Combustion chamber multi-flow coupling optimization design method, device and equipment and storage medium

Abstract

The application provides a combustion chamber multi-flow coupling optimization design method, device, equipment and storage medium. A combustion chamber flow path is drawn based on design parameters of the combustion chamber. Flow distribution of the combustion chamber is determined based on the combustion chamber flow path. A mathematical model corresponding to a combustion chamber optimization design target is constructed based on the fuel chamber flow path and the flow distribution of the combustion chamber. The mathematical model is optimized according to preset sample points to obtain parameter values of head structure design parameters and a prediction model for predicting combustion chamber emissions within a preset accuracy range. The application can obtain optimal values of head structure design parameters and a prediction model based on the mathematical model corresponding to the combustion chamber optimization design target by coupling multiple flow designs of the combustion chamber, so as to determine an optimal scheme of the combustion chamber, improve the design efficiency and design accuracy of designers as a whole, save labor costs, improve the combustion performance of the combustion chamber, and further improve the overall performance of the engine.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustor technology, and in particular to a method, apparatus, equipment and storage medium for multi-process coupled optimization design of combustors. Background Technology

[0002] To reduce carbon emissions in the aviation sector, the European Civil Aviation Authority (ECAA) has set stringent emission targets in FlightPath 2050, such as reducing CO2 emissions by 75% and nitrogen oxide emissions by 90% per kilometer per passenger. All fuels used in aviation are hydrocarbon fuels, which produce carbon-containing compounds such as CO2, CO, and UHC during combustion. CO2 is a major greenhouse gas contributing to global warming, while CO and UHC are major pollutants generated during flight. Low-carbon, low-pollution emission technologies are among the key technologies for the future development of aircraft engines and gas turbines. The advantages and potential of hydrogen-powered flight are gradually becoming apparent, making it crucial for the low-carbon development of the aviation industry.

[0003] On the other hand, hydrogen has the characteristics of low density, fast combustion speed, and high flame temperature, which presents problems such as difficulty in mixing, backfire, and high nitrogen oxide emissions. The backfire prevention measures of traditional combustion chamber head mixers are no longer suitable for the high flame propagation speed of hydrogen, and new structural forms must be explored to suit the characteristics of hydrogen combustion technology. Therefore, the innovative use of microscale mixing and combustion organization can quickly achieve uniform mixing, prevent backfire, and reduce nitrogen oxide emissions.

[0004] Currently, existing combustor optimization design methods rely on trial and error and multiple sets of experiments. This involves first providing a basic design, then using its structural parameters as a benchmark to set multiple sets of head structure parameters. Each design is then modeled, numerically simulated, and experimentally analyzed to compare combustion performance and select the optimal solution. However, these methods suffer from drawbacks such as long design cycles, high computational demands, heavy reliance on designer experience, and high experimental costs. Finding the best-performing design is difficult due to the need for extensive calculations on numerous individual cases, followed by manual selection and performance comparisons. This approach cannot cover all parameters, meaning the optimal solution obtained is not necessarily the best solution within the global parameter range, which affects the selection of the optimal combustor design. Summary of the Invention

[0005] This invention provides a combustion chamber multi-process coupled optimization design method, apparatus, equipment, and storage medium, which solves the problems of long design cycle, large amount of calculation, heavy reliance on the experience of designers, and high experimental cost in the existing combustion chamber optimization design methods, thereby improving design efficiency and design accuracy.

[0006] This invention provides a multi-flow coupled optimization design method for combustion chambers, comprising:

[0007] Based on the combustion chamber design parameters, draw the combustion chamber flow path;

[0008] Based on the combustion chamber flow path, the flow distribution in the combustion chamber is determined;

[0009] Based on the combustion chamber flow path and the flow distribution in the combustion chamber, a mathematical model corresponding to the combustion chamber optimization design objective is constructed;

[0010] The mathematical model is optimized based on preset sample points to obtain parameter values ​​of the head structure design parameters and a prediction model for combustion chamber emissions within a preset accuracy range.

[0011] According to the multi-flow coupled optimization design method for a combustion chamber provided by the present invention, the step of optimizing the mathematical model based on preset sample points to obtain the head structure design parameters and the predictive model for predicting combustion chamber emissions within a preset accuracy threshold range includes:

[0012] Several key parameters of the head structure are selected as target parameters, and the target index values ​​of the target parameters are determined.

[0013] Using the sample points as initial sample points, the mathematical model is optimized based on the target parameters to obtain parameter combinations;

[0014] The first index value of the target parameter is obtained by using the parameter combination through a simulation optimization platform;

[0015] The first indicator value is compared with the target indicator value. If the comparison result is greater than or equal to the preset error threshold, the first indicator value corresponding to the parameter combination replaces the original value of the initial sample point and is brought back to the mathematical model to continue iterative calculation until the comparison result is less than the preset error threshold. The iteration ends and the obtained first indicator value is used as the parameter value of the head structure design parameter.

[0016] A first prediction model is determined based on the parameter values ​​of the head structure design parameters to predict the emission of nitrogen oxides from the combustion chamber.

[0017] According to the multi-flow coupled optimization design method for a combustion chamber provided by the present invention, after the step of optimizing the mathematical model based on preset sample points to obtain the head structure design parameters and predict combustion chamber emissions within a preset accuracy threshold range, the method further includes:

[0018] Add sample points based on the initial sample points;

[0019] Expand the parameter range of each target parameter;

[0020] Approximate the first prediction model and obtain the fitting coefficients;

[0021] Gradient optimization analysis is performed on the fitted first prediction model to obtain the optimal solution of each target parameter that satisfies the combustion chamber optimization design target within the parameter range corresponding to each target parameter, and the optimal solution is used as the optimal parameter value of the target parameter.

[0022] Based on the fitting coefficients and the optimal parameter values, the first prediction model is optimized to obtain the second prediction model.

[0023] According to the present invention, a multi-flow coupled optimization design method for a combustion chamber is provided, wherein the design parameters include: combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet temperature, combustion chamber inlet pressure, and total air flow rate at the combustion chamber inlet. Correspondingly,

[0024] The step of drawing the combustion chamber flow path based on the combustion chamber design parameters includes:

[0025] Based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total air flow rate at the combustion chamber inlet, determine the combustion chamber reference cross-sectional radius, combustion chamber inlet height, combustion chamber outlet height, head height, and combustion chamber reference cross-sectional area;

[0026] Based on the ratio between the length of the flame tube and the height of the head, the length range of the flame tube is determined. Within the length range, the combustion chamber outlet temperature distribution coefficient is iteratively calculated based on the given flame tube length. When the combustion chamber outlet temperature distribution coefficient is less than a preset threshold, the final flame tube length is determined.

[0027] The inclination angle of the flame tube is determined based on the geometry of the combustion chamber inlet, the geometry of the combustion chamber outlet, and the length of the flame tube.

