Design method for large-scale scramjet combustion chamber

Abstract

The present invention relates to a method for designing a combustion chamber of a large-scale scramjet engine, comprising: S1. constructing a combustion chamber model, and obtaining the fuel injection position of the combustion chamber model based on the combustion chamber model, and determining the upstream section located upstream and the combustion section located downstream based on the fuel injection position; S2. respectively enlarging the upstream section and the combustion section of the combustion chamber model based on the obtained δ-Da scaling criterion to obtain a full-scale combustion chamber; wherein the δ-Da scaling criterion includes: a first criterion for scaling the upstream section, and a second criterion for scaling the combustion section. The scheme of the present invention can greatly reduce the time and economic cost of designing a combustion chamber of a full-scale large-scale scramjet engine.

Description

Technical Field

[0001] The present invention relates to the technical field of scramjet engine design, and in particular to a method for designing a combustion chamber of a large-scale scramjet engine. Background Art

[0002] The scramjet engine is mainly composed of an air inlet, a separation section, a combustion chamber and a tail nozzle. Because of its excellent performance at high flight Mach numbers, it is considered to be the preferred propulsion device for hypersonic aircraft. As the core component of the scramjet engine flow path design, the combustion chamber has always been the research focus in the field of hypersonic propulsion technology. The combustion chamber performance directly determines the overall design level of the scramjet engine.

[0003] At present, the development of large hypersonic aircraft, long-range hypersonic cruise missiles, and even large space planes has become a hot spot for research and competition among major aerospace powers. The development of large aircraft inevitably requires large-scale scramjet engine combustion chambers. In the current research on aircraft, considering the limitations of cost and size, most of them will conduct model tests under scaled conditions. However, the research goal is still the flight of full-scale aircraft. Furthermore, how to obtain a full-scale combustion chamber with the same / similar performance based on the combustion chamber model has become a problem that needs to be solved urgently.

[0004] At present, the geometric similarity criterion is usually used to scale up the combustion chamber model at a constant ratio to obtain the corresponding full-size combustion chamber. Although this scaling criterion is simple and convenient, it also has many disadvantages, such as:

[0005] 1. Ignoring the influence of the boundary layer in the combustion chamber, in fact, the thickness of the boundary layer in the engine combustion chamber is a factor that cannot be ignored, especially when the shock wave / boundary layer interference phenomenon is serious. According to the known flat plate turbulent boundary layer thickness formula:

[0006]

[0007] It can be seen that as the scale of the combustion chamber is enlarged, the incoming flow Reynolds number will increase, resulting in a decrease in the relative thickness of the incoming flow boundary layer, which will inevitably affect the incoming flow characteristics, mixing, and chemical reactions in the combustion chamber, and it is impossible to keep the flow field of the large-scale combustion chamber consistent with that of the model combustion chamber.

[0008] 2. When the combustion chamber maintains geometric similarity, the flow characteristic time in the combustion chamber will increase proportionally, while the chemical reaction time will be relatively shortened, resulting in the chemical reaction in the combustion chamber being unable to be similar. Summary of the invention

[0009] The purpose of the present invention is to provide a method for designing a large-scale scramjet engine combustion chamber.

[0010] To achieve the above-mentioned object of the invention, the present invention provides a method for designing a large-scale scramjet combustion chamber, comprising:

[0011] S1. constructing a combustion chamber model, and obtaining a fuel injection position of the combustion chamber model based on the combustion chamber model, and determining an upstream section located upstream and a downstream combustion section located downstream based on the fuel injection position;

[0012] S2. Based on the acquired δ-Da scaling criterion, the upstream section and the combustion section of the combustion chamber model are respectively enlarged to obtain a full-size combustion chamber; wherein the δ-Da scaling criterion includes: a first criterion for scaling the upstream section, and a second criterion for scaling the combustion section.

[0013] According to one aspect of the present invention, it also includes:

[0014] S3. Scale the operating conditions of the combustion chamber model based on the acquired δ-Da scaling criterion, wherein the operating conditions include: incoming flow conditions and fuel injection pressure; the δ-Da scaling criterion also includes: a third criterion for scaling the operating conditions.

