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CN115238483A - Optimization design method for liquid fuel injection section of large-scale scramjet - Google Patents

Optimization design method for liquid fuel injection section of large-scale scramjet Download PDF

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CN115238483A
CN115238483A CN202210801944.3A CN202210801944A CN115238483A CN 115238483 A CN115238483 A CN 115238483A CN 202210801944 A CN202210801944 A CN 202210801944A CN 115238483 A CN115238483 A CN 115238483A
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nozzle
liquid fuel
fuel injection
scramjet
scale
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孙明波
周曜智
赵国焱
李凡
马光伟
刘铭江
李岩松
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National University of Defense Technology
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
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Abstract

The invention provides an optimal design method for a liquid fuel injection section of a large-scale scramjet engine, which comprises the steps of obtaining the particle size distribution of different positions at the downstream of a nozzle when the nozzle of the small-scale scramjet engine injects liquid fuel under the condition of supersonic incoming flow; determining an equal-ratio amplification factor n of the combustion chamber of the scaled scramjet engine amplified to the combustion chamber of the large-scale scramjet engine; the optimized diameter of a nozzle of a liquid fuel injection section of the large-scale scramjet engine is
Figure DDA0003738109180000011
So that liquid fuel injection can be realized in a large-scale scramjet engineDownstream of the nozzles of the segment and at a distance from the nozzles
Figure DDA0003738109180000012
The diameter distribution of the position is the same as that of the position, which is downstream of a nozzle of a liquid fuel injection section of the reduced-scale scramjet engine and is away from the nozzle by kd, d is the diameter of the nozzle of the liquid fuel injection section of the reduced-scale scramjet engine, and k is larger than 0. The invention can ensure that the engines have the same atomization characteristic under different nozzle diameters.

Description

大尺度超燃冲压发动机液体燃料喷注段优化设计方法Optimization design method for liquid fuel injection section of large-scale scramjet

技术领域technical field

本发明属于超燃冲压发动机设计技术领域，特别涉及一种大尺度超燃冲压发动机液体燃料喷注段优化设计方法。The invention belongs to the technical field of scramjet engine design, and in particular relates to an optimization design method for a liquid fuel injection section of a large-scale scramjet engine.

背景技术Background technique

超燃冲压发动机主要由进气道、隔离段、燃烧室和尾喷管组成。因为其在高飞行马赫数下的性能优良，被认为是高超声速飞行器的首选推进装置。燃烧室作为超燃冲压发动机流道设计的核心部件，一直是高超声速推进技术领域的研究重点，燃烧室性能直接决定着超燃冲压发动机的总体设计水平。The scramjet is mainly composed of an intake port, an isolation section, a combustion chamber and a tail nozzle. Because of its excellent performance at high flight Mach numbers, it is considered to be the propulsion device of choice for hypersonic vehicles. As the core component of scramjet flow channel design, the combustion chamber has always been the focus of research in the field of hypersonic propulsion. The performance of the combustion chamber directly determines the overall design level of the scramjet.

目前我国在小尺度发动机(喷孔直径较小)的研究上取得了非常多成果，但未来对于大尺寸发动机的设计，如何将现有的在小喷孔直径下所获得的一些规律通过相似准则应用到大尺寸发动机设计上，还是一个急需解决的难题，明晰液体燃料射流雾化特性在不同流向位置上的相似性是必需的，这样可以大大减少大尺寸发动机设计研发周期和费用。At present, my country has made a lot of achievements in the research of small-scale engines (small nozzle diameter), but for the design of large-scale engines in the future, how to pass the existing laws obtained under small nozzle diameters through similarity criteria It is still an urgent problem to be applied to the design of large-scale engines. It is necessary to clarify the similarity of the atomization characteristics of liquid fuel jets in different flow positions, which can greatly reduce the design and development cycle and cost of large-scale engines.

目前，受限于试验面临试验难度大、试验耗时长、试验成本高等难题，大尺度超燃冲压发动机内型面一般直接从缩尺模型等比放大而来，但是基于缩尺模型及简化模型发动机燃烧室总结的结论和规律直接推广到大尺度发动机燃烧室设计，存在以下问题：At present, due to the difficulty of testing, long testing time, and high testing cost, the inner profile of large-scale scramjet is generally directly proportionally enlarged from the scaled model, but based on the scaled model and simplified model engine The conclusions and laws of the combustion chamber summary are directly extended to the design of large-scale engine combustion chambers, and there are the following problems:

(1)发动机尺度等比放大后，液体燃料喷嘴直径无法直接等比增大，现有的在小喷孔直径下所获得的一些规律通过直接应用到大尺寸发动机设计上；(1) After the engine scale is proportionally enlarged, the diameter of the liquid fuel nozzle cannot be directly proportionally increased, and some existing laws obtained under the small nozzle diameter can be directly applied to the design of large-scale engines;

(2)当控制喷注压降不变时，射流穿透深度随喷嘴直径等比放大，但液体射流的雾化特性(如粒径分布)并不是等比放大，无法为喷注方案的设计提供必要参考。(2) When the injection pressure drop is controlled, the penetration depth of the jet is proportionally enlarged with the diameter of the nozzle, but the atomization characteristics (such as particle size distribution) of the liquid jet are not proportionally amplified, which cannot be used for the design of the injection scheme. Provide necessary references.