[0028] According to the multi-flow coupling optimization design method for combustion chambers provided by the present invention, the design parameters further include: the outlet height of the pre-diffuser, correspondingly,

[0029] The step of drawing the combustion chamber flow path based on the combustion chamber design parameters further includes:

[0030] The pre-diffuser loss value is determined based on the pre-diffuser outlet height, the combustion chamber inlet pressure, and the combustion chamber inlet height.

[0031] The pressure loss value of the sudden expansion section is determined based on the outlet height of the pre-diffuser, the reference cross-sectional area of ​​the combustion chamber, and the inlet pressure of the combustion chamber.

[0032] The total diffuser loss value is determined based on the pre-diffuser loss value and the sudden diffusion section pressure loss value.

[0033] When the total loss value of the diffuser is less than or equal to the preset loss threshold, the diffuser design requirements are met, and the combustion chamber flow path is drawn.

[0034] According to the combustion chamber multi-flow coupling optimization design method provided by the present invention, the step of determining the flow distribution of the combustion chamber based on the combustion chamber flow path includes:

[0035] Determine the total effective opening area of ​​the flame tube;

[0036] The cooling area of ​​the flame tube is determined based on the reference cross-sectional radius of the combustion chamber, the length of the flame tube, and the height of the head.

[0037] The head cooling area is determined based on the head flow distribution and the total effective opening area of ​​the flame tube;

[0038] Based on the cooling area of ​​the flame tube and the cooling area of ​​the head, the cooling gas volume of the flame tube and the cooling gas volume of the head are determined.

[0039] Based on the total air flow rate at the combustion chamber inlet, the cooling gas volume of the flame tube, and the cooling gas volume of the head, the distribution of cooling gas volume for the flame tube and the head is determined.

[0040] According to the multi-flow coupling optimization design method for combustion chambers provided by the present invention, the step of determining the flow distribution of the combustion chamber based on the combustion chamber flow path further includes:

[0041] The head flow distribution is determined based on the total equivalence ratio of the combustion chamber and the head equivalence ratio.

[0042] When there is no main combustion orifice in the combustion chamber, the mixing orifice gas distribution is determined based on the head flow distribution, the flame tube cooling gas distribution, and the head cooling gas distribution.

[0043] When a main combustion orifice exists in the combustion chamber, the flow distribution of the main combustion orifice is determined, and the flow distribution of the mixing orifice is determined based on the flow distribution of the main combustion orifice, the flow distribution of the head, the flow distribution of the flame tube cooling gas, and the flow distribution of the head cooling gas.

[0044] The present invention also provides a combustion chamber multi-process coupling optimization design device, comprising:

[0045] The combustion chamber flow path design module is used to draw the combustion chamber flow path based on the combustion chamber design parameters;

[0046] A combustion chamber flow distribution module is used to determine the flow distribution of the combustion chamber based on the combustion chamber flow path;

[0047] The combustion chamber optimization model construction module is used to construct a mathematical model corresponding to the combustion chamber optimization design objective based on the combustion chamber flow path and the flow distribution of the combustion chamber.

[0048] The emission prediction model acquisition module is used to optimize the mathematical model based on preset sample points to obtain the parameter values ​​of the head structure design parameters and the prediction model for combustion chamber emissions within a preset accuracy range.

[0049] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the combustion chamber multi-process coupling optimization design method as described above.

[0050] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the combustion chamber multi-process coupling optimization design method as described above.

[0051] This invention provides a multi-process coupled optimization design method, apparatus, equipment, and storage medium for combustion chambers. It involves drawing the combustion chamber flow path based on the combustion chamber design parameters; determining the flow distribution within the combustion chamber based on the flow path; constructing a mathematical model corresponding to the combustion chamber optimization design objective based on the combustion chamber flow path and flow distribution; and optimizing the mathematical model using preset sample points to obtain parameter values ​​for the head structure design parameters and a prediction model for combustion chamber emissions within a preset accuracy range. This invention couples multiple design processes—flow path design, flow distribution design, and optimization design of multiple key target parameters of the head structure—to obtain the optimal values ​​of the head structure design parameters and the prediction model corresponding to the combustion chamber optimization design objective within the overall combustion chamber design scheme. Based on the high-precision prediction of the prediction model, the optimal combustion chamber scheme is selected, which improves the design efficiency and accuracy of designers, saves labor costs, enhances combustion performance, reduces combustion chamber pollutant emissions, broadens the stable operating range of combustion, and ultimately improves the overall engine performance. Attached Figure Description

[0052] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0053] Figure 1This is one of the flowcharts of a multi-process coupled optimization design method for a combustion chamber provided by the present invention;

[0054] Figure 2 The second schematic diagram of a multi-process coupled optimization design method for a combustion chamber provided by the present invention;

[0055] Figure 3 This is a performance design diagram of a pre-diffuser provided in an embodiment of the present invention;

[0056] Figure 4 A schematic diagram of a combustion chamber multi-process coupling optimization design device provided by the present invention;

[0057] Figure 5 This is a schematic diagram of the structure of the electronic device provided by the present invention.

[0058] Figure label:

[0059] 21: Combustion chamber flow path design module; 22: Combustion chamber flow distribution module; 23: Combustion chamber optimization model construction module; 24: Emission prediction model acquisition module. Detailed Implementation

[0060] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be described clearly and completely below with reference to specific embodiments and accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0061] It should be noted that those skilled in the art will understand, explicitly and implicitly, that the embodiments described in this invention can be combined with other embodiments without conflict. Unless otherwise defined, the technical or scientific terms used in this invention should be understood in their ordinary sense by those skilled in the art. The terms "a," "an," "an," "the," etc., used in this invention do not indicate quantity limitation and can represent singular or plural. The terms "comprising," "including," "having," and any variations thereof used in this invention are intended to cover non-exclusive inclusion; the terms "first," "second," "third," etc., used in this invention are merely to distinguish similar objects and do not represent a specific ordering of objects.

[0062] Example 1

[0063] Reference Figure 1 As shown, this embodiment provides a multi-process coupled optimization design method for combustion chambers, including:

[0064] Step S1: Draw the combustion chamber flow path based on the combustion chamber design parameters;

[0065] In this embodiment, the design parameters include: combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet temperature, combustion chamber inlet pressure, and total air flow rate at the combustion chamber inlet. Correspondingly, step S1 specifically includes:

[0066] Step S11: Based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total air flow rate at the combustion chamber inlet, determine the combustion chamber reference cross-sectional radius, combustion chamber inlet height, combustion chamber outlet height, head height, and combustion chamber reference cross-sectional area;

[0067] Specifically, refer to Figure 2 As shown, the combustion chamber flow path design includes:

[0068] (i) Combustion chamber inlet geometry includes: combustion chamber inlet inner radius R ci outer radius R of combustion chamber inlet co The average radius R of the combustion chamber inlet is calculated according to equations (1) and (2). 3,mean Combustion chamber inlet height h3:

[0069]

[0070] h3 = R co -R ci (2)

[0071] The combustion chamber outlet geometry includes: the inner radius R of the combustion chamber outlet. ti outer radius R of combustion chamber outlet to The average radius R of the combustion chamber outlet is calculated according to equations (3) and (4). 4,mean and combustion chamber outlet height h4:

[0072]

[0073] h4 = R to -R ti (4)

[0074] Based on the average radius R of the combustion chamber inlet 3,mean and the average radius R of the combustion chamber outlet 4,mean The reference cross-sectional radius R of the combustion chamber was calculated. ref As shown in equation (5):

[0075]

[0076] (ii) According to the low-emission combustion chamber nitrogen oxides (NOx) of civil aircraft xThe head equivalence ratio of the hydrogen combustion chamber can be obtained from emission standards or the lean-out quenching ratio of military engines. Knowing the total equivalence ratio of the combustion chamber, the head flow distribution μ can then be determined. d As shown in equation (6):

[0077]

[0078] Where, φ c φ is the total equivalence ratio of the combustion chamber. d This represents the head-to-body ratio.

