass flow meter C6-3: Large range mass flow meter

[0071] C7: Bypass valve C8-1 / C8-2 / C8-3: Check valve

[0072] C9: Pressure sensor C10: Temperature sensor

[0073] C11: Proximal pressure chamber DETAILED DESCRIPTION

[0074] The present invention is described in more detail below with reference to the accompanying drawings:

[0075] Combination Figure 1-7The test system for determining the atomizing gas parameters of the combustion chamber of a gas turbine adopted in the present invention comprises a test housing 1, a flame tube 2, a fuel nozzle 3, an igniter 4, a pressure pulsation sensor 5, a total temperature probe 6, a sampling probe 7, a flue gas analyzer 8, a central control computer 9, a liquid fuel system A, a main air system B and an atomizing gas system C; wherein the flame tube 2 is installed inside the test housing 1 and is fixed by the head and tail supports; the fuel nozzle 3 is plugged into the central hole of the swirler at the head of the flame tube 2 and is fixed on the nozzle mounting inclined surface 1-3 of the test housing 1, the liquid fuel inlet 3-1 of the fuel nozzle 3 is connected to the liquid fuel path A0 outlet of the liquid fuel system A, and the atomizing gas inlet 3-2 of the fuel nozzle 3 is connected to the atomizing gas system C The outlet of the atomizing gas main circuit C0 is connected; the outlet of the igniter 4 is plugged into the inlet of the flame tube and fixed on the surface of the upper cover plate 1-5 of the test shell 1; the surface of the upper cover plate 1-5 of the test shell is also installed with a pressure pulsation sensor 5, the sensor probe is coaxial with the central axis of the main combustion hole position of the flame tube, and can detect the flame pulsation signal inside the flame tube; the exhaust section 1-7 of the test shell 1 is installed with a total temperature probe 6 and a sampling probe 7, and the sampling probe 7 is connected to the flue gas analyzer 8 through the bleed pipe; the test shell 1 is connected to the main air circuit B0 outlet of the main air system B through the intake section 1-6, the main air is supplied by the air inlet 1-6A, connected to the exhaust pipeline of the test bench through the exhaust section 1-7, and the gas is discharged from the gas outlet 1-7A. In addition, the igniter 4, the pressure pulsation sensor 5, the total temperature probe 6, the flue gas analyzer 8, the liquid fuel system A, the main air system B and the atomizing gas system C are connected to the central control computer through signal lines to transmit real-time signals. The liquid fuel system A, the main air system B and the atomizing gas system C are all provided with regulating valves, shut-off valves and mass flow meters for regulation, shut-off and monitoring. The atomizing gas system C includes atomizing gas branch 1 C0-1, atomizing gas branch 2 C0-2 and atomizing gas branch 3 C0-3. The outlets of each branch are connected to the proximal pressure stabilizing chamber C11 after merging with the atomizing gas main line C0, so as to accurately control the atomizing gas with different flow requirements.

[0076] The test housing 1 is a reflux housing structure with a fan-shaped cross section. Figure 1 As shown, it mainly includes the fuel nozzle installation slope 1-3, the upper cover plate 1-5, the air intake section 1-6, the exhaust section 1-7, the air inlet 1-6A and the gas outlet 1-7A, etc. It is connected to the main air path B0 outlet of the main air system B through the air intake section 1-6, and connected to the exhaust pipeline of the test bench through the exhaust section 1-7, finally forming a combustion flame working chamber, and at the same time providing a fixed space for the installation of various test and measurement equipment and providing effective support.

[0077] like Figure 1As shown, the flame tube 2 is a nearly cylindrical structure. The figure shows a cross-section of the flame tube, which is composed of a straight tube section on the left and a contraction section on the right. A swirler for flame stabilization and a positioner structure for fixing the flame tube are provided at the left head portion, and a flame starter tube and a flame linking tube structure are provided in the straight tube section. The flame starter tube and the igniter 4 are plugged into each other to facilitate ignition and thermal expansion movement. The middle part of the flame tube is provided with a main combustion hole to provide combustion air and can also be used to detect pressure pulsation signals occurring inside the flame tube. The tail contraction section is provided with an arc-shaped mounting seat to facilitate plug-in installation and thermal expansion movement.