[0015] According to one aspect of the present invention, the δ-Da scaling criterion is obtained by the following steps:

[0016] A1. Setting characteristic size parameters of the upstream section and the combustion section of the combustion chamber model, height parameters of the combustion section, and setting the flow conditions of the combustion chamber model;

[0017] A2. Setting characteristic dimension parameters of the upstream section and the combustion section of the full-size combustion chamber, height parameters of the combustion section, and setting the flow conditions of the full-size combustion chamber;

[0018] A3. Construct a set of equations based on the characteristic size parameter, the height parameter, and the incoming flow condition, wherein for the combustion section:

[0019] P1 m C1=P2 m C2

[0020]

[0021] For the upstream segment:

[0022]

[0023] Wherein, I1 represents the characteristic size parameter of the upstream section of the combustion chamber model; C1 represents the characteristic size parameter of the combustion section of the combustion chamber model; H1 represents the height parameter of the combustion section of the combustion chamber model; I2 represents the characteristic size parameter of the upstream section of the full-size combustion chamber; C2 represents the characteristic size parameter of the combustion section of the full-size combustion chamber; H2 represents the height parameter of the combustion section of the full-size combustion chamber; P1 represents the incoming flow pressure in the incoming flow condition for the combustion chamber model; P2 represents the incoming flow pressure in the incoming flow condition for the full-size combustion chamber;

[0024] A4. Obtaining the first criterion and the second criterion based on the set of equations; wherein the first criterion is expressed as:

[0025]

[0026] Among them, n and m are constants;

[0027] The second criterion is expressed as:

[0028]

[0029] According to one aspect of the present invention, the incoming flow conditions further include: incoming flow Mach number and incoming flow temperature;

[0030] The step of obtaining the δ-Da scaling criterion further includes:

[0031] A5. Obtain the third criterion based on the incoming flow Mach number, the incoming flow temperature, and the set of equations in step A3; wherein the third criterion is expressed as:

[0032]

[0033] Among them, Ma1 represents the incoming flow Mach number in the incoming flow conditions for the combustion chamber model; Ma2 represents the incoming flow Mach number in the incoming flow conditions for the full-size combustion chamber; T1 represents the incoming flow temperature in the incoming flow conditions for the combustion chamber model; T2 represents the incoming flow temperature in the incoming flow conditions for the full-size combustion chamber.

[0034] According to one aspect of the present invention, in step S2, the upstream section and the combustion section of the combustion chamber model are respectively enlarged based on the acquired δ-Da scaling criterion to obtain a full-size combustion chamber, including:

[0035] Based on the first criterion, the upstream section of the combustion chamber model is proportionally enlarged times to obtain the upstream section of the full-size combustion chamber;

[0036] Based on the second criterion, the combustion section of the combustion chamber model is magnified n times to obtain the combustion section of the full-size combustion chamber, and based on the second criterion, the injection hole size of the fuel injection position is magnified n times.

[0037] According to one aspect of the present invention, in step S3, in the step of scaling the operating conditions of the combustion chamber model based on the acquired δ-Da scaling criterion, the operating conditions are scaled based on the third criterion; wherein, the step includes:

[0038] Keeping the incoming flow Mach number in the incoming flow condition of the combustion chamber model consistent with the incoming flow Mach number in the incoming flow condition of the full-size combustion chamber;

[0039] Keeping the incoming flow temperature in the incoming flow condition of the combustion chamber model consistent with the incoming flow temperature in the incoming flow condition of the full-size combustion chamber;

[0040] The incoming flow pressure in the incoming flow condition of the combustion chamber model is amplified times as the incoming flow pressure in the incoming flow condition of the full-size combustion chamber, and, simultaneously, amplifying the fuel injection pressure at the fuel injection position by the same ratio times.

[0041] According to one aspect of the present invention, the combustion chamber model and the full-size combustion chamber both adopt a hydrogen-air system; wherein m is 1.6 to 1.7.