[0079] Based on the total air flow rate W3 at the combustion chamber inlet, the head combustion air volume W is calculated. d As shown in equation (7):

[0080] W d =μ d W3 (7)

[0081] (iii) Select a head reference velocity V d Based on the head combustion air volume W d ,count

[0082] The head area A can be calculated. d As shown in equation (8):

[0083]

[0084] Where ρ3 is the air density at the combustion chamber inlet.

[0085] Based on head area A d and the reference cross-sectional radius R of the combustion chamber ref The head height H was calculated. d As shown in equation (9):

[0086]

[0087] Select a reference velocity V for the annular cavity p Based on the head combustion air volume W d The total air flow rate W3 at the combustion chamber inlet is used to calculate the annular cavity area A. p As shown in equation (10):

[0088]

[0089] Among them, W p This refers to the combustion air flow rate in the annular cavity.

[0090] Based on the annular cavity area A p and the reference cross-sectional radius R of the combustion chamber ref The height H of the annular cavity was calculated. p As shown in equation (11):

[0091]

[0092] Based on head area A d and the area of ​​the annular cavity A p The reference cross-sectional area A of the combustion chamber was calculated. ref As shown in equation (12):

[0093] A ref =A d +A p (12)

[0094] Furthermore, based on the combustion chamber reference cross-sectional area A ref The calculated reference section height H of the combustion chamber ref As shown in equation (13):

[0095]

[0096] (iv) Verify whether the combustion efficiency at the design point, idle point, and high-altitude wind turbine point meets the requirements. If not, reselect the head reference speed V. d The combustion efficiency η and the combustion chamber characteristic parameter θ are calculated. The characteristic parameter θ is a physical quantity related to the combustion chamber inlet temperature, combustion chamber inlet pressure, total air flow rate at the combustion chamber inlet, and the reference cross-sectional area and diameter of the combustion chamber. The characteristic parameter θ is calculated according to the following formula (14):

[0097]

[0098] Where P3 is the combustion chamber inlet pressure, T3 is the combustion chamber inlet temperature, and A ref D is the reference cross-sectional area of ​​the combustion chamber. ref D is the reference cross-sectional diameter of the combustion chamber, i.e., the average mean diameter of the combustion chamber. ref =2R ref .

[0099] Based on the calculated characteristic parameter θ, substitute it into the combustion efficiency η calculation formula, as shown in equation (15):

[0100] η = -3.4464 44 θ 6 +1.0602 35 θ 5 -1.3018 27 θ 4

[0101] +8.1337 20 θ 3 -2.7268 12 θ 2+4.7037 5 θ-2.4597 2 (15)

[0102] Generally, the engine is required to have a design point combustion efficiency greater than 99.5%, an idle point combustion efficiency greater than 95%, and a high-altitude wind turbine point combustion efficiency greater than 80%. When the above design conditions are not met, the head reference speed V is determined based on equations (8) to (12). d Recalculate the reference cross-sectional area A of the combustion chamber ref Substitute these values ​​into equations (14) and (15) to recalculate the combustion chamber characteristic parameters θ and combustion efficiency η until the combustion efficiency design conditions are met.

[0103] Step S12: Based on the ratio between the length of the flame tube and the height of the head, determine the length range of the flame tube. Within the length range, iteratively calculate the combustion chamber outlet temperature distribution coefficient based on the given flame tube length. When the combustion chamber outlet temperature distribution coefficient is less than a preset threshold, determine the final flame tube length.

[0104] (v) Flame tube length L f With head height H d The proportional relationship is shown in equation (16):

[0105]

[0106] Within this length range, for example, taking a proportional value of 2.5, given an initial flame tube length, the combustion chamber outlet temperature distribution coefficient PF is checked using equation (17) based on this initial flame tube length:

[0107]

[0108] Wherein, ΔP f For the pressure loss of the flame tube, q ref For moving pressure head.

[0109] The preset threshold is set to 0.25. If the combustion chamber outlet temperature distribution coefficient PF obtained by iterative calculation according to equation (17) is less than 0.25, then the requirement is met. The current flame tube length L f The final flame tube length is determined; if it is greater than or equal to 0.25, the head reference velocity V is reselected. d The head height is recalculated based on equations (8) to (9), and the proportion value is reselected based on equation (16) to determine the flame tube length. Then, the recalculated head height and flame tube length are substituted into equation (17) to recalculate the combustion chamber outlet temperature distribution coefficient PF until the requirements are met. In this embodiment, the preset threshold of 0.25 is only an example. In other embodiments, the size of the preset threshold is not specifically limited according to the actual design requirements.

[0110] Step S13: Determine the flame tube tilt angle based on the combustion chamber inlet geometry, combustion chamber outlet geometry, and flame tube length.

[0111] (vi) Verify whether the inner and outer radii of the combustion chamber casing exceed the geometric constraints of the combustion chamber. If they do not meet the requirements, reselect the head reference velocity V. d Correspondingly, its head height and flame tube length are also recalculated.

[0112] The inner radius of the combustion chamber casing is the same as the inner radius R of the combustion chamber inlet. casing,in Its calculation formula is: R casing,in =R ref -H ref / 2, where R ref H is the reference cross-sectional radius of the combustion chamber. ref Let R be the reference cross-sectional height of the combustion chamber. casing,in If it is greater than the given minimum inner radius of the casing, then R represents... casing,in The design requirements are met; similarly, the outer radius of the combustion chamber casing is the same as the outer radius R of the combustion chamber inlet. casing,out Its calculation formula is: R casing,out =R ref +H ref / 2, if R casing,out If it is less than the given maximum outer radius of the casing, then R represents... casing,out To meet design requirements, the flame tube tilt angle needs to be determined within the constraints of the combustion chamber's geometric dimensions, assuming the inner and outer radii of the combustion chamber casing do not exceed the average inlet radius R of the combustion chamber. 3,mean Average radius R of combustion chamber outlet 4,mean and flame tube length L f The inclination angle α of the flame tube is calculated based on equation (18). L :

[0113]

[0114] In this embodiment, the design parameters also include: the outlet height of the pre-diffuser. Correspondingly, step S1 further includes:

[0115] Step S14: Determine the pre-diffuser loss value based on the pre-diffuser outlet height, combustion chamber inlet pressure, and combustion chamber inlet height;

[0116] Specifically, the diffuser design includes:

[0117] (vii) Based on the outlet height of the pre-diffuser and the inlet height of the combustion chamber h3, the inlet-outlet area ratio AR of the pre-diffuser is calculated as shown in equation (19):

[0118]

[0119] Among them, W 3.1 This refers to the outlet height of the pre-diffuser.