[0078] like Figure 1 As shown, the fuel nozzle 3 is a supply device capable of providing one or more fuels including liquid fuel, including a liquid fuel inlet 3-1, an atomizing gas inlet 3-2, a plug-in joint and a mounting flange. The figure preferably illustrates only one liquid fuel inlet and one atomizing gas inlet, which can be multiple, or include one or more natural gas fuel, hydrogen and other fuel inlets. The plug-in joint is plugged and installed corresponding to the central hole of the swirler of the flame tube, and is used to reasonably distribute the liquid fuel and the like to the combustion space in the flame tube 2 to participate in the combustion.

[0079] like Figure 1 As shown, the igniter 4 is the ignition device of the test system, which is fixed on the upper cover plate 1-5 of the test shell 1 and plugged into the flame guide tube of the flame tube 2. According to the control signal requirements of the central control computer 9, sparks and flames are generated within a specific time period to provide a reliable ignition source for combustion chamber ignition, wherein the control signal is transmitted through the signal line connected to the central control computer 9.

[0080] like Figure 1 As shown, the pressure pulsation sensor 5 is a test device with a sensing probe, which is installed and fixed on the surface of the upper cover plate 1-5 of the test shell 1, and the axis of the probe is coaxial with the main combustion hole of the flame tube. It is used to detect the stability of the combustion flame, and its signal transmission is completed through the signal line connected to the central control computer 9, and the pulsation value is transferred and fed back to the control interface of the central control computer.

[0081] like Figure 1As shown, the liquid fuel system A includes a liquid fuel circuit A0, a liquid fuel source A1, a booster pump A2, a filter A3, a regulating valve A4, a shut-off valve A5, a mass flowmeter A6, a bypass valve A7 and a check valve A8. The outlet of the liquid fuel circuit A0 is connected to the liquid fuel inlet 3-1 of the fuel nozzle 3. Before the test, the shut-off valve A5 is opened, the booster pump A2 is started, and the liquid fuel of the liquid fuel source A1 is pressurized to the target pressure. During the test, the regulating valve A4 is opened to a specified opening, so that the liquid fuel can be filtered through the filter A3 and supplied to the liquid fuel inlet 3-1 of the fuel nozzle 3 after passing through the check valve A8. By adjusting the openings of the regulating valve A4, different required liquid fuel quantities can be obtained and supplied to the combustion chamber to maintain flame stability.

[0082] like Figure 1 As shown, the main air system B includes a main air circuit B0, a main air source B1, a heater B2, a regulating valve B4, a shut-off valve B5, a mass flow meter B6, a bypass valve B7, a check valve B8, a pressure sensor B9 and a temperature sensor B10. The outlet of the main air circuit B0 is connected to the air inlet 1-6A of the test shell. The main air circuit source B1 is used to provide an air source. The air supply temperature is adjusted by the heater B2. The check valve B8 is used to prevent the medium from flowing back. The air supply flow rate and pressure are adjusted and the on-off control is performed by the regulating valve B4, the bypass valve B7 and the shut-off valve B5. The air flow rate, pressure and temperature are monitored and collected by the mass flow meter B6, the pressure sensor B9 and the temperature sensor B10 respectively. The control of all valves and the sensor collection information are connected to the central control computer 9 through a transmission line. During the test, the valves and sensors in the main air system B are controlled by the central control computer 9.