[0042] To achieve the above-mentioned object of the invention, the present invention provides a design system for the aforementioned large-scale scramjet engine combustion chamber design method, comprising:

[0043] A scaling criterion determination module, used to obtain a δ-Da scaling criterion for scaling the combustion chamber model to generate a full-size combustion chamber, wherein the δ-Da scaling criterion includes: a first criterion for scaling an upstream section of the combustion chamber model, a second criterion for scaling a combustion section of the combustion chamber model, and a third criterion for scaling an incoming flow condition of the combustion chamber model;

[0044] A data acquisition module, used to collect data from the constructed combustion chamber model, obtain characteristic size parameters of the upstream section of the combustion chamber model, height parameters of the combustion section, and obtain operating conditions of the combustion chamber model;

[0045] The full-size combustion chamber generation module performs scaling processing based on the δ-Da scaling criterion obtained by the scaling criterion determination module, the characteristic size parameters collected by the data acquisition module, the height parameters of the combustion section and the operating conditions, so as to obtain the full-size combustion chamber corresponding to the combustion chamber model and the operating conditions for the full-size combustion chamber.

[0046] To achieve the above-mentioned object of the invention, the present invention provides a large-scale scramjet engine combustion chamber, which is designed using the large-scale scramjet engine combustion chamber design method as described above.

[0047] To achieve the above-mentioned object of the invention, the present invention provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the above-mentioned large-scale scramjet engine combustion chamber design method is executed.

[0048] According to one solution of the present invention, the solution of the present invention can greatly reduce the time and economic cost of designing a full-size large-scale scramjet engine combustion chamber.

[0049] According to one scheme of the present invention, by adopting the design method of the present invention and using different scaling rules for different sections of the model combustion chamber, the obtained full-size combustion chamber can ensure the similarity of the combustion flow field with the model combustion chamber and ensure the consistency of the flame stabilization effect.

[0050] According to one solution of the present invention, the δ-Da scaling criterion of the present invention takes into account the influence of the downflow boundary layer at different scales, fully ensures that the inflow parameters of different combustion chambers are similar, ensures the combustion similarity, and thus makes the flame stabilization effect the same at different scales.

[0051] According to a scheme of the present invention, the combustion efficiency and thrust performance of a large-scale engine can be accurately estimated according to the δ-Da scaling criterion, which greatly improves the design efficiency of the combustion chamber of a large-scale scramjet engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] Figure 1 is a flowchart schematically showing a method for designing a large-scale scramjet combustion chamber according to an embodiment of the present invention;

[0053] Figure 2 is a flow chart schematically showing a method for designing a large-scale scramjet combustion chamber according to an embodiment of the present invention;

[0054] Figure 3 It is a schematic diagram of the internal fuel distribution cloud diagram of a basic calculation example case N1 of a combustion chamber model;

[0055] Figure 4 It is a schematic representation based on Figure 3 The internal fuel distribution cloud diagram of the case N2 obtained by fully scaling up the basic example in the middle;

[0056] Figure 5 It is a schematic representation based on Figure 3 The internal fuel distribution cloud diagram of the case N2-Da obtained by scaling the basic example using the δ-Da scaling criterion;

[0057] Figure 6 is a diagram schematically showing the fuel distribution contour pressure curves of the basic calculation case N1, the calculation case N2, and the calculation case N2-Da;

[0058] Figure 7 It is a diagram schematically showing the combustion efficiency of the basic calculation case N1, the calculation case N2, and the calculation case N2-Da. DETAILED DESCRIPTION

[0059] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0060] For the combustion chamber of a large-scale scramjet engine, the stable internal flow and accurate similarity of combustion between the two combustion flows in the combustion chambers of different sizes are a very strict requirement, which means that all sub-processes of combustion, although occurring at different scales, occur in the same way. Therefore, although the actual scale of the large-scale combustion chamber and the model combustion chamber may be different, the flow characteristics, flame pattern, generation of combustion products and location of heat release should be geometrically similar.