[0120] Based on the inlet and outlet area ratio AR of the pre-diffuser, the length-to-width ratio LW of the pre-diffuser is calculated as shown in equation (20):

[0121]

[0122] Given that the aspect ratio of the current diffuser meets the calculation requirements of equation (20), the length L of the sudden expansion section is further calculated based on the combustion chamber inlet height h3. dc As shown in equation (21):

[0123] L dc =(0.9~1.43)h3 (21)

[0124] Based on the inlet / outlet area ratio AR of the pre-diffuser and the combustion chamber inlet pressure P3, the pre-diffuser loss value ΔP is calculated. pd As shown in equation (22):

[0125]

[0126] Among them, C p Ma is the static pressure recovery coefficient. 3.0 γ is the Mach number at the combustion chamber inlet, and γ is the gas constant.

[0127] Step S15: Determine the pressure loss value of the sudden expansion section based on the outlet height of the pre-diffuser, the reference cross-sectional area of ​​the combustion chamber, and the inlet pressure of the combustion chamber;

[0128] Specifically, based on the inlet / outlet area ratio AR of the pre-diffuser and the reference cross-sectional area A of the combustion chamber. ref The pressure drop ΔP in the sudden expansion section is calculated based on the combustion chamber inlet pressure P3. dd As shown in equation (23):

[0129]

[0130] Among them, A 3.0 This refers to the diffuser inlet area.

[0131] Step S16: Determine the total diffuser loss value based on the pre-diffuser loss value and the pressure loss value of the sudden diffusion section;

[0132] Specifically, based on the pre-diffuser loss value ΔP pd Pressure loss value ΔP in the sudden expansion section dd The total diffuser loss ΔP is calculated based on the combustion chamber inlet pressure P3. dif As shown in equation (24):

[0133]

[0134] Step S17: When the total loss value of the diffuser is less than or equal to the preset loss threshold, the diffuser design requirements are met, and the combustion chamber flow path is drawn.

[0135] In this embodiment, the loss threshold is set to 2% during the diffuser design process. Figure 3 As shown in the figure, the horizontal axis represents the ratio of the length of the front diffuser to the height of the combustion chamber inlet, and the vertical axis represents the ratio of the height of the front diffuser outlet to the height of the combustion chamber inlet (i.e., the ratio of the inlet and outlet areas of the front diffuser). The diffuser designed based on the diffuser parameters calculated above must have performance below the dotted line indicated by the arrow in the figure to ensure that the diffuser does not stall and that the total diffuser loss does not exceed 2%, thus completing the diffuser design. Finally, based on the calculated head height H... d Combustion chamber inlet height h3, combustion chamber outlet height h4, flame tube length L f Flame tube tilt angle α L And the aspect ratio LW of the pre-diffuser and the length L of the sudden expansion section. dc Then, draw the flow path of the combustion chamber.

[0136] In this embodiment, refer to Figure 2 As shown, step S2 involves designing the combustion chamber flow distribution, specifically including:

[0137] Step S21: Determine the total effective opening area of ​​the flame tube;

[0138] (i) Based on the pressure loss ΔP of the flame tube f Calculate the air density ρ3 at the combustion chamber inlet and the jet velocity V of the flame tube. j As shown in equation (25):

[0139]

[0140] (ii) Based on the jet velocity V of the flame tube j Further calculations yielded the total effective opening area A of the flame tube. le As shown in equation (26):

[0141]

[0142] Among them, W a3 This refers to the airflow rate into the flame tube.

[0143] Step S22: Determine the cooling area of ​​the flame tube based on the reference cross-sectional radius of the combustion chamber, the length of the flame tube, and the head height;

[0144] (iii) Based on the reference cross-sectional radius R of the combustion chamberref Flame tube length L f Head height H d The cooling area A of the flame tube was calculated. lc As shown in equation (27):

[0145] A lc =π(2R) ref +H d )·L f +π(2R ref -H d )·L f (27)

[0146] Step S23: Determine the head cooling area based on the head flow distribution and the total effective opening area of ​​the flame tube;

[0147] (iv) Allocate μ based on head flow d The effective combustion air area A at the head can be obtained. da This allows for the further calculation of the head cooling area A. dc As shown in equation (28):

[0148]

[0149] Among them, C da The flow coefficient of the head cooling hole.

[0150] Step S24: Determine the cooling gas volume of the flame tube and the cooling gas volume of the head based on the cooling area of ​​the flame tube and the cooling area of ​​the head;

[0151] (v) Based on cooling parameter G c Combustion chamber inlet pressure P3 and head cooling area A dc and the cooling area A of the flame tube lc The cooling gas volume W of the flame tube can be calculated separately. lc and head cooling air volume W dc As shown in equations (29) and (30):

[0152] W lc =G C A lc P3 / 100 (29)

[0153] W dc =G C A dc P3 / 100 (30)

[0154] Step S25: Determine the distribution of cooling gas volume in the combustion chamber and the distribution of cooling gas volume in the head based on the total air flow rate at the combustion chamber inlet, the cooling gas volume in the flame tube, and the cooling gas volume in the head.

[0155] (vi) Based on the total air flow rate W3 at the combustion chamber inlet and the cooling gas flow rate W of the flame tube lc and head cooling air volume W dc The distribution of cooling gas volume μ in the flame tube can be calculated separately. lc and head cooling air volume distribution μ dc As shown in equations (31) and (32):

[0156] μ lc =W lc / W3 (31)

[0157] μ dc =W dc / W3 (32)

[0158] Step S2 also includes:

[0159] Step S26: Determine the head flow distribution based on the total equivalence ratio of the combustion chamber and the head equivalence ratio;

[0160] When there is no main combustion orifice in the combustion chamber, the mixing orifice gas distribution is determined based on the head flow distribution, the flame tube cooling gas distribution, and the head cooling gas distribution.

[0161] When a main combustion orifice exists in the combustion chamber, the flow distribution of the main combustion orifice is determined, and the flow distribution of the mixing orifice is determined based on the flow distribution of the main combustion orifice, the flow distribution of the head, the flow distribution of the flame tube cooling gas, and the flow distribution of the head cooling gas.

