Cold spraying equivalent simulation method, device and equipment for aircraft fuel gas jet flow and medium

Abstract

The invention relates to the technical field of cold spraying equivalent simulation, in particular to a cold spraying equivalent simulation method, device and equipment for aircraft gas jet flow and a medium. The cold spraying equivalent simulation method comprises the steps that thermal state flow field parameters in an engine combustion chamber and a spraying pipe are obtained; on the basis of the obtained thermal state flow field parameters in the engine combustion chamber and the spray pipe, cold spray pipe outlet conditions are determined according to a cold spray equivalence principle; adjusting the profile of the cold-jet nozzle according to the outlet condition of the cold-jet nozzle and the isentropic relational expression, and obtaining inlet parameters of the cold-jet nozzle; the molded surface of the spray pipe is optimized, so that the jet flow boundaries of cold spraying and hot spraying are consistent; and completing equivalent simulation of the gas jet flow of the aircraft according to the inlet parameters of the cold jet pipe and the molded surface of the cold jet pipe obtained through equivalence. According to the method, simulation of aircraft fuel gas jet flow in computational fluid mechanics is simplified, mixing of different media does not need to be considered any more, and the calculation amount is reduced; the device can also be popularized to a ground jet flow simulation test, and the test design is simplified.

Description

Technical Field

[0001] The invention relates to the technical field of cold spray equivalent simulation, and in particular to a cold spray equivalent simulation method, device, equipment and medium for aircraft gas jet. Background Art

[0002] Modern aircraft such as rockets, missiles, and aerospace aircraft are equipped with various types of jet engines. The high-temperature and high-pressure gas generated by the jet interacts with the incoming flow or directly interferes with the body, which will produce complex flow phenomena such as shock wave\boundary layer interference, shock wave\shock wave interference, and multi-scale flow separation, which makes it extremely difficult to accurately predict the aerodynamic performance and thus affects the reliability of the aerodynamic design of the aircraft. Therefore, accurately simulating the aerodynamic interference characteristics of the gas jet has become an important part of the development of aircraft with jet engines.

[0003] There are generally two methods for simulating aircraft gas jets: hot spray and equivalent cold spray. In the hot spray method, the incoming flow is air medium, and the engine gas is another (or multiple) medium. Cold spray equivalent treats the gas as air, that is, the entire flow field is the same medium. The thermal spray simulation of aircraft gas jets is very difficult for both ground tests and numerical simulations. Hot spray simulation places strict requirements on ground test equipment. First, the device for generating high-temperature gas flow is very complex, and the test equipment and costs are greatly increased; second, the high-temperature and high-pressure air flow delivery technology is also difficult to solve, and the gas flow erodes the wall of the wind tunnel nozzle very seriously; therefore, hot spray simulation experiments are difficult to carry out. For the numerical simulation of aircraft gas jets, the calculation model and equations are complex, the calculation stability is poor, and the calculation amount is huge; using a suitable cold spray equivalent method can greatly simplify the calculation process and reduce the calculation amount. Summary of the invention

[0004] The first purpose of the present invention is to provide a cold spray equivalent simulation method, device, equipment and medium for aircraft gas jets, so as to overcome the shortcomings of the prior art, simplify the complexity of aircraft gas jet simulation, and solve the problem that jet tests and jet numerical simulations are difficult to implement due to their high complexity.

[0005] The present invention provides a cold spray equivalent simulation method of an aircraft gas jet, which comprises the following steps:

[0006] Obtain the thermal flow field parameters in the engine combustion chamber and nozzle;

[0007] Based on the thermal flow field parameters in the engine combustion chamber and nozzle, the cold spray nozzle exit conditions are determined according to the cold spray equivalent principle.

[0008] According to the cold spray nozzle outlet conditions and isentropic relationship, the cold spray nozzle profile is adjusted, and the cold spray nozzle inlet parameters are obtained;

[0009] Optimize the nozzle profile to make the jet boundaries of cold spray and hot spray consistent;

[0010] The equivalent simulation of the aircraft gas jet is completed based on the equivalently obtained cold spray nozzle inlet parameters and cold spray nozzle profile.