[0061] To this end, for the compressible combustion flow field, considering the mass, momentum and energy conservation equations of the combustion flow, a set of dimensionless parameters formed by the superposition of a set of dimensionless differential equations is identified, and a set of similarity parameters of the internal gas thermochemistry of the compressible combustion flow field can be obtained. For the reaction of a multi-component gas mixture ignoring the effects of gravity, radiation heat transfer and thermal diffusion, this complete set of combustion similarity parameters is:

[0062] Reynolds number:

[0063] Schmidt number:

[0064] Prandtl number:

[0065] Mach number:

[0066] Specific Heat Ratio:

[0067] Ratio of kinetic energy to internal energy:

[0068] The first Damklee number:

[0069] The third Damklee number:

[0070] Among them, the first six dimensionless numbers are similar parameters in common non-reacting flows: Reynolds number (Re) is the ratio of inertial force to viscous force per unit volume, Schmidt number (Sc) is the ratio of dynamic viscosity to molecular diffusivity, Prandtl number (Pr) is the ratio of momentum diffusivity to thermal diffusivity, and Mach number (Ma) is the ratio of flow kinetic energy to internal energy (or velocity to speed of sound);

[0071] The chemical reaction in the flow process is characterized by two Damkle numbers (Da numbers). Da,i is the convection time L / v and the chemical time τ i Da,iii is the ratio of the transport of component substances caused by chemical reaction to the transport of component substances caused by convection. Da,iii is the heating rate of chemical reaction per unit volume q' / τ i and the convective heat transfer rate vc p T / L ratio.

[0072] From the above eight dimensionless criteria, it can be seen that if the inflow gas parameter conditions of the model combustion chamber and the large-scale combustion chamber are guaranteed to remain unchanged, the five parameters Sc, Ma, Pr, γ, and φ can remain unchanged;

[0073] In addition, due to It can be found that Re and Da,i cannot be guaranteed to be the same at different scales.

[0074] Therefore, an attempt is made to change the incoming flow pressure in the incoming flow condition to make Re and Da,i the same at different scales.

[0075] For Re, keeping Re the same at different scales is mainly to ensure the relative thickness of the boundary layer (δ / H, H is the height of the combustion chamber):

[0076]

[0077] The subscripts 1 and 2 represent two different scales.

[0078] Combined with the known flat plate turbulent boundary layer thickness formula:

[0079]

[0080] You can get:

[0081]

[0082] Keeping Da,i the same is mainly to ensure the consistency of flow chemical reaction coupling. For Da,i, it mainly involves two scales in the combustion chamber. The flow characteristic time is basically proportional to the combustion chamber size, and the focus is on the chemical reaction time. The total chemical time is the sum of the ignition time and the combustion time:

[0083] τ i =τ ignition +τ combustion

[0084] Generally speaking, chemical reaction time is related to temperature and pressure, namely:

[0085]

[0086] For the hydrogen-air system, m = 1.6 ~ 1.7, combined with the first Damklee number formula, we have:

[0087]

[0088] Combining formula (1) and formula (2), it can be seen that by changing the incoming flow pressure, if formula (1) is guaranteed to be the same, that is, the incoming flow boundary layer characteristics are guaranteed to be the same, then formula (2) cannot be guaranteed to be the same, that is, the chemical reaction characteristics cannot be guaranteed to be the same.

[0089] To this end, according to an embodiment of the present invention, two scaling criteria are applied to different positions of the combustion chamber according to the specific physical and chemical processes in the combustion chamber, and a new scale scaling criterion is proposed, which is called the δ-Da scaling criterion. In this embodiment, the fuel basin bead position based on the combustion chamber model is used as the dividing line, and the upstream of the fuel injection that is basically not involved in the chemical reaction (called the upstream section) is scaled according to the δ / H=const criterion, that is, the first criterion, and the downstream of the fuel injection that involves the chemical reaction (called the combustion section) is scaled according to the Da,i=const criterion, that is, the second criterion. Furthermore, the specific steps for obtaining the δ-Da scaling criterion include:

