A method for loading solid particles in a two-phase jet of a solid-liquid bundled rocket
By dividing the nozzle throat into multiple small regions and calculating the particle phase loading parameters, the complexity of particle phase loading in solid-liquid bonded rockets is solved, accurate particle phase loading is achieved, the particle phase loading state is simplified, and input is provided for two-phase flow simulation analysis.
Patent Information
- Application Number
- CN202211255839.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-10-13
- Publication Date
- 2026-01-02
- Estimated Expiration
- 2042-10-13
AI Technical Summary
Existing solid-liquid jet simulation technologies have failed to effectively simulate and resolve the two-phase flow field distribution in solid-liquid bundled rockets, and cannot achieve particle phase loading. The technical problems caused by the inability to achieve particle phase loading are: the inability to achieve particle phase loading, the inability to achieve particle phase loading, the inability to achieve particle phase loading, the inability to achieve particle phase loading, and the inability of existing technologies to resolve the issues of sorting out and simplifying the particle phase loading state.
The nozzle throat is divided into multiple small regions as particulate phase inlets. The particulate phase loading parameters of each small region are determined, including the molar mass of the particulate phase, average diameter, diameter distribution, temperature and velocity. The precise loading of the particulate phase is achieved by calculation using formulas.
By loading the granular phase, particle loading was achieved, particle loading was achieved, particle loading was achieved, particle loading was achieved, particle loading was achieved, particle loading was achieved, particle loading was achieved, the loading state of the granular phase was sorted out and simplified, and input was provided for two-phase flow simulation analysis.
Smart Images
Figure CN115585077B_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application belongs to the field of carrier rockets, and relates to a method for loading a particle phase of a two-phase jet of a solid-liquid bundled rocket. BACKGROUND
[0002] In a solid-liquid bundled rocket, a large amount of solid particles in a solid boost engine affect the flow field distribution of the airflow at the bottom of the rocket, cause exhaust cross effects and additional interference between the flames of the boost and main engines, and intensify the interaction between the plume of the solid engine and the plume of the liquid core stage.
[0003] The combustion process of the particle phase of the solid boost engine in the combustion chamber is complex, and the diameter distribution, flow distribution, velocity and temperature distribution of the particle phase are all complex. SUMMARY
[0004] The present application solves the technical problem of overcoming the deficiencies of the prior art and providing a method for loading a particle phase of a two-phase jet of a solid-liquid bundled rocket.
[0005] The technical solution of the present application is as follows:
[0006] A method for loading a particle phase of a two-phase jet of a solid-liquid bundled rocket, comprising:
[0007] The throat of the nozzle is taken as the particle inlet, and the throat is divided into a plurality of small regions as the particle phase inlet.
[0008] The particle phase loading parameters of each small region are determined to realize the particle phase loading of each small region, and finally realize the particle phase loading of the entire nozzle throat.
[0009] In the above method for loading a particle phase of a two-phase jet of a solid-liquid bundled rocket, the throat of the nozzle is a circular through hole or an elliptical through hole.
[0010] The center of the throat is a circular small region, and a plurality of annular small regions are divided outward from the center along the radial direction.
[0011] In the above method for loading a particle phase of a two-phase jet of a solid-liquid bundled rocket, the radius of the circular small region and the width of each annular small region are the same.
[0012] In the aforementioned method for loading the particle phase of a two-phase jet in a solid-liquid bound rocket, the particle phase loading parameters include the particle phase molar mass C. mr Average diameter of the particle phase d mr The distribution law of average diameter of particle phase, particle phase temperature, and particle phase velocity c.
[0013] In the above-mentioned solid-liquid bonded rocket two-phase jet particle phase loading method, the method for determining the molar mass of the particle phase is as follows:
[0014] Molar mass of the particulate phase C mr The flow rate is linearly distributed radially outward from the small circular regions; the flow rate is highest at the throat axis and gradually decreases radially outward; the particle molar mass C of each small region... mr Load according to the actual engine flow data.
[0015] In the aforementioned method for loading particle phases into a two-phase jet of a solid-liquid bound rocket, the average diameter d of the particle phase is... mr The method for determining it is as follows:
[0016] d mr =1.38D 0.2932 (1-exp(-0.833×10 -8 C mr P m τ))
[0017] In the formula, D is the diameter of the nozzle throat;
[0018] C mr It is the molar mass of the particles in that small region;
[0019] P m It is the pressure in the engine's combustion chamber;
[0020] τ is the residence time of the particle.