[0011] Preferably, the thermal flow field parameters in the engine combustion chamber and nozzle are obtained from engine ground tests.

[0012] Preferably, the thermal flow field parameters in the engine combustion chamber and nozzle include the expansion ratio, pressure, temperature, gas density, average molecular weight, Mach number, gas constant R and specific heat ratio γ of the combustion chamber, throat and outlet.

[0013] Preferably, the cold spray equivalence principle is to ensure that the momentum and pressure ratio at the hot spray nozzle outlet and the cold spray nozzle outlet are equal.

[0014] Preferably, the specific method for adjusting the cold spray nozzle profile is: using an isentropic relationship to obtain the ratio of the nozzle outlet to the throat area, and adjusting the nozzle throat area.

[0015] Preferably, the method of optimizing the nozzle profile to make the jet boundaries of cold spray and hot spray consistent is: by changing the nozzle profile, changing the outlet jet boundary, making the jet boundaries of cold spray and hot spray consistent.

[0016] Preferably, the specific method for completing the equivalent simulation of the aircraft gas jet based on the equivalently obtained cold spray nozzle inlet parameters and cold spray nozzle profile is: using computational fluid dynamics methods or wind tunnel test methods to complete the aircraft jet simulation and obtain the aircraft jet aerodynamic interference characteristics.

[0017] A cold spray equivalent simulation device for an aircraft gas jet, characterized in that it comprises:

[0018] An acquisition module is used to obtain the thermal flow field parameters in the engine combustion chamber and nozzle;

[0019] The exit condition determination module determines the cold spray nozzle exit condition based on the thermal flow field parameters in the engine combustion chamber and the nozzle and the cold spray equivalent principle;

[0020] A profile adjustment module adjusts the profile of the cold spray nozzle according to the cold spray nozzle outlet conditions and the isentropic relationship, and obtains the cold spray nozzle inlet parameters;

[0021] Profile optimization module, which optimizes the nozzle profile to make the jet boundaries of cold spray and hot spray consistent;

[0022] The equivalent simulation module completes the equivalent simulation of the aircraft gas jet based on the equivalent cold spray nozzle inlet parameters and cold spray nozzle profile.

[0023] An electronic device comprises: a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the computer program, when executed by the processor, implements the steps of the cold spray equivalent simulation method of the aircraft gas jet as described above.

[0024] A computer-readable storage medium stores an information transmission implementation program, and when the program is executed by a processor, the steps of the cold spray equivalent simulation method of the aircraft gas jet as described above are implemented.

[0025] Beneficial effects:

[0026] The cold spray equivalent simulation method of aircraft gas jets treats the high-temperature gas of aircraft jets as equivalent to air medium. By adjusting the nozzle profile, the outlet conditions of cold spray and hot spray meet the equivalent principle, while also ensuring that the jet boundaries of cold spray and hot spray are consistent. Compared with the hot spray simulation method, there is no need to consider the mixing of different media such as engine gas and air, which greatly reduces the amount of calculation; at the same time, it can be extended to jet simulation tests to simplify test equipment and save test funds. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0028] Figure 1 is a flow chart of the method of the present invention;

[0029] Figure 2 This is the nozzle profile diagram before and after adjustment;

[0030] Figure 3 For different nozzle profiles

[0031] Figure 4 Jet boundaries obtained for different nozzle profiles

[0032] Figure 5 The jet boundary of the hot jet

[0033] Figure 6 Simulate the interference of the gas jet of the aircraft. DETAILED DESCRIPTION

[0034] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0036] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0037] This embodiment provides a cold spray equivalent simulation method of an aircraft gas jet, which includes the following steps:

[0038] Obtain the thermal flow field parameters in the engine combustion chamber and nozzle.

[0039] The thermal flow field parameters in the engine combustion chamber and nozzle are obtained from the engine ground test. The thermal flow field parameters in the engine combustion chamber and nozzle include the expansion ratio, pressure, temperature, gas density, average molecular weight, Mach number, gas constant R and specific heat ratio γ of the combustion chamber, throat and outlet.