[0090] A1. Setting characteristic size parameters of the upstream section and the combustion section of the combustion chamber model, height parameters of the combustion section, and setting the incoming flow conditions of the combustion chamber model;

[0091] A2. Setting characteristic size parameters of the upstream section and the combustion section of the full-size combustion chamber, height parameters of the combustion section, and setting the incoming flow conditions of the full-size combustion chamber;

[0092] A3. Construct a set of equations based on characteristic size parameters, height parameters, and incoming flow conditions, where for the combustion section:

[0093] P1m C1=P2 m C2

[0094]

[0095] For the upstream segment:

[0096]

[0097] Wherein, I1 represents the characteristic size parameter of the upstream section of the combustion chamber model; C1 represents the characteristic size parameter of the combustion section of the combustion chamber model; H1 represents the height parameter of the combustion section of the combustion chamber model; I2 represents the characteristic size parameter of the upstream section of the full-size combustion chamber; C2 represents the characteristic size parameter of the combustion section of the full-size combustion chamber; H2 represents the height parameter of the combustion section of the full-size combustion chamber; P1 represents the incoming flow pressure in the incoming flow condition for the combustion chamber model; P2 represents the incoming flow pressure in the incoming flow condition for the full-size combustion chamber;

[0098] A4. Obtaining the first criterion and the second criterion based on the set of equations; In this embodiment, the set of equations corresponding to the upstream section and the combustion section in step A3 can be combined to obtain the corresponding first criterion and the second criterion; Specifically, the first criterion is expressed as:

[0099]

[0100] Among them, n and m are constants;

[0101] The second criterion is expressed as:

[0102]

[0103] In this embodiment, since the upstream section and the combustion section of the combustion chamber model are scaled based on the δ-Da scaling criterion, the size (e.g., diameter) of the structure (i.e., the fuel injection port) at the boundary of the upstream section and the combustion section also needs to be scaled to match the obtained full-size combustion chamber. In this embodiment, since the combustion section is geometrically enlarged according to the second criterion, the size of the fuel injection port at the fuel injection position is also geometrically enlarged according to the second criterion to adapt to the obtained full-size combustion chamber, which can be expressed as:

[0104]

[0105] Wherein, d1 represents the fuel injection port size of the combustion chamber model, and d2 represents the fuel injection port size of the full-size combustion chamber.

[0106] In this embodiment, the incoming flow condition also includes: the incoming flow Mach number and the incoming flow temperature; similarly, the δ-Da scaling criterion also includes: a third criterion for scaling the incoming flow condition. Furthermore, the step of obtaining the δ-Da scaling criterion also includes:

[0107] A5. Obtain a third criterion based on the incoming flow Mach number, the incoming flow temperature, and the equation group in step A3; wherein the third criterion is expressed as:

[0108]

[0109] Among them, Ma1 represents the incoming flow Mach number in the incoming flow conditions for the combustion chamber model; Ma2 represents the incoming flow Mach number in the incoming flow conditions for the full-size combustion chamber; T1 represents the incoming flow temperature in the incoming flow conditions for the combustion chamber model; T2 represents the incoming flow temperature in the incoming flow conditions for the full-size combustion chamber.

[0110] Furthermore, combined with Figure 1 and Figure 2 As shown, according to one embodiment of the present invention, a large-scale scramjet engine combustion chamber design method of the present invention is designed based on the aforementioned acquired δ-Da scaling criterion, specifically comprising:

[0111] S1. constructing a combustion chamber model, and obtaining a fuel injection position of the combustion chamber model based on the combustion chamber model, and determining an upstream section and a downstream combustion section based on the fuel injection position;

[0112] S2. Based on the obtained δ-Da scaling criterion, the upstream section and the combustion section of the combustion chamber model are enlarged respectively to obtain a full-size combustion chamber; wherein the δ-Da scaling criterion includes: a first criterion for scaling the upstream section and a second criterion for scaling the combustion section. In this embodiment, based on the first criterion, the upstream section of the combustion chamber model is enlarged proportionally. times to obtain the upstream section of the full-size combustion chamber; based on the second criterion, the combustion section of the combustion chamber model is proportionally enlarged by n times to obtain the combustion section of the full-size combustion chamber, and, based on the second criterion, the injection hole size of the fuel injection position is proportionally enlarged by n times.