发明内容SUMMARY OF THE INVENTION

针对现有技术存在的问题，本发明提出了一种大尺度超燃冲压发动机液体燃料喷注段优化设计方法。Aiming at the problems existing in the prior art, the present invention proposes an optimization design method for the liquid fuel injection section of a large-scale scramjet.

为实现上述技术目的，本发明提出的技术方案为：For realizing the above-mentioned technical purpose, the technical scheme proposed by the present invention is:

一方面，本发明提供一种大尺度超燃冲压发动机液体燃料喷注段优化设计方法，包括：On the one hand, the present invention provides a large-scale scramjet liquid fuel injection section optimization design method, comprising:

开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；Carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the particle size distribution of the nozzles in the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. The distance between different downstream positions and the nozzle is kd, where d is the nozzle diameter of the liquid fuel injection section of the scaled scramjet, and k is greater than 0;

确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；Determine the proportional magnification n from the scaled-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000021
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000022
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure BDA0003738109160000021
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000022
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd.

进一步地，可以基于上述方案获得大尺度超燃冲压发动机的点火位置，具体包括：Further, the ignition position of the large-scale scramjet engine can be obtained based on the above solution, which specifically includes:

基于缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，确定适宜点火的粒径分布所在的喷嘴下游位置，设缩尺超燃冲压发动机其适宜点火的粒径分布所在的喷嘴下游位置与喷嘴的距离为k*d，k*大于0；Based on the particle size distribution of the nozzles of the liquid fuel injection section of the scaled scramjet at different positions downstream of the nozzle when liquid fuel is injected, determine the downstream position of the nozzle where the particle size distribution suitable for ignition is located, and set the scaled scramjet. The distance between the downstream position of the nozzle where the particle size distribution suitable for ignition of the engine is located and the nozzle is k * d, and k * is greater than 0;

优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000023
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000024
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为k*d处相同的粒径分布，将大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000025
处设为大尺度超燃冲压发动机的点火位置。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure BDA0003738109160000023
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000024
There is the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the small-scale scramjet and the distance from the nozzle is k * d, and the nozzle of the liquid fuel injection section of the large-scale scramjet is The distance from the nozzle is
Figure BDA0003738109160000025
is set as the ignition position of the large-scale scramjet.

进一步地，本发明提供一种大尺度超燃冲压发动机采用上述任一种大尺度超燃冲压发动机液体燃料喷注段优化设计方法对其液体燃料喷注段进行设计。Further, the present invention provides a large-scale scramjet for designing its liquid fuel injection section by adopting any of the above-mentioned optimization design methods for the liquid fuel injection section of a large-scale scramjet.

进一步地，本发明提供一种大尺度超燃冲压发动机液体燃料喷注段优化设计装置，包括：Further, the present invention provides a large-scale scramjet liquid fuel injection section optimization design device, including:

第一模块，用于开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；The first module is used to carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the nozzles of the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. Particle size distribution, set the distance between different positions downstream of the nozzle and the nozzle as kd, where d is the nozzle diameter of the liquid fuel injection section of the reduced-scale scramjet, and k is greater than 0;

第二模块，用于确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；The second module is used to determine the proportional magnification factor n that is enlarged from the reduced-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

第三模块，用于优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000034
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000035
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The third module is used to optimally set the nozzle diameter of the liquid fuel injection section of the large-scale scramjet to be
Figure BDA0003738109160000034
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000035
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd.

进一步地，所述第一模块中包括基于缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，确定适宜点火的粒径分布所在的喷嘴下游位置，设缩尺超燃冲压发动机其适宜点火的粒径分布所在的喷嘴下游位置与喷嘴的距离为k*d，k*大于0；Further, the first module includes the particle size distribution at different positions downstream of the nozzle when the nozzle of the liquid fuel injection section of the reduced-scale scramjet engine performs liquid fuel injection, and determines where the particle size distribution suitable for ignition is located. The downstream position of the nozzle, the distance between the downstream position of the nozzle where the particle size distribution suitable for ignition of the reduced-scale scramjet is located and the nozzle is k * d, and k * is greater than 0;

所述第三模块中包括优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000031
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000032
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为k*d处相同的粒径分布，将大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000033
处设为大尺度超燃冲压发动机的点火位置。The third module includes optimizing the setting of the nozzle diameter of the liquid fuel injection section of the large-scale scramjet engine:
Figure BDA0003738109160000031
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000032
There is the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the small-scale scramjet and the distance from the nozzle is k * d, and the nozzle of the liquid fuel injection section of the large-scale scramjet is The distance from the nozzle is
Figure BDA0003738109160000033
is set as the ignition position of the large-scale scramjet.

另一方面，本发明提供一种计算机系统，包括存储器和处理器，存储器存储有计算机程序，所述处理器执行所述计算机程序时实现以下步骤：In another aspect, the present invention provides a computer system, comprising a memory and a processor, the memory stores a computer program, and the processor implements the following steps when executing the computer program:

开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；Carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the particle size distribution of the nozzles in the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. The distance between different downstream positions and the nozzle is kd, where d is the nozzle diameter of the liquid fuel injection section of the scaled scramjet, and k is greater than 0;

确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；Determine the proportional magnification n from the scaled-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000041
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000042
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure BDA0003738109160000041
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000042
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd.