[0083] like Figure 1As shown, the atomizing gas system C includes the atomizing gas main circuit C0, the atomizing gas 1 branch circuit C0-1, the atomizing gas 2 branch circuit C0-2, the atomizing gas 3 branch circuit C0-3, the atomizing gas source C1, the water bath heater C2, the filter C3, the regulating valve C4-1 / C4-2 / C4-3, the shut-off valve C5 / C5-1 / C5-2 / C5-3, the small-range mass flow meter C6-1, the medium-range mass flow meter C6-2, the large-range mass flow meter C6-3, the bypass Valve C7, check valve C8-1 / C8-2 / C8-3, pressure sensor C9, temperature sensor C10 and proximal pressure stabilizing chamber C11, wherein the atomizing gas main circuit B0 is connected to the atomizing gas source C1, the cut-off valve C5, the filter C3 and the water bath heater C2 in sequence, and then is divided into atomizing gas 1 branch C0-1, atomizing gas 2 branch C0-2 and atomizing gas 3 branch C0-3, a total of 3 branches, and then merged into the atomizing gas main circuit C0, and then connected to the proximal pressure stabilizing chamber C11 After the incoming atomizing gas is buffered and pressure-stabilized, it is connected to the atomizing gas inlet 3-2 of the fuel nozzle 3, wherein the pressure-stabilizing chamber C11 is provided with a pressure sensor C9 and a temperature sensor C10 to monitor and record the pressure and temperature of the incoming gas in real time. The three atomizing gas branches are respectively used for adjusting different atomizing gas flow rates to improve the control accuracy of the atomizing flow rate. The structure of each branch is basically the same, including adjusting the gas supply flow rate, pressure size and on-off control through the regulating valve C4-1 / C4-2 / C4-3, the bypass valve C7 and the cut-off valve C5-1 / C5-2 / C5-3. The atomizing gas flow rate, pressure and temperature are monitored by the mass flow meter C6-1 / C6-2 / C6-3, the pressure sensor C9 and the temperature sensor C10 respectively. The control of all valves and the sensor acquisition information are connected to the central control computer 9 through transmission lines. During the test, the valves and sensors in the atomizing gas system C are controlled by the central control computer 9. The atomizing gas source C1 is used to provide the gas source, the gas supply temperature is adjusted by the water bath heater C2, and the check valve C8-1 / C8-2 / C8-3 is used to prevent the medium from flowing back.

[0084] like Figure 1 As shown, the central control computer 9 is connected to the igniter 4, the pressure pulsation sensor 5, the total temperature probe 6, the flue gas analyzer 8, the liquid fuel system A, the main air system B and the atomizing gas system C through signal lines, and can send out control signals to control the states of the regulating valves and the shut-off valves of each system, can verify and further calculate the collected data, and perform logical judgment on the reliability of the data according to specific logic, so as to provide an effective control scheme for the smooth progress of the experiment.

[0085] During the test, after the installation and preparation of each equipment and system are completed, adjust the main air and atomizing gas parameters to the ignition condition, start the igniter, and after a certain period of time, add liquid fuel into the flame tube 2 through the liquid fuel system A to achieve stable combustion after ignition, adjust the main air parameters and liquid fuel flow to the target operating condition parameters, and determine the accuracy of the atomizing gas parameters in real time through logic. After adjusting the atomizing gas parameters so that the combustion efficiency η, the maximum unevenness OT of the combustion chamber outlet temperature, the maximum radial unevenness RT of the combustion chamber outlet temperature, and the pressure pulsation δ test results all meet the requirements of the combustion chamber performance indicators, record the atomizing air pressure Pw parameter range of the current operating condition, adjust the target operating condition to be stable, and use the same method to determine the atomizing air pressure Pw parameter range under the new operating condition. Finally, complete the determination of the atomizing air parameters for all operating conditions, and obtain the following Figure 7 The characteristic curve of the atomizing gas pressure parameter Pw changing with the operating condition Ne provides real and reliable data support for the application of new combustion chambers and the operation of gas turbines. The test is now completed.

[0086] This test system is composed of a fuel nozzle and a flame tube arranged in an independent test shell, and is equipped with an igniter, a pressure pulsation sensor, a total temperature probe, a sampling probe, a flue gas analyzer, a liquid fuel system, a main air system and an atomizing gas system. Combined with a central control computer, the system automatically obtains the optimal atomizing gas parameters under each working condition while ensuring accurate verification of the atomizing parameters, and obtains an accurate and reliable optimal atomizing gas pressure parameter working band for all working conditions of this type of combustion chamber. High-precision parameter numerical results for all working conditions within a wide parameter range can be obtained under relatively small working input conditions, which greatly reduces the development investment and test costs of the combustion chamber and shortens the development cycle. At the same time, the verification results are reliable, effectively avoiding the risk of failure in the development of the combustion chamber. The system has strong engineering practicality and good promotion.