[0021] In the above-mentioned solid-liquid bonded rocket two-phase jet particle phase loading method, the particle residence time τ is calculated as follows:
[0022] τ=ρ c V c / S m
[0023] In the formula, ρ c The density of the gas;
[0024] V c This refers to the volume of the combustion chamber;
[0025] S m This represents the gas mass flow rate.
[0026] In the solid-liquid bundled rocket two-phase jet particle phase loading method, the method for determining the average diameter distribution of the particle phase is:
[0027] The particle phase diameter loaded at the throat is based on the average diameter of the normal distribution, which is expressed as:
[0028]
[0029] In the formula, d is the particle size of the reference particle;
[0030] Y dr The mass fraction of the particle larger than the reference particle size d;
[0031] d mr The average particle size;
[0032] n is the propagation coefficient.
[0033] In the solid-liquid bundled rocket two-phase jet particle phase loading method, the method for determining the temperature of the particle phase is:
[0034] The particle phase temperature is the melting point temperature of the particle.
[0035] In the solid-liquid bundled rocket two-phase jet particle phase loading method, the particle phase velocity c is the speed of sound of the engine temperature, specifically:
[0036]
[0037] In the formula, k is the gas specific heat ratio of the engine jet;
[0038] R is the gas constant of the engine jet;
[0039] T is the temperature of the engine jet.
[0040] The beneficial effects of the present application compared with the prior art are:
[0041] (1) The present application innovatively provides a partitioning method from a central circular small area to an annular small area, accurately simulates the two-phase jet in the solid-liquid bundled rocket, and accurately divides the loading area of the particle phase according to the actual situation;
[0042] (2) The present application designs the molar mass, diameter, flow distribution, velocity and temperature distribution of the particle phase, considers the complex combustion process of the particle phase of the full solid booster engine in the combustion chamber, and numerous influencing factors, and the loading result is accurate;
[0043] (3) The present application sorts out and simplifies the particle phase loading state of each small area, and provides input for two-phase flow simulation analysis. BRIEF DESCRIPTION OF DRAWINGS
[0044] Figure 1 Flow chart for loading particle phase of the present application;
[0045] Figure 2 Schematic diagram for dividing throat into multiple small areas of the present application. DETAILED DESCRIPTION
[0046] The present application is further described below in conjunction with examples.
[0047] The present application provides a method for loading particle phase of solid-liquid bundled rocket two-phase jet flow. The combustion process of particle phase of solid boost engine in combustion chamber is complex, and there are many influencing factors. The diameter distribution, flow distribution, velocity and temperature distribution of particle phase are all complex. The present application provides a method for loading particle phase of solid-liquid bundled rocket two-phase jet flow, which clearly defines the loading method of particle phase, sorts and simplifies the loading state of particle phase, and provides input for two-phase flow simulation analysis.
[0048] The method for loading particle phase of solid-liquid bundled rocket two-phase jet flow, as shown in Figure 1 , specifically includes the following steps:
[0049] Step one, taking the throat of the nozzle as the particle inlet, and dividing the throat into multiple small areas as the particle phase inlet; the method for dividing into multiple small areas is that: the throat of the nozzle is a circular through hole or an elliptical through hole; the center of the throat is a circular small area; multiple annular small areas are divided from the center along the radial direction outward. The radius of the circular small area and the width of each annular small area are the same.
[0050] Step two, determining the particle phase loading parameters of each small area to realize the particle phase loading of each small area; and finally realizing the particle phase loading of the entire nozzle throat.
[0051] The particle phase loading parameters include particle phase molar mass C mr , particle phase average diameter d mr , particle phase average diameter distribution law, particle phase temperature, and particle phase velocity c.
[0052] The determination method of the particle phase molar mass is as follows:
[0053] The particle phase molar mass C mr is linearly distributed along the radial outward direction from the circular small area; the flow is highest on the axis of the throat and gradually decreases along the radial outward direction; the particle phase molar mass C mr of each small area is loaded according to the actual flow data of the engine.
[0054] The determination method of the particle phase average diameter d mr is as follows:
[0055] d mr = 1.38D 0.2932(1-exp(-0.833×10 -8 C mr P m τ))
[0056] In the formula, D is the diameter of the nozzle throat;
[0057] C mr It is the molar mass of the particles in that small region;
[0058] P m It is the pressure in the engine's combustion chamber;
[0059] τ is the residence time of the particle.