[0162] (vii) It should be noted that civil aircraft engine combustion chambers generally do not have main combustion ports; therefore, the calculation of main combustion port flow rate and main combustion port flow rate distribution does not need to be considered for civil aircraft combustion chambers. Therefore, based on the nose flow rate distribution μ... d Flame tube cooling gas distribution μ lc and head cooling air volume distribution μ dc The gas distribution μ in the mixed pores was calculated. hc As shown in equation (33):

[0163] μ hc =1-μ d -μ lc -μ dc (33)

[0164] Military engine combustion chambers typically have main combustion orifices, requiring consideration of the main combustion orifice flow rate and its distribution. The specific calculation process is as follows:

[0165] The total equivalence ratio Φ at the combustion chamber design point is known. dp The design equivalence ratio of the main combustion zone Φ pz Based on empirical values, the flow distribution in the combustion zone (i.e., the sum of the flow distribution in the main combustion zone and the head) is as shown in equation (34):

[0166] μ pz =Φ dp / Φ pz (34)

[0167] Further obtain the main combustion orifice flow distribution μ ph As shown in equation (35):

[0168] μ ph =μ pz -μ d -μ dc -μ pzc (35)

[0169] Where, μ pz Combustion zone flow distribution, μd is the head flow distribution, μ dc For the distribution of cooling air volume to the head, μ pzc Distribution of cooling gas volume to the main combustion zone flame tube.

[0170] Cooling gas distribution in the main combustion zone flame tube μ pzc The specific calculation process is as follows:

[0171] Generally speaking, the length L of the main combustion zone of the flame tube pz Height H of the flame tube head d The ratio range is 0.5 to 1, with a value of 0.6. The ratio relationship between the two is L. pz =0.6H d .

[0172] Based on the length L of the main combustion zone pz Height H of the flame tube head d The inner wall area A of the main combustion zone flame tube was calculated. pzi and the outer wall area A of the main combustion zone flame tube pzo As shown in equations (36) and (37):

[0173]

[0174]

[0175] Among them, D pzi The diameter of the inner wall of the main combustion zone flame tube, D pzo The outer wall diameter of the main combustion zone flame tube, α L D is the tilt angle of the flame tube. ref This is the reference cross-sectional diameter of the combustion chamber.

[0176] Based on the inner wall area A of the main combustion zone flame tube pzi and the outer wall area A of the main combustion zone flame tube pzo The cooling gas volume W in the main combustion zone was calculated. pzcAs shown in equation (38):

[0177] W pzc =G cpz *(A pzi +A pzo )*P3 / 100 (38)

[0178] Among them, G cpz The main combustion zone cooling parameters are P3 and P3 is the combustion chamber inlet pressure.

[0179] Based on the cooling gas volume W in the main combustion zone pzc Airflow rate W into the flame tube a3 The cooling gas distribution μ in the main combustion zone was calculated. pzc As shown in equation (39):

[0180] μ pzc =W pzc / W a3 (39)

[0181] Based on the distribution of cooling gas volume in the main combustion zone flame tube μ pzc The flow distribution μ of the main combustion orifice is calculated using equation (35). ph Head flow allocation μ d The value of μ based on the main combustion orifice flow distribution is obtained by equation (6). ph Head flow allocation μ d Flame tube cooling gas distribution μ lc and head cooling air volume distribution μ dc The flow distribution μ of the mixed pores was calculated. hc As shown in equation (40):

[0182] μ hc =1-μ d -μ dc -μ lc -μ ph (40)

[0183] Step S3: Based on the combustion chamber flow path and the flow distribution in the combustion chamber, construct a mathematical model corresponding to the combustion chamber optimization design objective;

[0184] Specifically, the optimization design target for low-emission combustion chambers in civil aircraft is nitrogen oxides (NOx). x For military aircraft combustion chamber optimization design, the goals are to achieve the lowest emissions and the highest combustion efficiency, with the widest stability boundary, the lowest smoke, and the highest combustion efficiency. For example, using the blunt body angle and blunt body exit height as target parameters, and nitrogen oxides (NOx) as the primary combustion parameters... xMinimizing the emission and combustion chamber outlet temperature distribution coefficient PF is the optimization design objective. With combustion efficiency EFF and total pressure loss Ploss as constraints, a mathematical model corresponding to the combustion chamber optimization design objective is constructed, as shown in equation (41):

[0185]

[0186] Step S4: Optimize the mathematical model based on preset sample points to obtain parameter values ​​for the head structure design parameters and a prediction model for combustion chamber emissions within a preset accuracy range. Specifically, this includes:

[0187] Step S41: Select multiple key parameters of the head structure as target parameters, and determine the target index values ​​of the target parameters;

[0188] Step S42: Using the sample points as initial sample points, optimize the mathematical model based on the target parameters to obtain the parameter combination;

[0189] Step S43: Combine the parameters and obtain the first index value of the target parameter through the simulation optimization platform;

[0190] Step S44: Compare the first indicator value with the target indicator value. If the comparison result is greater than or equal to the preset error threshold, replace the original value of the initial sample point with the first indicator value corresponding to the parameter combination, and bring it back to the mathematical model to continue iterative calculation until the comparison result is less than the preset error threshold. The iteration ends, and the obtained first indicator value is used as the parameter value of the head structure design parameter.

[0191] Step S45: Determine the first prediction model based on the parameter values ​​of the head structure design parameters to predict the emissions of nitrogen oxides from the combustion chamber.

[0192] Specifically, by constructing a joint simulation and optimization platform using Workbench and UG, and based on a genetic aggregation approximation model and a genetic algorithm, the micro-mixing unit of the hydrogen combustion chamber head structure was optimized. Several key parameters of the head structure were taken as target parameters. For a honeycomb micro-mixing hydrogen combustion chamber with an integrated bluff body, the key parameters were: bluff body angle and bluff body outlet height; for a honeycomb micro-mixing hydrogen combustion chamber with an integrated vortex generator, the key parameters were: vortex generator height, length, ramp angle, and hydrogen orifice position, etc. (Refer to...) Figure 2As shown, the basic process of multi-objective parameter optimization design of the head structure is as follows: Initially, a small number of sample points are used as initial sample points. Based on the target parameters, optimization calculations are performed on the mathematical model. The obtained parameter combinations are then fed back into the simulation software of the simulation optimization platform to calculate the first index value of the target parameters. The calculated first index value is compared with the target index value of the target parameters. If the comparison result does not meet the error requirements, the parameter combination is added to the initial sample points and the calculation continues until the comparison result is less than the preset error threshold. The iteration ends, and the first index value of the target parameters that meets the fitting accuracy requirements with the initial sample points as the first sampling range is obtained. In this way, high-precision target parameter values ​​can be obtained with a small number of sample points, which can be used as the parameter values ​​of the head structure design parameters.