[0113] According to one embodiment of the present invention, a large-scale scramjet engine combustion chamber design method of the present invention, in the process of designing based on the aforementioned acquired δ-Da scaling criterion, further includes:

[0114] S3. Scaling the operating conditions of the combustion chamber model based on the acquired δ-Da scaling criterion, wherein scaling the operating conditions based on the third criterion specifically includes:

[0115] Keep the incoming flow Mach number in the incoming flow condition of the combustion chamber model consistent with the incoming flow Mach number in the incoming flow condition of the full-scale combustion chamber;

[0116] Keep the incoming flow temperature in the incoming flow condition of the combustion chamber model consistent with the incoming flow temperature in the incoming flow condition of the full-scale combustion chamber;

[0117] Amplify the incoming flow pressure in the incoming flow condition of the combustion chamber model times as the incoming flow pressure in the incoming flow conditions of a full-size combustion chamber.

[0118] In this embodiment, since the incoming flow conditions of the full-size combustion chamber have changed, the corresponding fuel injection pressure at the fuel injection position also needs to be changed accordingly. In this embodiment, while the incoming flow pressure is amplified, the fuel injection pressure is also amplified to the original times, so that it can meet the fuel injection requirements of a full-size combustion chamber.

[0119] According to one embodiment of the present invention, both the combustion chamber model and the full-size combustion chamber adopt a hydrogen-air system, wherein m is 1.6 to 1.7.

[0120] According to the present invention, by analyzing similar parameters of flame stabilization in supersonic combustion flow fields, the variation law of the incoming flow parameters and combustion chamber size of a large-scale combustion chamber is obtained to achieve the same flame stabilization effect when designing a large-scale engine combustion chamber based on a model combustion chamber. This scaling criterion can greatly reduce the time and economic cost of designing a full-scale engine combustion chamber.

[0121] To further illustrate the present invention, the present invention is exemplified with reference to the accompanying drawings.

[0122] A combustion chamber model of a hydrogen-air system is constructed as a basic example and recorded as case N1 (see Figure 3 ), the supersonic inflow state of the combustion chamber model is set to Mach number 2.52, total temperature 1486K and total pressure 1.5MPa, hydrogen is used as fuel for wall injection, the injection speed is a Mach number, the injection total temperature is 300K, and the total pressure is 1.6Mpa.

[0123] In order to facilitate comparison with this solution, the traditional full proportional enlargement method is used to enlarge it to obtain a reference case. For example, the enlargement factor is 2, and the basic case N1 is proportionally enlarged and recorded as case N2 (see Figure 4 );

[0124] According to the scheme of the present invention, the δ-Da scaling criterion is adopted. For the combustion chamber model, the combustion section is proportionally enlarged n times (where n is 2), and the upstream section is enlarged n times. 1.093times to obtain the corresponding full-size combustion chamber, and the supersonic flow pressure and fuel injection pressure are scaled to times, the temperature and Mach number remain unchanged, and the case N2-Da is amplified by the δ-Da scaling criterion (see Figure 5 );

[0125] Combination Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown in the figure, after adopting the traditional full proportional amplification method, the thickness of the incoming flow boundary layer becomes relatively thinner, resulting in the fuel penetration depth of the case N2 being lower than that of the basic case N1. The fuel distribution of the full-size combustion chamber (i.e., the case N2-Da) obtained by adopting the δ-Da scaling criterion of the present invention is relatively consistent with and basically overlaps with that of the basic case N1, indicating that the air-dried fuel flow field has great similarity.