[0040] Based on the thermal flow field parameters in the engine combustion chamber and nozzle, the cold spray nozzle exit conditions are determined according to the cold spray equivalent principle. The cold spray equivalent principle is to ensure that the momentum and pressure ratio of the hot spray nozzle exit and the cold spray nozzle exit are equal.

[0041] According to the cold spray nozzle outlet condition and the isentropic relationship, the cold spray nozzle profile is adjusted, and the cold spray nozzle inlet parameters are obtained. In this step, the specific method used is: using the isentropic relationship to obtain the nozzle outlet and throat area ratio, and adjusting the nozzle throat area.

[0042] Optimize the nozzle profile to make the jet boundaries of cold spray and hot spray consistent. In this step, the specific method used is: by changing the nozzle profile, changing the outlet jet boundary, making the jet boundaries of cold spray and hot spray consistent.

[0043] The equivalent simulation of the aircraft gas jet is completed according to the equivalent cold jet nozzle inlet parameters and cold jet nozzle profile. In this step, the specific method used is: using the computational fluid dynamics method or the wind tunnel test method to complete the aircraft jet simulation and obtain the aircraft jet aerodynamic interference characteristics.

[0044] In order to make the above-mentioned purposes, features and advantages of the embodiments of the present invention more obvious and easy to understand, the specific implementation of the present invention is described in detail below in conjunction with the accompanying drawings. The embodiments provided are for explaining the application process of the present invention. The drawings and embodiments of the present invention are only for illustrative purposes and are not intended to limit the scope of protection of the present invention.

[0045] Method Embodiment

[0046] The flow chart of the present invention is as follows Figure 1 As shown, a cold spray equivalent simulation method of an aircraft gas jet is implemented by the following steps:

[0047] Step 1: Obtain the hot flow field parameters in the combustion chamber and nozzle of the jet engine obtained from the engine ground test:

[0048] Table 1 Thermal flow field parameters in the engine combustion chamber and nozzle

[0049]

[0050] Step 2: Ensure that the momentum and pressure ratio of the hot spray nozzle outlet and the cold spray nozzle outlet are equal according to the cold spray equivalent principle. Due to the different specific heat ratios of hot and cold gases, the throat area of ​​the nozzle must be modified for the cold spray state. According to the isentropic relationship, compared with the hot spray (γ = 1.149) case, the throat area of ​​the cold spray (γ = 1.4) equivalent adjustment needs to be increased to 1.69 times, and the cold spray nozzle inlet parameters are obtained. Figure 2 To adjust the front and rear nozzle profiles.

[0051] Step 3: Based on the equivalent nozzle profile obtained by adjusting in step 2, further optimize the nozzle profile to make the cold and hot jet boundaries consistent. Figure 3 For different nozzle profiles. Figure 4 The jet boundaries obtained for different nozzle profiles. Figure 5It is the jet boundary of the hot jet. According to the comparison, the nozzle profile 6 is closest to the hot jet state.

[0052] Step 4: Complete the equivalent simulation of the entire aircraft gas jet based on the equivalently obtained cold spray nozzle inlet parameters and cold spray nozzle profile. Figure 6 Simulation of aerodynamic interference of gas jet of aircraft.

[0053] The contents not described in detail in this embodiment are well known to those skilled in the art.

[0054] Device Example 1

[0055] A cold spray equivalent simulation device for an aircraft gas jet, comprising:

[0056] An acquisition module is used to obtain the thermal flow field parameters in the engine combustion chamber and nozzle;

[0057] The exit condition determination module determines the cold spray nozzle exit condition based on the thermal flow field parameters in the engine combustion chamber and the nozzle and the cold spray equivalent principle;

[0058] A profile adjustment module adjusts the profile of the cold spray nozzle according to the cold spray nozzle outlet conditions and the isentropic relationship, and obtains the cold spray nozzle inlet parameters;

[0059] Profile optimization module, which optimizes the nozzle profile to make the jet boundaries of cold spray and hot spray consistent;

[0060] The equivalent simulation module completes the equivalent simulation of the aircraft gas jet based on the equivalent cold spray nozzle inlet parameters and cold spray nozzle profile.