另一方面，本发明提供一种计算机可读存储介质，其上存储有计算机程序，所述处理器执行计算机程序时实现以下步骤：On the other hand, the present invention provides a computer-readable storage medium on which a computer program is stored, and the processor implements the following steps when executing the computer program:

开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；Carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the particle size distribution of the nozzles in the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. The distance between different downstream positions and the nozzle is kd, where d is the nozzle diameter of the liquid fuel injection section of the scaled scramjet, and k is greater than 0;

确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；Determine the proportional magnification n from the scaled-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000043
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000044
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure BDA0003738109160000043
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000044
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd.

本发明能够实现的技术效果是：The technical effect that the present invention can realize is:

(1)本发明通过开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，可精确获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布；(1) By carrying out the numerical simulation of the scaled scramjet engine under the condition of supersonic flow, the present invention can accurately obtain the nozzles in the liquid fuel injection section of the scaled scramjet engine that are located at different positions downstream of the nozzle when the liquid fuel is injected. particle size distribution by location;

(2)本发明拓展了喷嘴直径等比放大在穿透深度和展向宽度上的局限性。在超声速来流条件下条件下，冲压发动机由小尺度向大尺度放大过程中，燃烧室液体燃料喷嘴直径由小变大的过程中，通过本发明方法对喷嘴直径进行优化设置，能够保证不同的喷嘴直径下发动机具有相同雾化特性。(2) The present invention expands the limitations of the proportional enlargement of the nozzle diameter on the penetration depth and the spanwise width. Under the condition of supersonic incoming flow, in the process of enlarging the ramjet engine from small scale to large scale, and in the process that the diameter of the liquid fuel nozzle of the combustion chamber changes from small to large, the method of the present invention optimizes the setting of the nozzle diameter, which can ensure that different The engine has the same atomization characteristics at the nozzle diameter.

附图说明Description of drawings

为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图示出的结构获得其他的附图。In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can also be obtained according to the structures shown in these drawings without creative efforts.

图1本发明一实施例的流程图；1 is a flowchart of an embodiment of the present invention;

图2是一仿真实验中获得的不同喷嘴直径下液体射流的穿透深度图；Fig. 2 is the penetration depth diagram of liquid jet under different nozzle diameters obtained in a simulation experiment;

图3是一仿真实验中获得的无量纲的不同喷嘴直径下液体射流穿透深度对比图；Fig. 3 is a dimensionless comparison diagram of the penetration depth of liquid jets under different nozzle diameters obtained in a simulation experiment;

图4是一仿真实验中获得的

Figure BDA0003738109160000053
倍和n倍两种放大准则下不同喷嘴直径的喷嘴在其下游不同位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，其中(a)为基于
Figure BDA0003738109160000054
倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离30d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(b)为基于n倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离30d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(c)为基于
Figure BDA0003738109160000051
倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离45d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(d)为基于n倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离45d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(e)为基于
Figure BDA0003738109160000052
倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离60d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(f)为基于n倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离60d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图；Figure 4 is obtained in a simulation experiment
Figure BDA0003738109160000053
Comparison of the particle size distribution of the average particle size along the longitudinal height on the jet center symmetry plane for nozzles with different nozzle diameters at different downstream positions under the two magnification criteria of times and n times, where (a) is based on
Figure BDA0003738109160000054
Comparison of the particle size distributions of the average particle size along the longitudinal height on the jet center symmetry plane at the downstream of the nozzle with different nozzle diameters and at a distance of 30d from the nozzle under the magnification criterion, (b) is based on the n times magnification criterion for different nozzles Comparison of the particle size distribution of the average particle size along the longitudinal height on the symmetrical plane of the jet center at the downstream of the nozzle with a diameter of 30d and a distance from the nozzle, (c) is based on
Figure BDA0003738109160000051
Comparison of the particle size distributions of the average particle size along the longitudinal height on the jet center symmetry plane at the downstream of the nozzle with different nozzle diameters and at a distance of 45d from the nozzle under the double magnification criterion, (d) is based on the n times magnification criterion for different nozzles Comparison of the particle size distribution of the average particle size along the longitudinal height on the symmetrical plane of the jet center at the downstream of the nozzle with a distance of 45d from the nozzle, (e) is based on
Figure BDA0003738109160000052
Comparison of the particle size distributions of the average particle size along the longitudinal height on the jet center symmetry plane at the downstream of the nozzle with different nozzle diameters and at a distance of 60d from the nozzle under the magnification criterion, (f) is based on the n times magnification criterion for different nozzles Comparison of the particle size distribution of the average particle size along the longitudinal height on the symmetrical plane of the jet center at the downstream of the nozzle with a diameter of 60d from the nozzle;

图5为本发明一实施例的结构示意图。FIG. 5 is a schematic structural diagram of an embodiment of the present invention.