[0126] like Figure 7 As shown in the combustion efficiency comparison diagram of the basic case N1, the case N2 and the case N2-Da, it can be seen that after the combustion chamber is enlarged by the traditional completely proportional enlargement method, the combustion efficiency distribution in the combustion chamber of the case N2 is higher than that of the combustion chamber of the basic case N1; the combustion efficiency distribution curves of the case N2-Da scaled according to the δ-Da criterion of the present invention are consistent with the overall trend of the basic case N1, and almost overlap, indicating that there is a strong correlation between the two, which again illustrates from a quantitative perspective that the combustion flow fields of the two are very similar.

[0127] It can be seen from the above numerical calculation results that scaling the combustion chamber using the δ-Da scaling criterion of the present invention can ensure the similarity of the combustion flow field in the combustion chamber and the consistency of the flame stabilization effect.

[0128] According to one embodiment of the present invention, a design system for the aforementioned large-scale scramjet engine combustion chamber design method of the present invention comprises:

[0129] A scaling criterion determination module is used to obtain a δ-Da scaling criterion for scaling the combustion chamber model to generate a full-size combustion chamber, wherein the δ-Da scaling criterion includes: a first criterion for scaling an upstream section of the combustion chamber model, a second criterion for scaling a combustion section of the combustion chamber model, and a third criterion for scaling an incoming flow condition of the combustion chamber model;

[0130] A data acquisition module is used to collect data from the constructed combustion chamber model, obtain characteristic size parameters of the upstream section of the combustion chamber model, height parameters of the combustion section, and obtain operating conditions of the combustion chamber model;

[0131] The full-size combustion chamber generation module performs scaling processing on the δ-Da scaling criteria obtained by the scaling criteria determination module, the characteristic size parameters collected by the data acquisition module, the height parameters of the combustion section and the operating conditions, so as to obtain the full-size combustion chamber corresponding to the combustion chamber model and the operating conditions for the full-size combustion chamber.

[0132] According to one embodiment of the present invention, the present invention provides a large-scale scramjet engine combustion chamber, which is designed using the aforementioned large-scale scramjet engine combustion chamber design method.

[0133] According to one embodiment of the present invention, the present invention provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the aforementioned large-scale scramjet engine combustion chamber design method is executed. In this embodiment, the computer-readable storage medium may include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchl ink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0134] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

[0135] The above is only one solution of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. Design method of large-scale scramjet combustion chamber, include: S1. constructing a combustion chamber model, and obtaining a fuel injection position of the combustion chamber model based on the combustion chamber model, and determining an upstream section located upstream and a downstream combustion section located downstream based on the fuel injection position; S2. Based on acquisition δ - Da The upstream section and the combustion section of the combustion chamber model are respectively enlarged according to the scaling criterion to obtain a full-size combustion chamber; wherein the δ - Da The scaling criteria include: a first criterion for scaling the upstream section, and a second criterion for scaling the combustion section; S3. Based on acquisition δ - Da The scaling criterion scales the operating conditions of the combustion chamber model, wherein the operating conditions include: incoming flow conditions and fuel injection pressure; δ - Da The scaling criteria also include: a third criterion for scaling the operating condition; Said δ - Da The scaling criteria are obtained using the following steps: A1. Setting characteristic size parameters of the upstream section and the combustion section of the combustion chamber model, height parameters of the combustion section, and setting the flow conditions of the combustion chamber model; A2. Setting characteristic dimension parameters of the upstream section and the combustion section of the full-size combustion chamber, height parameters of the combustion section, and setting the flow conditions of the full-size combustion chamber; A3. Construct a set of equations based on the characteristic size parameter, the height parameter, and the incoming flow condition, wherein for the combustion section: For the upstream segment: in, I 1 Characteristic size parameters representing the upstream section of the combustion chamber model; C 1 Characteristic size parameters representing the combustion section of the combustion chamber model; H 1 A height parameter representing the combustion section of the combustion chamber model; I 2 Characteristic dimensional parameters representing the upstream section of the full-scale combustion chamber; C 2 Characteristic dimensional parameters representing the combustion section of the full-scale combustion chamber; H 2 A height parameter representing the combustion section of the full-size combustion chamber; P 1 represents the incoming flow pressure in the incoming flow condition for the combustion chamber model; P 2 represents the incoming flow pressure in the incoming flow condition for the full-scale combustion chamber; A4. Obtaining the first criterion and the second criterion based on the set of equations; wherein the first criterion is expressed as: Among them, n and m are constants; The second criterion is expressed as: ； The incoming flow conditions also include: incoming flow Mach number and incoming flow temperature; Get the δ - Da The steps of scaling criteria also include: A5. Obtain the third criterion based on the incoming flow Mach number, the incoming flow temperature, and the set of equations in step A3; wherein the third criterion is expressed as: in, Ma 1 represents the incoming flow Mach number in the incoming flow condition for the combustion chamber model; Ma 2 represents the incoming flow Mach number in the incoming flow condition for the full-scale combustion chamber; T 1 represents the incoming flow temperature in the incoming flow condition for the combustion chamber model; T 2 represents the incoming flow temperature in the incoming flow conditions for the full-scale combustor.