[0087] The present invention provides a test method for determining combustion chamber atomization gas parameters, such as Figure 6 As shown, the following steps are included:

[0088] S1. Prepare the main air and atomizing gas 1001: Open the main air system B, adjust the main air temperature, pressure and flow rate to the values ​​Ta0, Pa0 and Ga0 required for the ignition condition to maintain stability, open the atomizing gas system C, select a suitable atomizing gas branch, adjust the atomizing gas temperature, pressure and flow rate to the initial values ​​Tw0, Pw0 and Gw0 to maintain stability.

[0089] S2. Perform liquid fuel ignition 1002: Open the liquid fuel supply system A, start the boost pump A2, adjust the liquid fuel regulating valve A4 to the target opening corresponding to the initial ignition flow Gl0A, and after preparing for the initial ignition flow Gl0A to be supplied, open the igniter 4 through the central control computer 9, and after Δt s, open the liquid fuel shut-off valve A5 to start the ignition process of the liquid fuel entering the fuel nozzle 3 and the flame tube 2.

[0090] S3, the central control computer automatically performs logical judgment 1003: if the ignition is successful, the main air and liquid fuel parameters are adjusted to the target operating condition 1 parameters, so that the temperature, pressure and flow of the main air are adjusted to Ta1, Pa1 and Ga1, and the liquid fuel flow is adjusted to the target operating condition value Gl1, and the atomizing gas parameters are stably and continuously supplied according to the initial value; if the ignition fails, the liquid fuel supply is stopped, and after the main air is purged for 3 minutes, the initial ignition flow is adjusted to increase to Gl0B and steps S2 and S3 are re-executed until the ignition is successful.

[0091] S4. The central control computer performs initial combustion chamber performance recording 1004: Under target operating condition 1, the central control computer 9 calculates the combustion efficiency η0 according to the flue gas components obtained by the flue gas analyzer 8 according to the set program, calculates the average pressure pulsation δ0 according to the sampling data of the pressure pulsation sensor, and calculates the maximum unevenness OT0 and the maximum radial unevenness RT0 of the combustion chamber outlet temperature according to the temperature measurement result of the total temperature probe 6 at the flame tube outlet.

[0092] S5. Adjust the atomizing gas parameters to further evaluate the combustion chamber performance 1005: Under the above combustion chamber initial performance conditions, adjust the atomizing gas pressure parameters to evaluate the combustion efficiency η, the maximum non-uniformity OT and maximum radial non-uniformity RT of the combustion chamber outlet temperature, the combustion chamber pressure pulsation δ and other performance parameters under the conditions of reaching the standard, and the corresponding optimal working parameters of the atomizing gas pressure parameters. Figure 2 As shown, when the atomizing gas pressure changes from Pw1 to Pw2, the combustion efficiency satisfies η≥η min Therefore, the optimal atomizing gas pressure parameter interval corresponding to the combustion efficiency η is [Pw1, Pw2]. Similarly, Figure 3 , Figure 4 and Figure 5 As shown, the maximum non-uniformity OT and maximum radial non-uniformity RT of the combustion chamber outlet temperature, and the upper limit index OT of the combustion chamber pressure pulsation delta max , RT max and δ maxThe corresponding optimal atomizing gas pressure parameter intervals are [Pw3, Pw4], [Pw5, Pw6] and [Pw7, Pw8], respectively. On this basis, the central control computer 9 performs an intersection operation on the four atomizing gas pressure parameter working intervals according to the set logic program to obtain the optimal atomizing gas pressure parameter interval that meets the requirements of the four performances, for example, [Pw5, Pw6];