[0193] The first prediction model is determined based on the parameter values ​​of the head structure design parameters. That is, the corresponding nitrogen oxide (NOx) is obtained by solving the problem through simulation calculation for each current sample point. x Emission values, based on parameter values ​​and nitrogen oxides (NOx) x The correlation between emission values ​​is fitted to generate a first prediction model to predict nitrogen oxide emissions from the combustion chamber. After the first prediction model is constructed, it can also be used to solve for nitrogen oxide (NOx) emissions within a given range. x The minimum value and the corresponding target parameters are then used in simulation software to calculate the nitrogen oxide (NO) value. x The emission results are simulated and calculated. The results of the simulation calculation are compared with those obtained by the first prediction model. If the error value is within the preset accuracy error threshold range, it indicates that the error between the two is relatively small, which verifies that the first prediction model is reliable and ensures the prediction accuracy.

[0194] In this embodiment, after step S4, the method further includes:

[0195] Add sample points based on the initial sample points;

[0196] Expand the parameter range of each target parameter;

[0197] Approximate the first prediction model and obtain the fitting coefficients;

[0198] Gradient optimization analysis is performed on the fitted first prediction model to obtain the optimal solution of each target parameter that satisfies the combustion chamber optimization design target within the parameter range corresponding to each target parameter. The optimal solution is used as the optimal parameter value of the target parameter.

[0199] Based on the fitting coefficients and optimal parameter values, the first prediction model is optimized to obtain the second prediction model.

[0200] Specifically, to construct a more accurate prediction model, additional sample points are added to the existing sample points. These additional sample points are generated using optimal Latin hypercube sampling and are used to approximate the first prediction model, obtaining the fitting coefficients. Gradient optimization analysis is then performed based on the fitted first prediction model. During optimization, the parameter range of each objective parameter is expanded; for example, for a certain objective parameter X... i The original parameter range was (-5, 5), and the expanded parameter range is (-10, 10), enabling it to obtain the optimal solution within a wider parameter range. The optimal solution is then used as the optimal parameter value for the target parameter. Based on the fitting coefficient and the optimal parameter value, the first prediction model is optimized to obtain the second prediction model, the calculation formula of which is shown in equation (42):

[0201] y = β0 + ∑β i x i +∑β i x i 2 +∑β i x i x j (42)

[0202] Where y is the optimization design objective, β0~β j X represents the fitting coefficient. i ~X j For design variables.

[0203] Through the above steps, the multi-objective parameter optimization design of the head structure can be traversed to reach all parameter combinations, ensuring that the optimal design scheme obtained is the optimal solution within the global parameter range. The verification method for the prediction accuracy of the second prediction model can refer to the first prediction model described above, and will not be repeated here.

[0204] In summary, the combustion chamber multi-process coupled optimization design method provided in this embodiment couples multiple design processes of the combustion chamber, including: combustion chamber flow path design, combustion chamber flow distribution design, and multi-objective parameter optimization design of the head structure. By coupling multiple design processes of the combustion chamber, the method can traverse all parameter combinations within the overall combustion chamber design scheme based on the mathematical model corresponding to the combustion chamber optimization design objective. The optimal solution obtained is the optimal solution within the global parameter range, thereby determining the prediction model corresponding to the combustion chamber optimization design objective. Based on the high-precision prediction of the prediction model, the selection of the optimal combustion chamber scheme is determined. Therefore, it improves the design efficiency and accuracy of designers, saves labor costs, improves combustion performance, reduces combustion chamber pollutant emissions, and broadens the stable combustion operating range, thereby improving the overall engine performance. Therefore, this invention has the advantages of high design efficiency and simple operation, overcoming the problems of long cycle and heavy reliance on engineer experience in existing combustion chamber optimization design methods.

[0205] Example 2

[0206] Based on the same inventive concept as the above method, and referring to... Figure 4 As shown, this embodiment provides a combustion chamber multi-process coupling optimization design device, including:

[0207] Combustion chamber flow path design module 21 is used to draw the combustion chamber flow path based on the combustion chamber design parameters;

[0208] Combustion chamber flow distribution module 22 is used to determine the flow distribution of the combustion chamber based on the combustion chamber flow path;

[0209] Combustion chamber optimization model construction module 23 is used to construct a mathematical model corresponding to the combustion chamber optimization design objective based on the fuel chamber flow path and the flow distribution in the combustion chamber.

[0210] The emission prediction model acquisition module 24 is used to optimize the mathematical model based on preset sample points in order to obtain the parameter values ​​of the head structure design parameters and the prediction model for combustion chamber emissions within a preset accuracy range.

[0211] In this embodiment, the combustion chamber flow path design module 21 specifically includes: a first calculation and determination unit, used to determine the combustion chamber inlet height, combustion chamber outlet height, head height, and combustion chamber reference cross-sectional area based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total combustion chamber inlet air flow rate; a second calculation and determination unit, used to determine the length range of the flame tube based on the ratio of the flame tube length to the head height, and iteratively calculate the combustion chamber outlet temperature distribution coefficient based on the given flame tube length within the length range. When the combustion chamber outlet temperature distribution coefficient is less than a preset threshold, the final flame tube length is determined; a third calculation and determination unit, used to determine the combustion chamber flow path design module 21 based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total combustion chamber inlet air flow rate; and a third calculation and determination unit, used to determine the combustion chamber flow path design module 21 based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total combustion chamber inlet air flow rate. The system comprises six units: a first unit for determining the diffuser inclination angle; a second unit for determining the diffuser inclination angle; a third unit for determining the diffuser loss value based on the diffuser outlet geometry, combustion chamber inlet pressure, and combustion chamber inlet height; a fourth unit for determining the pressure loss value of the sudden expansion section based on the diffuser outlet height, combustion chamber reference cross-sectional area, and combustion chamber inlet pressure; a fifth unit for determining the total diffuser loss value based on the diffuser loss value and the sudden expansion section pressure loss value; and a sixth unit for drawing the combustion chamber flow path when the total diffuser loss value is less than or equal to a preset loss threshold, meeting the diffuser design requirements.

[0212] The combustion chamber flow distribution module 22 specifically includes: a seventh calculation and determination unit for determining the total effective orifice area of ​​the flame tube; an eighth calculation and determination unit for determining the flame tube cooling area based on the combustion chamber reference cross-sectional radius, flame tube length, and head height; a ninth calculation and determination unit for determining the head cooling area based on the head flow distribution and the total effective orifice area of ​​the flame tube; a tenth calculation and determination unit for determining the flame tube cooling gas volume and the head cooling gas volume based on the flame tube cooling area and the head cooling area; and an eleventh calculation and determination unit for determining the total inlet air flow of the combustion chamber. The first unit calculates the cooling gas volume of the flame tube and the cooling gas volume of the head, and determines the cooling gas volume distribution of the flame tube and the head. The twelfth unit is used to determine the head flow distribution based on the total equivalence ratio of the combustion chamber and the head equivalence ratio. When there is no main combustion orifice in the combustion chamber, the mixing orifice gas volume distribution is determined based on the head flow distribution, the cooling gas volume distribution of the flame tube, and the cooling gas volume distribution of the head. Or, when there is a main combustion orifice in the combustion chamber, the main combustion orifice flow distribution is determined, and the mixing orifice gas volume distribution is determined based on the main combustion orifice flow distribution, the head flow distribution, the cooling gas volume distribution of the flame tube, and the cooling gas volume distribution of the head.