具体实施方式Detailed ways

为使本发明实施例的目的、技术方案和优点更加清楚明白，下面将以附图及详细叙述来清楚说明本发明所揭示内容的精神，任何所属技术领域技术人员在了解本发明内容的实施例后，当可由本发明内容所教示的技术，加以改变及修饰，其并不脱离本发明内容的精神与范围。本发明的示意性实施例及其说明用于解释本发明，但并不作为对本发明的限定。In order to make the purposes, technical solutions and advantages of the embodiments of the present invention more clearly understood, the following will clearly illustrate the spirit of the disclosed contents of the present invention with the accompanying drawings and detailed description. Afterwards, changes and modifications can be made by the technology taught by the content of the present invention, without departing from the spirit and scope of the content of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention, but are not intended to limit the present invention.

目前已有研究获得了改变喷嘴直径的大小对液体射流穿透深度的影响规律。在试验工况设计中，喷嘴直径是一个主要的变量。液气动量通量比通过公式(1.1)计算得到，其中Δp为喷注压降，p0为气流总压，液相和气相动量通量之比转化为与喷前压力相关的表达式，即通过控制喷前压力调节液气动量通量比，在保持液气动量比一致的条件下，研究喷孔直径的影响。At present, some studies have obtained the effect of changing the diameter of the nozzle on the penetration depth of the liquid jet. In the design of test conditions, nozzle diameter is a major variable. The hydrodynamic momentum flux ratio is calculated by formula (1.1), where Δp is the injection pressure drop, p0 is the total airflow pressure, and the ratio of the liquid phase and gas phase momentum fluxes is converted into an expression related to the pre-injection pressure, namely By controlling the pre-spray pressure to adjust the hydraulic-pneumatic flow ratio, the influence of the nozzle diameter was studied under the condition of keeping the same hydraulic-pneumatic flow ratio.

Figure BDA0003738109160000061
Figure BDA0003738109160000061

图2给出了一仿真实验中获得的不同喷嘴直径下液体射流的穿透深度图，在气流马赫数2.0条件下，对不同喷嘴直径(喷嘴直径d＝0.5mm、d＝0.7mm以及d＝1.0mm)下水射流的喷注穿透深度进行比较。数据点均为PDA测得的射流的边界点，虚线为采用幂函数形式拟合得到的射流穿透深度曲线，横纵坐标对应了距离喷孔中心的实际距离。由图2可以发现，随着喷孔直径的增大，射流的穿透深度显著增大，由于射流的液气动量通量比保持不变，因此穿透深度的增长完全是由于喷孔直径增加造成的。Figure 2 shows the penetration depth diagram of the liquid jet under different nozzle diameters obtained in a simulation experiment. Under the condition of airflow Mach number 2.0, for different nozzle diameters (nozzle diameter d=0.5mm, d=0.7mm and d= The injection penetration depth of the water jet under 1.0 mm) was compared. The data points are the boundary points of the jet measured by PDA, the dotted line is the jet penetration depth curve fitted by the power function, and the abscissa and ordinate correspond to the actual distance from the center of the orifice. It can be found from Figure 2 that with the increase of the diameter of the orifice, the penetration depth of the jet increases significantly. Since the hydro-pneumatic flux ratio of the jet remains unchanged, the increase in the penetration depth is entirely due to the increase in the diameter of the orifice. Caused.

图3给出了一仿真实验中获得的无量纲的不同喷嘴直径下(喷嘴直径d＝0.5mm、d＝0.7mm以及d＝1.0mm)液体射流穿透深度对比图，穿透深度和距离喷孔的距离均采用喷嘴直径进行无量纲化，图3中的横纵坐标采用对数形式进行表示。可以看出，无量纲化之后的穿透深度曲线几乎一致，穿透深度和喷孔直径是等比增大的。计算得到最大相对差为2.88％，可以认为穿透深度随着喷孔尺寸的等比放大而近似成比例增大。Figure 3 shows a comparison chart of the penetration depth of liquid jet under different nozzle diameters (nozzle diameter d=0.5mm, d=0.7mm and d=1.0mm) obtained in a simulation experiment, penetration depth and distance jet The distance of the holes is dimensionless using the nozzle diameter, and the abscissa and ordinate in Fig. 3 are expressed in logarithmic form. It can be seen that the penetration depth curves after dimensionless are almost the same, and the penetration depth and the diameter of the nozzle increase in equal proportions. The maximum relative difference is calculated to be 2.88%, and it can be considered that the penetration depth increases approximately proportionally with the proportional enlargement of the orifice size.