[0093] S6. The central control computer automatically checks the atomizing gas pressure parameters and performs a logical judgment 1006: The central control computer automatically checks and calculates the atomizing gas pressure parameters according to the measured flow corresponding to the collected atomizing gas pressures Pw5 and Pw6, that is, the flow value collected by the mass flow meter C6-1, C6-2 or C6-3, wherein the pressure Pw5 corresponds to the measured atomizing gas flow Gw5, and the pressure Pw6 corresponds to the measured atomizing gas flow Gw6, according to the following calculation procedure. Specifically, for example, under the condition that the current pressure is Pw5, the theoretical calculated flow of the atomizing gas path of the fuel nozzle is calculated according to the following formula:

[0094]

[0095] The meanings of the parameters are as follows:

[0096] ①k is the adiabatic index, Rg is the gas constant;

[0097] ②Pw5 is the atomizing gas inlet pressure of the fuel nozzle, in Pa, and the data comes from the pressure sensor C9 on the proximal pressure stabilizing chamber C11 of the atomizing gas system C;

[0098] ③Tw5 is the atomizing gas inlet temperature of the fuel nozzle, in K, and the data comes from the temperature sensor C10 on the proximal pressure stabilizing chamber C11 of the atomizing gas system C;

[0099] ④P b is the combustion chamber inlet pressure, in Pa, the data comes from the pressure sensor B9 at the end of the main air path B0 of the main air system B, the nozzle atomizing gas outlet pressure Pw(out) = P b *(1-σ), where σ is the total pressure loss coefficient after the combustion chamber inlet passes through the combustion chamber inlet diffuser section and the flame tube;

[0100] ⑤Aw is the throttling area of ​​the fuel nozzle atomization gas path, unit: m 2 , determined according to the nozzle design structure;

[0101] ⑥α is the fuel nozzle atomization gas path flow coefficient, which is given based on nozzle test experience.

[0102] After obtaining the Gw5 (calculated) value, perform automatic verification:

[0103] a. When the absolute value of the relative deviation of the result |(Gw5(calculated)-Gw5) / Gw5|≤β%, the logic judges that the data is reliable under the current conditions and is an accurate atomizing gas pressure parameter. Similarly, it can be judged that the data is accurate when the atomizing pressure is Pw6, and finally the accurate optimal atomizing gas pressure parameter range [Pw5, Pw6] is obtained. This verification method is also applicable to the data accuracy verification under other pressure and flow parameter conditions.

[0104] b. When the relative deviation of the result is greater than β%, shut down the engine, check the relevant equipment, analyze the cause and make corrections, and then repeat the process of steps S1-S6 until the deviation is ≤ β%.

[0105] S7, adjust the working condition, determine the atomizing gas pressure parameters of other working conditions 1007: Based on step S6, keep the atomizing air parameters in the optimal range [Pw5, Pw6], adjust the target working condition to working condition 2, that is, adjust the temperature, pressure and flow rate of the main air to Ta2, Pa2 and Ga2, adjust the liquid fuel flow rate to the target working condition value Gl2 and maintain stability, repeat steps S4, S5 and S6, and obtain the reliable optimal atomizing gas pressure parameter optimal range [Pw5, Pw6] under working condition 2, and so on, and finally obtain the optimal atomizing gas pressure parameter working band under all working conditions of this type of combustion chamber, such as Figure 6 As shown, the determination of the atomizing gas parameters is completed and the test is ended.

[0106] The liquid fuel may be diesel, kerosene, ethanol, etc., and the atomizing gas may be air, natural gas or other combustible gases.

[0107] The igniter start time Δt∈[10s, 15s] ensures reliable ignition.

[0108] Combustion efficiency η min =99.9%, the maximum unevenness OT and maximum radial unevenness RT of the combustion chamber outlet temperature, and the upper limit index of the combustion chamber pressure pulsation δ are OT max =20%, RT max =10% and δ max =4kPa.

[0109] The combustion chamber performance includes but is not limited to combustion efficiency, maximum non-uniformity and maximum radial non-uniformity of combustion chamber outlet temperature, and combustion chamber pressure pulsation.