[0213] The emission prediction model acquisition module 24 specifically includes: a target parameter selection unit, used to select multiple key parameters of the head structure as target parameters and determine the target index values ​​of the target parameters; a parameter combination acquisition unit, used to use sample points as initial sample points, optimize the mathematical model based on the target parameters, and obtain parameter combinations; a target parameter simulation calculation unit, used to obtain the first index value of the target parameters through a simulation optimization platform; a parameter value acquisition unit, used to compare the first index value with the target index value, and if the comparison result is greater than or equal to a preset error threshold, the first index value corresponding to the parameter combination replaces the original value of the initial sample point and is brought back to the mathematical model for iterative calculation until the comparison result is less than the preset error threshold, the iteration ends, and the obtained first index value is used as the parameter value of the head structure design parameters; and a first prediction model determination unit, used to determine the first prediction model based on the parameter values ​​of the head structure design parameters to predict the emission of nitrogen oxides from the combustion chamber.

[0214] The emission prediction model acquisition module 24 also includes: a model verification unit, used to solve for the nitrogen oxides (NOx) within a given range using the first prediction model. x The minimum value and the corresponding target parameters are then used in simulation software to calculate the nitrogen oxide (NO) value. x The emission results are simulated and calculated. The results of the simulation calculation are compared with those obtained from the first prediction model to determine whether the error value is within the preset accuracy error threshold, thereby verifying the prediction accuracy of the model.

[0215] In this embodiment, the device further includes: an emission prediction model optimization module, specifically comprising: a sample point addition unit, used to add sample points based on the initial sample points; a parameter range expansion unit, used to expand the parameter range of each target parameter; a model fitting unit, used to approximate the first prediction model and obtain fitting coefficients; an optimal parameter value acquisition unit, used to perform gradient optimization analysis on the fitted first prediction model, obtain the optimal solution of each target parameter that satisfies the combustion chamber optimization design objective within the parameter range corresponding to each target parameter, and use the optimal solution as the optimal parameter value of the target parameter; and a second prediction model determination unit, used to optimize the first prediction model based on the fitting coefficients and the optimal parameter values ​​to obtain a second prediction model.

[0216] The specific implementation process of the functions and roles of each module in the above device can be found in the implementation process of the corresponding steps in the above method. Therefore, relevant parts can be referred to in the description of the method embodiment, and will not be repeated here.

[0217] The device embodiments described above are merely illustrative. For example, the division of modules is only a logical functional division. In actual implementation, there may be other division methods. In the embodiments, each functional module can be integrated into a processor, or each module can be a separate device, or two or more modules can be integrated into a device. Each functional module in each embodiment can be implemented in hardware or in the form of hardware plus software functional units.

[0218] Example 3

[0219] Reference Figure 5 As shown, this embodiment provides an electronic device, which includes a processor 310, a communication interface 320, a memory 330, and a communication bus 340. The processor 310, communication interface 320, and memory 330 communicate with each other via the communication bus 340. The processor 310 can call logical instructions from the memory 330, and executes the combustion chamber multi-process coupling optimization design method described in the above embodiment. This method includes:

[0220] Based on the combustion chamber design parameters, draw the combustion chamber flow path;

[0221] Based on the combustion chamber flow path, determine the flow distribution within the combustion chamber;

[0222] Based on the flow path in the fuel chamber and the flow distribution in the combustion chamber, a mathematical model corresponding to the optimization design objective of the combustion chamber is constructed;

[0223] The mathematical model is optimized based on preset sample points to obtain parameter values ​​of the head structure design parameters and a predictive model for combustion chamber emissions within a preset accuracy range.

[0224] Furthermore, the logical instructions in the aforementioned memory 330 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, essentially, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0225] On the other hand, the present invention also provides a computer program product, the computer program product comprising a computer program that can be stored on a non-transitory computer-readable storage medium, wherein when the computer program is executed by a processor, the computer is able to execute the combustion chamber multi-process coupling optimization design method described in the above method embodiments, the method comprising:

[0226] Based on the combustion chamber design parameters, draw the combustion chamber flow path;

[0227] Based on the combustion chamber flow path, determine the flow distribution within the combustion chamber;

[0228] Based on the flow path in the fuel chamber and the flow distribution in the combustion chamber, a mathematical model corresponding to the optimization design objective of the combustion chamber is constructed;

[0229] The mathematical model is optimized based on preset sample points to obtain parameter values ​​of the head structure design parameters and a predictive model for combustion chamber emissions within a preset accuracy range.

[0230] Example 4

[0231] This embodiment provides a non-transitory computer-readable storage medium storing a computer program thereon. When the computer program is executed by a processor, it implements the combustion chamber multi-flow coupling optimization design method described in the above method embodiment. The method includes:

[0232] Based on the combustion chamber design parameters, draw the combustion chamber flow path;

[0233] Based on the combustion chamber flow path, determine the flow distribution within the combustion chamber;

[0234] Based on the flow path in the fuel chamber and the flow distribution in the combustion chamber, a mathematical model corresponding to the optimization design objective of the combustion chamber is constructed;

[0235] The mathematical model is optimized based on preset sample points to obtain parameter values ​​of the head structure design parameters and a predictive model for combustion chamber emissions within a preset accuracy range.

[0236] The various embodiments in this invention are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the device and medium embodiments are relatively simple in description because they are fundamentally similar to the method embodiments; relevant parts can be referred to the descriptions in the method embodiments.

[0237] The devices, media, and methods provided in the embodiments of the present invention are one-to-one correspondences. Therefore, the devices and media also have similar beneficial technical effects as their corresponding methods. Since the beneficial technical effects of the methods have been described in detail above, the beneficial technical effects of the devices and media will not be repeated here.

[0238] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process method or product that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process method or product. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process method or product that includes that element.

[0239] The above are merely embodiments of the present invention and are not intended to limit the invention. Although the present invention has been described in detail above with general descriptions and specific embodiments, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of the present invention fall within the scope of protection claimed by the present invention.