如图4所示，一仿真实验中，

Figure BDA0003738109160000071
倍和n倍两种放大准则下不同喷嘴直径(喷嘴直径d＝0.5mm、d＝0.7mm以及d＝1.0mm)的喷嘴在其下游不同位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，其中(a)为基于
Figure BDA0003738109160000072
倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离30d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(b)为基于n倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离30d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(c)为基于
Figure BDA0003738109160000076
倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离45d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(d)为基于n倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离45d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图；(e)为基于
Figure BDA0003738109160000077
倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离60d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图，(f)为基于n倍放大准则下不同喷嘴直径的喷嘴在其下游且与喷嘴距离60d位置处的射流中心对称面上平均粒径沿纵向高度的粒径分布对比图。从三种不同位置的对比中可以看到在近壁面低速区，两种放大原则下，粒径分布均相差较大，而在靠近射流边界的高速区域可以看到在两种放大准则下粒径分布均能较好吻合。当以
Figure BDA0003738109160000073
去选取流向位置时，不同孔径射流测量得到的粒径分布相较于等比位置分布更为一致，说明对于不同孔径射流当以
Figure BDA0003738109160000074
作为流向特征长度对射流的流向距离做无量纲化时，在相同无量纲位置上流过该截面的粒子分布具有一定的分布相似性，由此也可以推测，射流的雾化完成距离近似正比于
Figure BDA0003738109160000075
As shown in Figure 4, in a simulation experiment,
Figure BDA0003738109160000071
The average particle size along the longitudinal height of the nozzles with different nozzle diameters (nozzle diameters d=0.5mm, d=0.7mm and d=1.0mm) on the symmetrical plane of the jet center at different downstream positions under the two magnification criteria of times and n times The particle size distribution comparison diagram of , where (a) is based on
Figure BDA0003738109160000072
Comparison of the particle size distributions of the average particle size along the longitudinal height on the jet center symmetry plane at the downstream of the nozzle with different nozzle diameters and at a distance of 30d from the nozzle under the magnification criterion, (b) is based on the n times magnification criterion for different nozzles Comparison of the particle size distribution of the average particle size along the longitudinal height on the symmetrical plane of the jet center at the downstream of the nozzle with a diameter of 30d and a distance from the nozzle, (c) is based on
Figure BDA0003738109160000076
Comparison of the particle size distributions of the average particle size along the longitudinal height on the jet center symmetry plane at the downstream of the nozzle with different nozzle diameters and at a distance of 45d from the nozzle under the double magnification criterion, (d) is based on the n times magnification criterion for different nozzles Comparison of the particle size distribution of the average particle diameter along the longitudinal height on the symmetrical plane of the jet center at the downstream of the nozzle with a distance of 45d from the nozzle; (e) is based on
Figure BDA0003738109160000077
Comparison of the particle size distributions of the average particle size along the longitudinal height on the jet center symmetry plane at the downstream of the nozzle with different nozzle diameters and at a distance of 60d from the nozzle under the magnification criterion, (f) is based on the n times magnification criterion for different nozzles Comparison of the particle size distribution of the average particle size along the longitudinal height on the symmetrical plane of the jet center at a position downstream of the nozzle with a diameter of 60d and a distance from the nozzle. From the comparison of the three different positions, it can be seen that in the low-velocity region near the wall, the particle size distribution is quite different under the two amplification principles, while in the high-speed region near the jet boundary, it can be seen that the particle size distribution under the two amplification principles The distributions are in good agreement. when
Figure BDA0003738109160000073
When the flow direction position is selected, the particle size distribution measured by jets with different apertures is more consistent than the distribution at the equal ratio position, indicating that for jets with different apertures, the
Figure BDA0003738109160000074
When the flow direction distance of the jet is dimensionless as the flow direction characteristic length, the distribution of particles flowing through the section at the same dimensionless position has a certain distribution similarity. It can also be inferred that the atomization completion distance of the jet is approximately proportional to
Figure BDA0003738109160000075

基于上述分析，参照图1，一实施例提供一种大尺度超燃冲压发动机液体燃料喷注段优化设计方法，包括：Based on the above analysis, referring to FIG. 1 , an embodiment provides a method for optimizing the design of a liquid fuel injection section of a large-scale scramjet, including:

S1开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布；S1 carries out the numerical simulation of the reduced-scale scramjet under the condition of supersonic incoming flow, and obtains the particle size distribution of the nozzle of the liquid fuel injection section of the reduced-scale scramjet at different positions downstream of the nozzle when the liquid fuel is injected;

具体地，S1中设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；Specifically, in S1, the distance between different positions downstream of the nozzle and the nozzle is set as kd, where d is the nozzle diameter of the liquid fuel injection section of the reduced-scale scramjet, and k is greater than 0;

S2确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；S2 determines the proportional magnification n from the reduced-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

S3优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径；S3 optimizes the setting of the nozzle diameter of the liquid fuel injection section of the large-scale scramjet;

具体地，S3中优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000081
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000082
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。Specifically, in S3, the nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure BDA0003738109160000081
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000082
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd.

一实施例中，提供一种可以基于上述大尺度超燃冲压发动机液体燃料喷注段优化设计方法，获得大尺度超燃冲压发动机的点火位置，具体包括：In one embodiment, a method for optimizing the design of the liquid fuel injection section of the large-scale scramjet engine is provided to obtain the ignition position of the large-scale scramjet engine, specifically including:

基于缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，确定适宜点火的粒径分布所在的喷嘴下游位置，设缩尺超燃冲压发动机其适宜点火的粒径分布所在的喷嘴下游位置与喷嘴的距离为k*d，k*大于0；Based on the particle size distribution of the nozzles of the liquid fuel injection section of the scaled scramjet at different positions downstream of the nozzle when liquid fuel is injected, determine the downstream position of the nozzle where the particle size distribution suitable for ignition is located, and set the scaled scramjet. The distance between the downstream position of the nozzle where the particle size distribution suitable for ignition of the engine is located and the nozzle is k * d, and k * is greater than 0;

确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；Determine the proportional magnification n from the scaled-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000085
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000083
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为k*d处相同的粒径分布，将大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000084
处设为大尺度超燃冲压发动机的点火位置。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure BDA0003738109160000085
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000083
There is the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the small-scale scramjet and the distance from the nozzle is k * d, and the nozzle of the liquid fuel injection section of the large-scale scramjet is The distance from the nozzle is
Figure BDA0003738109160000084
is set as the ignition position of the large-scale scramjet.