[0061] Device Example 2

[0062] An electronic device, characterized in that it includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the steps of the cold spray equivalent simulation method of the aircraft gas jet as described above are implemented.

[0063] Device Example 3

[0064] A computer-readable storage medium stores an information transmission implementation program, which, when executed by a processor, implements the steps of the cold spray equivalent simulation method of the aircraft gas jet as described above.

[0065] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can 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 (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0066] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device or system embodiment, since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment. The device and system embodiments described above are merely schematic, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A cold spray equivalent simulation method for aircraft gas jet, characterized in that: The steps include: Obtain the thermal flow field parameters in the engine combustion chamber and nozzle; Based on the thermal flow field parameters in the engine combustion chamber and nozzle, the cold spray nozzle exit conditions are determined according to the cold spray equivalent principle. According to the cold spray nozzle outlet conditions and isentropic relationship, the cold spray nozzle profile is adjusted, and the cold spray nozzle inlet parameters are obtained; Optimize the nozzle profile to make the jet boundaries of cold spray and hot spray consistent; The equivalent simulation of the aircraft gas jet is completed based on the equivalently obtained cold spray nozzle inlet parameters and cold spray nozzle profile.

2. The cold spray equivalent simulation method of aircraft gas jet according to claim 1, characterized in that: The thermal flow field parameters in the engine combustion chamber and nozzle are obtained from the engine ground test.

3. The cold spray equivalent simulation method of aircraft gas jet according to claim 2, characterized in that: The thermal flow field parameters in the engine combustion chamber and nozzle include the expansion ratio, pressure, temperature, gas density, average molecular weight, Mach number, gas constant R and specific heat ratio γ of the combustion chamber, throat and outlet.

4. The cold spray equivalent simulation method of aircraft gas jet according to any one of claims 1 to 3, characterized in that: The cold spray equivalence principle is to ensure that the momentum and pressure ratio at the hot spray nozzle outlet and the cold spray nozzle outlet are equal.

5. The cold spray equivalent simulation method of aircraft gas jet according to claim 4, characterized in that: The specific method for adjusting the cold spray nozzle profile is: using the isentropic relationship to obtain the ratio of the nozzle outlet to the throat area, and adjusting the nozzle throat area.

6. The cold spray equivalent simulation method of aircraft gas jet according to claim 5, characterized in that: The method of optimizing the nozzle profile to make the jet boundaries of the cold spray and the hot spray consistent is: by changing the nozzle profile, changing the outlet jet boundary, making the jet boundaries of the cold spray and the hot spray consistent.

7. The cold spray equivalent simulation method of aircraft gas jet according to claim 6, characterized in that: The specific method for completing the equivalent simulation of the aircraft gas jet based on the equivalently obtained cold spray nozzle inlet parameters and cold spray nozzle profile is: using the computational fluid dynamics method or the wind tunnel test method to complete the aircraft jet simulation and obtain the aircraft jet aerodynamic interference characteristics.

8. A cold spray equivalent simulation device for aircraft gas jet, characterized in that: include: An acquisition module is used to obtain the thermal flow field parameters in the engine combustion chamber and nozzle; The exit condition determination module determines the exit condition of the cold spray nozzle based on the thermal flow field parameters in the engine combustion chamber and the nozzle and the cold spray equivalent principle; A profile adjustment module adjusts the profile of the cold spray nozzle according to the cold spray nozzle outlet conditions and the isentropic relationship, and obtains the cold spray nozzle inlet parameters; Profile optimization module, which optimizes the nozzle profile to make the jet boundaries of cold spray and hot spray consistent; The equivalent simulation module completes the equivalent simulation of the aircraft gas jet based on the equivalent cold spray nozzle inlet parameters and cold spray nozzle profile.

9. An electronic device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the steps of the cold spray equivalent simulation method of the aircraft gas jet as described in any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores an implementation program for information transmission, and when the program is executed by a processor, the steps of the cold spray equivalent simulation method of the aircraft gas jet according to any one of claims 1 to 7 are implemented.

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