[0110] The total pressure loss coefficient σ∈[4.9%, 5%] at the combustion chamber inlet after passing through the combustion chamber inlet diffusion section and the flame tube, the fuel nozzle atomization gas path flow coefficient α∈[0.95, 0.96], and the absolute value of the relative deviation |(Gw5(calculated)-Gw5) / Gw5|∈[0, 2%].

[0111] The present invention fully considers the wide range and high precision of the determination of the atomizing gas parameters, expands the working range of the atomizing parameters through multiple atomizing gas branches, determines the accuracy of the atomizing gas parameters through an automatic verification program, solves the difficulty of determining the atomizing gas parameters of the gas turbine combustion chamber, and the current research and development dilemma of no effective technical solution, greatly reduces the shortcomings of high risk and large investment in the whole machine test, and has low test cost, which is very suitable for engineering design applications. At the same time, the test method is simple, the scope of application is wide, the degree of automation is high, the interference of human factors is reduced, the test efficiency is improved, and the economy is good. It can be widely used in the determination of atomizing gas parameters of conventional liquid fuel combustion chambers, staged combustion chambers, dual-fuel combustion chambers, liquid fuel low-emission combustion chambers, and dual-fuel low-emission combustion chambers that use liquid fuel and are applied to gas turbines or aircraft engines, and can provide strong technical support for the design and finalization of gas turbine combustion chambers, especially new combustion chambers, and has high practical value.

Claims

1. A test system for determining the parameters of atomized gas in a gas turbine combustion chamber, characterized in that: It includes a test shell, a flame tube, a fuel nozzle, an igniter, a pressure pulsation sensor, a total temperature probe, a sampling probe, a flue gas analyzer, a central control computer, a liquid fuel system, a main air system, and an atomizing gas system. The flame tube is installed inside the test shell, the fuel nozzle is plugged into the flame tube head and fixed on the nozzle mounting slope of the test shell, the liquid fuel inlet of the fuel nozzle is connected to the liquid fuel system, the atomizing gas inlet of the fuel nozzle is connected to the atomizing gas system, the igniter is plugged into the flame guide tube inlet of the flame tube, the probe of the pressure pulsation sensor is coaxial with the central axis of the main combustion hole position of the flame tube, the igniter and the pressure pulsation sensor are both fixed on the upper cover surface of the test shell, the exhaust section of the test shell is installed with a total temperature probe and a sampling probe, the sampling probe is connected to the flue gas analyzer, the air intake section of the test shell is connected to the main air system, the igniter, the pressure pulsation sensor, the total temperature probe, the flue gas analyzer, the liquid fuel system, the main air system, and the atomizing gas system are connected to the central control computer.

2. A test system for determining atomizing gas parameters of a gas turbine combustion chamber according to claim 1, characterized in that: The liquid fuel system comprises a liquid fuel path, on which a liquid fuel source, a booster pump, a liquid filter, a liquid regulating valve, a liquid shut-off valve, a liquid mass flow meter, and a liquid check valve are sequentially arranged, a liquid bypass path is extended between the liquid check valve and the liquid mass flow meter, and a liquid bypass valve is installed on the liquid bypass path.

3. The test system for determining the atomizing gas parameters of a gas turbine combustion chamber according to claim 1, characterized in that: The main air system includes a main air circuit, on which a main air source, a heater, an air regulating valve, an air shut-off valve, an air mass flow meter, and an air check valve are sequentially arranged; an air bypass circuit is provided between the air check valve and the air mass flow meter, and an air bypass valve is installed on the air bypass circuit.