一实施例中，k*＝45。本发明已经经过实验计算验证，方案可行，结果达到预期目标。In one embodiment, k * =45. The present invention has been verified by experimental calculation, the scheme is feasible, and the result achieves the expected goal.

一实施例中，提供一种大尺度超燃冲压发动机，采用上述任一实施例中提供的大尺度超燃冲压发动机液体燃料喷注段优化设计方法对其液体燃料喷注段进行设计。In one embodiment, a large-scale scramjet is provided, and the liquid fuel injection section of the large-scale scramjet is designed by using the optimization design method for the liquid fuel injection section of the large-scale scramjet provided in any of the above embodiments.

一实施例中，提供一种大尺度超燃冲压发动机，基于上述大尺度超燃冲压发动机液体燃料喷注段优化设计方法，获得大尺度超燃冲压发动机的点火位置。In one embodiment, a large-scale scramjet engine is provided, and the ignition position of the large-scale scramjet engine is obtained based on the above-mentioned optimization design method for the liquid fuel injection section of the large-scale scramjet engine.

大尺度超燃冲压发动机液体燃料喷注段优化设计方法与上述实施例中相同，各步骤在前面实施例中已经详细叙述清楚，在此不再赘述。同样的，如何获得大尺度超燃冲压发动机的点火位置与上述实施例中相同，各步骤在前面实施例中已经详细叙述清楚，在此不再赘述。The method for optimizing the design of the liquid fuel injection section of the large-scale scramjet is the same as that in the above-mentioned embodiment. Each step has been described in detail in the previous embodiment, and will not be repeated here. Similarly, how to obtain the ignition position of the large-scale scramjet is the same as that in the above-mentioned embodiment, and each step has been described in detail in the previous embodiment, and will not be repeated here.

一实施例中，一种大尺度超燃冲压发动机液体燃料喷注段优化设计装置，其特征在于，包括：In one embodiment, a large-scale scramjet liquid fuel injection section optimization design device is characterized in that, comprising:

第一模块，用于开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；The first module is used to carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the nozzles of the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. Particle size distribution, set the distance between different positions downstream of the nozzle and the nozzle as kd, where d is the nozzle diameter of the liquid fuel injection section of the reduced-scale scramjet, and k is greater than 0;

第二模块，用于确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；The second module is used to determine the proportional magnification factor n that is enlarged from the reduced-scale scramjet combustion chamber to the large-scale scramjet combustion chamber;

第三模块，用于优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为

Figure BDA0003738109160000091
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure BDA0003738109160000092
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The third module is used to optimally set the nozzle diameter of the liquid fuel injection section of the large-scale scramjet to be
Figure BDA0003738109160000091
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure BDA0003738109160000092
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd.

上述各模块功能的实现方法，可以采用前述各实施例中相同的方法实现，在此不再赘述。The methods for implementing the functions of the above modules can be implemented by the same methods as those in the foregoing embodiments, and details are not described herein again.

在本实施例中，提供了一种计算机设备，该计算机设备可以是服务器，其内部结构图可以如图5所示。该计算机设备包括通过系统总线连接的处理器、存储器、网络接口和数据库。其中，该计算机设备的处理器用于提供计算和控制能力。该计算机设备的存储器包括非易失性存储介质、内存储器。该非易失性存储介质存储有操作系统、计算机程序和数据库。该内存储器为非易失性存储介质中的操作系统和计算机程序的运行提供环境。该计算机设备的数据库用于存储样本数据。该计算机设备的网络接口用于与外部的终端通过网络连接通信。该计算机程序被处理器执行时以实现上述实施例中大尺度超燃冲压发动机液体燃料喷注段优化设计方法的步骤。In this embodiment, a computer device is provided, the computer device may be a server, and its internal structure diagram may be as shown in FIG. 5 . The computer device includes a processor, memory, a network interface, and a database connected by a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium, an internal memory. The nonvolatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the execution of the operating system and computer programs in the non-volatile storage medium. The computer device's database is used to store sample data. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, the steps of the method for optimizing the design of the liquid fuel injection section of the large-scale scramjet engine in the above-mentioned embodiments are realized.

本领域技术人员可以理解，图5中示出的结构，仅仅是与本申请方案相关的部分结构的框图，并不构成对本申请方案所应用于其上的计算机设备的限定，具体的计算机设备可以包括比图中所示更多或更少的部件，或者组合某些部件，或者具有不同的部件布置。Those skilled in the art can understand that the structure shown in FIG. 5 is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer equipment to which the solution of the present application is applied. Include more or fewer components than shown in the figures, or combine certain components, or have a different arrangement of components.

在一个实施例中，提供了一种计算机设备，包括存储器和处理器，该存储器存储有计算机程序，该处理器执行计算机程序时实现上述实施例中大尺度超燃冲压发动机液体燃料喷注段优化设计方法的步骤。In one embodiment, a computer device is provided, including a memory and a processor, the memory stores a computer program, and the processor implements the optimization of the liquid fuel injection section of the large-scale scramjet in the above embodiment when the processor executes the computer program Design method steps.