Claims

1. A multi-flow coupled optimization design method for combustion chambers, characterized in that, include: Based on the combustion chamber design parameters, draw the combustion chamber flow path; The design parameters include: combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet temperature, combustion chamber inlet pressure, and total airflow at the combustion chamber inlet. Correspondingly, The step of drawing the combustion chamber flow path based on the combustion chamber design parameters includes: Based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total air flow rate at the combustion chamber inlet, determine the combustion chamber reference cross-sectional radius, combustion chamber inlet height, combustion chamber outlet height, head height, and combustion chamber reference cross-sectional area; Based on the ratio between the length of the flame tube and the height of the head, the length range of the flame tube is determined. Within the length range, the combustion chamber outlet temperature distribution coefficient is iteratively calculated based on the given flame tube length. When the combustion chamber outlet temperature distribution coefficient is less than a preset threshold, the final flame tube length is determined. The inclination angle of the flame tube is determined based on the geometry of the combustion chamber inlet, the geometry of the combustion chamber outlet, and the length of the flame tube. Based on the combustion chamber flow path, the flow distribution of the combustion chamber is determined; the step of determining the flow distribution of the combustion chamber based on the combustion chamber flow path includes: Determine the total effective opening area of ​​the flame tube; The cooling area of ​​the flame tube is determined based on the reference cross-sectional radius of the combustion chamber, the length of the flame tube, and the height of the head. The head cooling area is determined based on the head flow distribution and the total effective opening area of ​​the flame tube; Based on the cooling area of ​​the flame tube and the cooling area of ​​the head, the cooling gas volume of the flame tube and the cooling gas volume of the head are determined. The distribution of cooling air volume in the combustion chamber and the distribution of cooling air volume in the head are determined based on the total air flow rate at the combustion chamber inlet, the cooling air volume in the flame tube, and the cooling air volume in the head. Based on the combustion chamber flow path and the flow distribution in the combustion chamber, a mathematical model corresponding to the combustion chamber optimization design objective is constructed; The mathematical model is optimized based on preset sample points to obtain parameter values ​​of the head structure design parameters and a prediction model for combustion chamber emissions within a preset accuracy range.

2. The combustion chamber multi-flow coupled optimization design method according to claim 1, characterized in that, The step of optimizing the mathematical model based on preset sample points to obtain the head structure design parameters and the prediction model for combustion chamber emissions within a preset accuracy threshold range includes: Several key parameters of the head structure are selected as target parameters, and the target index values ​​of the target parameters are determined. Using the sample points as initial sample points, the mathematical model is optimized based on the target parameters to obtain parameter combinations; The first index value of the target parameter is obtained by using the parameter combination through a simulation optimization platform; The first indicator value is compared with the target indicator value. If the comparison result is greater than or equal to the preset error threshold, the first indicator value corresponding to the parameter combination replaces the original value of the initial sample point and is brought back to the mathematical model to continue iterative calculation until the comparison result is less than the preset error threshold. The iteration ends and the obtained first indicator value is used as the parameter value of the head structure design parameter. A first prediction model is determined based on the parameter values ​​of the head structure design parameters to predict the emission of nitrogen oxides from the combustion chamber.

3. The combustion chamber multi-flow coupled optimization design method according to claim 2, characterized in that, After the step of optimizing the mathematical model based on preset sample points to obtain the head structure design parameters and predict combustion chamber emissions within a preset accuracy threshold range, the method further includes: Add sample points based on the initial sample points; Expand the parameter range of each target parameter; Approximate the first prediction model and obtain the fitting coefficients; Gradient optimization analysis is performed on the fitted first prediction model to obtain the optimal solution of each target parameter that satisfies the combustion chamber optimization design target within the parameter range corresponding to each target parameter, and the optimal solution is used as the optimal parameter value of the target parameter. Based on the fitting coefficients and the optimal parameter values, the first prediction model is optimized to obtain the second prediction model.

4. The combustion chamber multi-flow coupled optimization design method according to claim 1, characterized in that, The design parameters also include: the outlet height of the pre-diffuser, correspondingly, The step of drawing the combustion chamber flow path based on the combustion chamber design parameters further includes: The pre-diffuser loss value is determined based on the pre-diffuser outlet height, the combustion chamber inlet pressure, and the combustion chamber inlet height. The pressure loss value of the sudden expansion section is determined based on the outlet height of the pre-diffuser, the reference cross-sectional area of ​​the combustion chamber, and the inlet pressure of the combustion chamber. The total diffuser loss value is determined based on the pre-diffuser loss value and the sudden diffusion section pressure loss value. When the total loss value of the diffuser is less than or equal to the preset loss threshold, the diffuser design requirements are met, and the combustion chamber flow path is drawn.

5. The combustion chamber multi-flow coupled optimization design method according to claim 1, characterized in that, The step of determining the flow distribution of the combustion chamber based on the combustion chamber flow path further includes: The head flow distribution is determined based on the total equivalence ratio of the combustion chamber and the head equivalence ratio. When there is no main combustion orifice in the combustion chamber, the mixing orifice gas distribution is determined based on the head flow distribution, the flame tube cooling gas distribution, and the head cooling gas distribution. When a main combustion orifice exists in the combustion chamber, the flow distribution of the main combustion orifice is determined, and the flow distribution of the mixing orifice is determined based on the flow distribution of the main combustion orifice, the flow distribution of the head, the flow distribution of the flame tube cooling gas, and the flow distribution of the head cooling gas.

6. A combustion chamber multi-flow coupling optimization design device, characterized in that, include: The combustion chamber flow path design module is used to draw the combustion chamber flow path based on the combustion chamber design parameters; The design parameters include: combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet temperature, combustion chamber inlet pressure, and total combustion chamber inlet air flow rate. Correspondingly, drawing the combustion chamber flow path based on the combustion chamber design parameters includes: determining the combustion chamber reference cross-sectional radius, combustion chamber inlet height, combustion chamber outlet height, head height, and combustion chamber reference cross-sectional area based on the combustion chamber inlet geometry, combustion chamber outlet geometry, combustion chamber inlet pressure, and total combustion chamber inlet air flow rate; determining the length range of the flame tube based on the ratio of the flame tube length to the head height; iteratively calculating the combustion chamber outlet temperature distribution coefficient based on the given flame tube length within the length range; determining the final flame tube length when the combustion chamber outlet temperature distribution coefficient is less than a preset threshold; and determining the flame tube tilt angle based on the combustion chamber inlet geometry, combustion chamber outlet geometry, and flame tube length. A combustion chamber flow distribution module is used to determine the flow distribution of the combustion chamber based on the combustion chamber flow path. The determination of the flow distribution based on the combustion chamber flow path includes: determining the total effective opening area of ​​the flame tube; determining the flame tube cooling area based on the combustion chamber reference cross-sectional radius, the flame tube length, and the head height; determining the head cooling area based on the head flow distribution and the total effective opening area of ​​the flame tube; determining the flame tube cooling gas volume and the head cooling gas volume based on the flame tube cooling area and the head cooling area; and determining the flame tube cooling gas volume distribution and the head cooling gas volume distribution based on the total inlet air flow of the combustion chamber, the flame tube cooling gas volume, and the head cooling gas volume. The combustion chamber optimization model construction module is used to construct a mathematical model corresponding to the combustion chamber optimization design objective based on the combustion chamber flow path and the flow distribution of the combustion chamber. The emission prediction model acquisition module is used to optimize the mathematical model based on preset sample points to obtain the parameter values ​​of the head structure design parameters and the prediction model for combustion chamber emissions within a preset accuracy range.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the combustion chamber multi-process coupling optimization design method as described in any one of claims 1-5.

8. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the combustion chamber multi-process coupling optimization design method as described in any one of claims 1-5.

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