4. A test system for determining atomizing gas parameters of a gas turbine combustion chamber according to claim 1, characterized in that: The atomizing gas system comprises an atomizing gas main circuit, a first atomizing gas branch circuit, a second atomizing gas branch circuit and a third atomizing gas branch circuit. The first atomizing gas branch circuit, the second atomizing gas branch circuit and the third atomizing gas branch circuit are connected in parallel and then connected to the atomizing gas main circuit. An atomizing gas source, a main atomizing shut-off valve, an atomizing filter and a water bath heater are sequentially arranged on the atomizing gas main circuit. An atomizing bypass circuit is provided between the water bath heater and the atomizing filter, and an atomizing bypass valve is installed on the atomizing bypass circuit. A first atomizing regulating valve, a first atomizing shut-off valve, a small-range mass flowmeter and a first atomizing check valve are sequentially arranged on the first atomizing gas branch circuit. A second atomizing regulating valve, a second atomizing shut-off valve, a medium-range mass flowmeter and a second atomizing check valve are sequentially arranged on the second atomizing gas branch circuit. A third atomizing regulating valve, a third atomizing shut-off valve, a large-range mass flowmeter and a third atomizing check valve are sequentially arranged on the third atomizing gas branch circuit.

5. A test method for determining the parameters of atomizing gas in a gas turbine combustion chamber, characterized in that: The test system for determining the atomizing gas parameters of a gas turbine combustion chamber according to claim 1 comprises the following steps: (1) Prepare the main air and atomizing gas: start the main air system, adjust the main air temperature, pressure and flow rate to the values ​​Ta0, Pa0 and Ga0 required for ignition conditions and keep them stable; start the atomizing gas system, select the atomizing gas branch, adjust the atomizing gas temperature, pressure and flow rate to the initial values ​​Tw0, Pw0 and Gw0 and keep them stable; (2) Liquid fuel ignition: Open the liquid fuel supply system, start the booster pump, adjust the liquid fuel regulating valve to the target opening corresponding to the initial ignition flow Gl0A, and after the initial ignition flow Gl0A is ready to be supplied, turn on the igniter through the central control computer. After Δt s, open the liquid fuel cut-off valve to start the ignition process of liquid fuel entering the fuel nozzle and the flame tube; (3) The central control computer performs logical judgment: if the ignition is successful, the main air and liquid fuel parameters are adjusted to the target operating condition 1 parameters, so that the temperature, pressure and flow rate of the main air are adjusted to Ta1, Pa1 and Ga1, and the liquid fuel flow rate is adjusted to the target operating condition value Gl1, and the atomizing gas parameters are stably and continuously supplied according to the initial value; if the ignition fails, the liquid fuel supply is stopped, and after the main air is purged for 3 minutes, the initial ignition flow rate is adjusted to increase to Gl0B and steps (2) and (3) are re-executed until the ignition is successful; (4) The central control computer records the initial performance of the combustion chamber: Under target operating condition 1, the central control computer calculates the combustion efficiency η0 according to the flue gas components obtained by the flue gas analyzer according to the set program, calculates the average pressure pulsation δ0 according to the sampling data of the pressure pulsation sensor, and calculates the maximum non-uniformity OT0 and the maximum radial non-uniformity RT0 of the combustion chamber outlet temperature according to the temperature measurement results of the total temperature probe at the flame tube outlet; (5) Adjust the atomizing gas parameters to further evaluate the combustion chamber performance: Under the above combustion chamber initial performance conditions, adjust the atomizing gas pressure parameters to evaluate the combustion efficiency η, the maximum non-uniformity OT and the maximum radial non-uniformity RT of the combustion chamber outlet temperature, the combustion chamber pressure pulsation δ and other performance parameters. The corresponding atomizing gas pressure parameters are the best working parameters: When the atomizing gas pressure changes from Pw1 to Pw2, the combustion efficiency satisfies η≥η min The requirements of combustion efficiency η, the optimal atomizing gas pressure parameter interval corresponding to the combustion efficiency η is [Pw1, Pw2], the maximum unevenness OT and the maximum radial unevenness RT of the combustion chamber outlet temperature, the upper limit index OT of the combustion chamber pressure pulsation δ max , RT max and δ max The corresponding optimal atomizing gas pressure parameter intervals are [Pw3, Pw4], [Pw5, Pw6] and [Pw7, Pw8] respectively. The central control computer performs intersection calculation on the four atomizing gas pressure parameter working intervals according to the set logic program to obtain the optimal atomizing gas pressure parameter interval that meets the requirements of the four performances. (6) The central control computer verifies the atomizing gas pressure parameter and performs a logical judgment: if the optimal atomizing gas pressure parameter interval is [Pw5, Pw6], the central control computer verifies the atomizing gas pressure parameter according to the measured flow rates corresponding to the collected atomizing gas pressures Pw5 and Pw6, that is, the flow rate values ​​collected by the mass flow meter, where the pressure Pw5 corresponds to the measured atomizing gas flow rate Gw5, and the pressure Pw6 corresponds to the measured atomizing gas flow rate Gw6; (7) Adjust the operating conditions and determine the atomizing gas pressure parameters for other operating conditions: Based on step (6), keep the atomizing air parameters within the optimal range [Pw5, Pw6] and adjust the target operating condition to operating condition 2, that is, adjust the temperature, pressure and flow rate of the main air to Ta2, Pa2 and Ga2, so that the liquid fuel flow rate is adjusted to the target operating condition value Gl2 and remains stable. Repeat steps (4), (5) and (6) to obtain the optimal range [Pw5, Pw6] of the optimal atomizing gas pressure parameters under operating condition 2. Similarly, the optimal atomizing gas pressure parameter working band under all operating conditions of this type of combustion chamber is finally obtained, the atomizing gas parameters are determined, and the test is ended.