在一个实施例中，提供了一种计算机可读存储介质，其上存储有计算机程序，计算机程序被处理器执行时实现上述实施例中大尺度超燃冲压发动机液体燃料喷注段优化设计方法的步骤。In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, realizes the optimization design method of the liquid fuel injection section of the large-scale scramjet in the above-mentioned embodiment. step.

本领域普通技术人员可以理解实现上述实施例方法中的全部或部分流程，是可以通过计算机程序来指令相关的硬件来完成，所述的计算机程序可存储于一非易失性计算机可读取存储介质中，该计算机程序在执行时，可包括如上述各方法的实施例的流程。其中，本申请所提供的各实施例中所使用的对存储器、存储、数据库或其它介质的任何引用，均可包括非易失性和/或易失性存储器。非易失性存储器可包括只读存储器(ROM)、可编程ROM(PROM)、电可编程ROM(EPROM)、电可擦除可编程ROM(EEPROM)或闪存。易失性存储器可包括随机存取存储器(RAM)或者外部高速缓冲存储器。作为说明而非局限，RAM以多种形式可得，诸如静态RAM(SRAM)、动态RAM(DRAM)、同步DRAM(SDRAM)、双数据率SDRAM(DDRSDRAM)、增强型SDRAM(ESDRAM)、同步链路(Synchlink)DRAM(SLDRAM)、存储器总线(Rambus)直接RAM(RDRAM)、直接存储器总线动态RAM(DRDRAM)、以及存储器总线动态RAM(RDRAM)等。Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be implemented by instructing relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage In the medium, when the computer program is executed, it may include the processes of the above-mentioned method embodiments. Wherein, any reference to memory, storage, database or other medium used in the various embodiments provided in this application may include non-volatile and/or volatile memory. Nonvolatile 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. By way of illustration and not limitation, RAM is available in various forms such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous chain Road (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

以上实施例的各技术特征可以进行任意的组合，为使描述简洁，未对上述实施例中的各个技术特征所有可能的组合都进行描述，然而，只要这些技术特征的组合不存在矛盾，都应当认为是本说明书记载的范围。The technical features of the above embodiments can be combined arbitrarily. In order to make the description simple, all possible combinations of the technical features in the above embodiments are not described. However, as long as there is no contradiction in the combination of these technical features It is considered to be the range described in this specification.

以上所述实施例仅表达了本申请的几种实施方式，其描述较为具体和详细，但并不能因此而理解为对发明专利范围的限制。应当指出的是，对于本领域的普通技术人员来说，在不脱离本申请构思的前提下，还可以做出若干变形和改进，这些都属于本申请的保护范围。因此，本申请专利的保护范围应以所附权利要求为准。The above-mentioned embodiments only represent several embodiments of the present application, and the descriptions thereof are relatively specific and detailed, but should not be construed as a limitation on the scope of the invention patent. It should be pointed out that for those skilled in the art, without departing from the concept of the present application, several modifications and improvements can be made, which all belong to the protection scope of the present application. Therefore, the scope of protection of the patent of the present application shall be subject to the appended claims.

Claims (8)