2. The large-scale scramjet combustion chamber design method according to claim 1, It is characterized in that In step S2, based on the obtained δ - Da The step of respectively enlarging the upstream section and the combustion section of the combustion chamber model according to the scaling criterion to obtain a full-size combustion chamber comprises: Based on the first criterion, the upstream section of the combustion chamber model is proportionally enlarged times to obtain the upstream section of the full-size combustion chamber; Based on the second criterion, the combustion section of the combustion chamber model is magnified n times to obtain the combustion section of the full-size combustion chamber, and based on the second criterion, the injection hole size of the fuel injection position is magnified n times.

3. The large-scale scramjet combustion chamber design method according to claim 2, It is characterized in that In step S3, based on the obtained δ - Da In the step of scaling the operating conditions of the combustion chamber model according to the scaling criterion, the operating conditions are scaled based on the third criterion; wherein, the step includes: Keeping the incoming flow Mach number in the incoming flow condition of the combustion chamber model consistent with the incoming flow Mach number in the incoming flow condition of the full-size combustion chamber; Keeping the incoming flow temperature in the incoming flow condition of the combustion chamber model consistent with the incoming flow temperature in the incoming flow condition of the full-size combustion chamber; The incoming flow pressure in the incoming flow condition of the combustion chamber model is amplified times as the incoming flow pressure in the incoming flow condition of the full-size combustion chamber, and simultaneously amplifying the fuel injection pressure at the fuel injection position times.

4. The large-scale scramjet combustion chamber design method according to claim 3, It is characterized in that The combustion chamber model and the full-size combustion chamber both adopt a hydrogen-air system, wherein m is 1.6 to 1.

7.

5. A design system for the large-scale scramjet engine combustion chamber design method according to any one of claims 1 to 4, It is characterized in that include: A scaling criterion determination module is used to obtain the scaling criteria for the combustion chamber model to generate a full-size combustion chamber. δ - Da Scaling criteria, where the δ - Da The scaling criteria include: a first criterion for scaling the upstream section of the combustion chamber model, a second criterion for scaling the combustion section of the combustion chamber model, and a third criterion for scaling the incoming flow condition of the combustion chamber model; A data acquisition module, used to collect data from the constructed combustion chamber model, obtain characteristic size parameters of the upstream section of the combustion chamber model, height parameters of the combustion section, and obtain operating conditions of the combustion chamber model; A full-size combustion chamber generation module is provided, based on the scaling criteria to determine the module to obtain δ - Da The scaling criteria, as well as the characteristic size parameters, the height parameters of the combustion section and the operating conditions collected by the data acquisition module are scaled respectively to obtain the full-size combustion chamber corresponding to the combustion chamber model and to obtain the operating conditions for the full-size combustion chamber.

6. A large-scale scramjet combustion chamber, It is characterized in that The design is performed using the large-scale scramjet engine combustion chamber design method as described in any one of claims 1 to 4.

7. A computer-readable storage medium, It is characterized in that The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method for designing a large-scale scramjet engine combustion chamber according to any one of claims 1 to 4 is executed.

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