6. The test method for determining the atomizing gas parameters of a gas turbine combustion chamber according to claim 5, characterized in that: In step (6), the atomizing gas pressure parameter is calibrated and calculated according to the following calculation procedure: Under the condition that the current pressure is Pw5, the theoretical calculated flow rate of the atomizing gas path of the fuel nozzle is calculated according to the following formula: The meanings of the parameters are as follows: k is the adiabatic index, Rg is the gas constant; Pw5 is the fuel nozzle atomizing gas inlet pressure, Tw5 is the fuel nozzle atomizing gas inlet temperature, Pb is the combustion chamber inlet pressure, nozzle atomizing gas outlet pressure Pw(out)=Pb*(1-σ), where σ is the total pressure loss coefficient after the combustion chamber inlet passes through the combustion chamber inlet expansion section and the flame tube; Aw is the throttling area of ​​the fuel nozzle atomizing gas path, and α is the fuel nozzle atomizing gas path flow coefficient; After obtaining the Gw5 (calculated) value, check it: When the absolute value of the relative deviation of the result |(Gw5(calculated)-Gw5) / Gw5|≤β%, the logic judges that the data is reliable under the current conditions and is an accurate atomizing gas pressure parameter. Similarly, the data is accurate when the atomizing pressure is Pw6, and finally the accurate optimal atomizing gas pressure parameter interval [Pw5, Pw6] is obtained; When the relative deviation of the result is greater than β%, the engine is turned off, relevant equipment is checked, the cause is analyzed and corrected, and the process of steps S1-S6 is repeated until the deviation is ≤ β%.

7. The test method for determining the atomizing gas parameters of a gas turbine combustion chamber according to claim 5, characterized in that: The igniter start time Δt∈[10s, 15s] described in step (2) ensures reliable ignition.

8. The test method for determining the atomizing gas parameters of a gas turbine combustion chamber according to claim 5, characterized in that: The combustion efficiency η described in step (5) min =99.9%, the maximum unevenness OT and maximum radial unevenness RT of the combustion chamber outlet temperature, and the upper limit index of the combustion chamber pressure pulsation δ are OT max =20%, RT max =10% and δ max =4kPa.

9. The test method for determining the atomizing gas parameters of a gas turbine combustion chamber according to claim 5, characterized in that: The total pressure loss coefficient σ∈[4.9%, 5%] of the combustion chamber inlet after passing through the combustion chamber inlet diffuser section and the flame tube in step (6), the fuel nozzle atomization gas path flow coefficient α∈[0.95, 0.96], and the relative deviation absolute value |(Gw5(calculated)-Gw5) / Gw5|∈[0, 2%].

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