1.大尺度超燃冲压发动机液体燃料喷注段优化设计方法，其特征在于，包括：1. a large-scale scramjet liquid fuel injection section optimization design method, is characterized in that, comprises: 开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；Carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the particle size distribution of the nozzles in the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. The distance between different downstream positions and the nozzle is kd, where d is the nozzle diameter of the liquid fuel injection section of the scaled scramjet, and k is greater than 0; 确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；Determine the proportional magnification n from the scaled-scale scramjet combustion chamber to the large-scale scramjet combustion chamber; 优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为
Figure FDA0003738109150000011
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure FDA0003738109150000012
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure FDA0003738109150000011
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure FDA0003738109150000012
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd. 2.根据权利要求1所述的大尺度超燃冲压发动机液体燃料喷注段优化设计方法，其特征在于，基于缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，确定适宜点火的粒径分布所在的喷嘴下游位置，设缩尺超燃冲压发动机其适宜点火的粒径分布所在的喷嘴下游位置与喷嘴的距离为k*d，k*大于0；2. the large-scale scramjet liquid fuel injection section optimization design method according to claim 1, is characterized in that, when the nozzle of its liquid fuel injection section of the reduced-scale scramjet carries out liquid fuel injection, it is located at The particle size distribution at different positions downstream of the nozzle, determine the downstream position of the nozzle where the particle size distribution suitable for ignition is located, and set the distance between the downstream position of the nozzle where the particle size distribution suitable for ignition of the reduced-scale scramjet is located and the nozzle is k * d, k * greater than 0; 优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为
Figure FDA0003738109150000013
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure FDA0003738109150000014
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为k*d处相同的粒径分布，将大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure FDA0003738109150000015
处设为大尺度超燃冲压发动机的点火位置。The nozzle diameter of the liquid fuel injection section of the large-scale scramjet is optimized to be
Figure FDA0003738109150000013
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure FDA0003738109150000014
There is the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the small-scale scramjet and the distance from the nozzle is k * d, and the nozzle of the liquid fuel injection section of the large-scale scramjet is The distance from the nozzle is
Figure FDA0003738109150000015
is set as the ignition position of the large-scale scramjet. 3.根据权利要求2所述的大尺度超燃冲压发动机液体燃料喷注段优化设计方法，其特征在于，k*＝45。3 . The method for optimizing the design of the liquid fuel injection section of a large-scale scramjet according to claim 2 , wherein k * =45. 4 . 4.一种大尺度超燃冲压发动机，其特征在于，采用如权利要求1或2或3所述的大尺度超燃冲压发动机液体燃料喷注段优化设计方法对其液体燃料喷注段进行设计。4. A large-scale scramjet, characterized in that the liquid fuel injection section of a large-scale scramjet is designed using the method for optimizing the design of the liquid fuel injection section of a large-scale scramjet as claimed in claim 1 or 2 or 3. . 5.一种大尺度超燃冲压发动机液体燃料喷注段优化设计装置，其特征在于，包括：5. A large-scale scramjet liquid fuel injection section optimization design device is characterized in that, comprising: 第一模块，用于开展在超声速来流条件下的缩尺超燃冲压发动机数值仿真，获取缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，设喷嘴下游不同位置与喷嘴的距离为kd，其中d为缩尺超燃冲压发动机其液体燃料喷注段的喷嘴直径，k大于0；The first module is used to carry out the numerical simulation of the reduced-scale scramjet engine under the condition of supersonic incoming flow, and obtain the nozzles of the liquid fuel injection section of the reduced-scale scramjet engine at different positions downstream of the nozzle when the liquid fuel is injected. Particle size distribution, set the distance between different positions downstream of the nozzle and the nozzle as kd, where d is the nozzle diameter of the liquid fuel injection section of the reduced-scale scramjet, and k is greater than 0; 第二模块，用于确定由缩尺超燃冲压发动机燃烧室放大到大尺度超燃冲压发动机燃烧室的等比放大倍数n；The second module is used to determine the proportional magnification factor n that is enlarged from the reduced-scale scramjet combustion chamber to the large-scale scramjet combustion chamber; 第三模块，用于优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为
Figure FDA0003738109150000021
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure FDA0003738109150000022
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为kd处相同的粒径分布。The third module is used to optimally set the nozzle diameter of the liquid fuel injection section of the large-scale scramjet to be
Figure FDA0003738109150000021
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure FDA0003738109150000022
It has the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the scaled scramjet and the distance from the nozzle is kd. 6.根据权利要求5所述的大尺度超燃冲压发动机液体燃料喷注段优化设计装置，其特征在于，所述第一模块中包括基于缩尺超燃冲压发动机其液体燃料喷注段的喷嘴进行液体燃料喷注时位于喷嘴下游不同位置的粒径分布，确定适宜点火的粒径分布所在的喷嘴下游位置，设缩尺超燃冲压发动机其适宜点火的粒径分布所在的喷嘴下游位置与喷嘴的距离为k*d，k*大于0；6. The large-scale scramjet liquid fuel injection section optimization design device according to claim 5, wherein the first module includes a nozzle based on the liquid fuel injection section of the scaled scramjet engine The particle size distribution at different positions downstream of the nozzle during liquid fuel injection, determine the downstream position of the nozzle where the particle size distribution suitable for ignition is located, and set the downstream position of the nozzle where the particle size distribution suitable for ignition is located in the reduced-scale scramjet engine and the nozzle. The distance is k * d, and k * is greater than 0; 所述第三模块中包括优化设置大尺度超燃冲压发动机其液体燃料喷注段的喷嘴直径为
Figure FDA0003738109150000023
使得在大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure FDA0003738109150000024
处具有与缩尺超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为k*d处相同的粒径分布，将大尺度超燃冲压发动机其液体燃料喷注段的喷嘴下游且与喷嘴距离为
Figure FDA0003738109150000025
处设为大尺度超燃冲压发动机的点火位置。The third module includes optimizing the setting of the nozzle diameter of the liquid fuel injection section of the large-scale scramjet engine:
Figure FDA0003738109150000023
Make the nozzle downstream of the liquid fuel injection section of the large-scale scramjet and the distance from the nozzle is
Figure FDA0003738109150000024
There is the same particle size distribution as the nozzle downstream of the liquid fuel injection section of the small-scale scramjet and the distance from the nozzle is k * d, and the nozzle of the liquid fuel injection section of the large-scale scramjet is The distance from the nozzle is
Figure FDA0003738109150000025
is set as the ignition position of the large-scale scramjet. 7.一种计算机系统，包括存储器和处理器，存储器存储有计算机程序，其特征在于，处理器执行所述计算机程序时实现如权利要求1或2或3所述的大尺度超燃冲压发动机液体燃料喷注段优化设计方法的步骤。7. A computer system comprising a memory and a processor, wherein the memory stores a computer program, wherein the processor implements the large-scale scramjet liquid as claimed in claim 1 or 2 or 3 when the processor executes the computer program Steps of a fuel injection section optimization design method. 8.一种计算机可读存储介质，其上存储有计算机程序，其特征在于：处理器执行计算机程序时实现如权利要求1或2或3所述的大尺度超燃冲压发动机液体燃料喷注段优化设计方法的步骤。8. A computer-readable storage medium having a computer program stored thereon, characterized in that: when the processor executes the computer program, the large-scale scramjet liquid fuel injection section as claimed in claim 1 or 2 or 3 is realized Steps to optimize the design method.
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