[0060] The particle residence time τ is calculated as follows:
[0061] τ=ρ c V c / S m
[0062] In the formula, ρ c The density of the gas;
[0063] V c This refers to the volume of the combustion chamber;
[0064] S m This represents the gas mass flow rate.
[0065] The method for determining the distribution law of the average diameter of the particle phase is as follows:
[0066] The particle phase diameters loaded at the throat exhibit a normal distribution based on the average diameter, as expressed as:
[0067]
[0068] In the formula, d is the particle size of the reference particle;
[0069] Y dr This represents the mass fraction of particles larger than the reference particle size d.
[0070] d mr The average particle size;
[0071] n is the propagation coefficient.
[0072] The method for determining the particulate phase temperature is as follows:
[0073] The particle phase temperature is taken as the melting point temperature of the particles.
[0074] The particle phase velocity c is the speed of sound at engine temperature, specifically:
[0075]
[0076] where k is the gas specific heat ratio of the engine jet;
[0077] R is the gas constant of the engine jet;
[0078] T is the temperature of the engine jet.
[0079] Embodiment
[0080] The particle phase is loaded into the flow field area from the throat of the nozzle. To refine the particle phase parameters at different positions of the throat, the throat is divided into four small areas z1 to z4 to load the particle phase respectively, as shown in Figure 2 .
[0081] Taking the z1 area as an example, according to the particle average calculation formula:
[0082] d mr =1.38D 0.2932 (1-exp(-0.833×10 -8 C mr P m τ))
[0083] Where D is the diameter of the throat of the nozzle, which is 300 mm; C mr is the molar mass of the particles at the local position of the throat, which is 18%; P m is the pressure in the combustion chamber, which is 6.3 MPa; τ is the residence time of the particles in the combustion chamber, τ = ρ c V c / S m , ρ c is the density of the gas, V c is the volume of the combustion chamber, and S m is the mass flow rate of the gas, and the residence time is 0.6 s. The final average diameter of the local particles is 60.9 um.
[0084] After determining the local average particle diameter, the distribution of the particles satisfies the normal distribution, which is in the form of , where Y dr is the mass fraction of the particles larger than the specified particle size d; d mr is the average particle size; and n is the propagation coefficient, which is 10.
[0085] The particles complete condensation in the combustion chamber, exist as droplets in the combustion chamber, and gradually change to solid phase in the nozzle with temperature drop. The phase transition of the particle phase is complex, the particles at the inlet of the throat are in the temperature zone of liquid and solid phases, and the temperature is taken as the melting point temperature of the particles, which is 2300 K.
[0086] The particle phase velocity at the throat of the nozzle is taken as the local sound velocity, and the calculation formula is as follows:
[0087]
[0088] wherein the jet has a jet specific heat ratio of k = 1.16 and a gas constant of R = 320 J / kg-K, and a local jet velocity of 924 m / s.
[0089] Although the present application has been disclosed with reference to the preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not depart from the technical solutions of the present application, shall fall within the protection scope of the technical solutions of the present application.
Claims
1. A method of loading the particle phase of a solid-liquid bundled rocket two-phase jet with a substance, characterized in that: The application relates to a method for loading a particle phase into a throat of a nozzle. The throat of the nozzle is taken as a particle inlet, and the throat is divided into multiple small areas as particle phase inlets; Particle phase loading parameters of each small area are determined to realize particle phase loading of each small area, and finally realize particle phase loading of the whole nozzle throat; The particle phase loading parameters include the particle phase molar mass C mr , the particle phase average diameter d mr , the particle phase average diameter distribution law, the particle phase temperature, the particle phase velocity c; The average diameter d of the particle phase is determined by the following method: mr The determination method is as follows: d mr = 1.38 D 0.2932 (1 - exp(-0.833 x 10 -8 C mr P m τ)) In the formula, D is the diameter of the nozzle throat; C mr is the molar mass of the small region particles; P m is the pressure in the engine combustion chamber; Tau is the residence time of the particles; The calculation method of the particle residence time tau is as follows: = p c V c / S m In the formula, ρ c The density of the gas; V c V is the volume of the combustion chamber; S m for the gas mass flow rate; The determination method of the average diameter distribution of the particle phase is as follows: The diameter of the particle phase loaded in the throat is based on the average diameter and is in a normal distribution, and is expressed as: In the formula, d is the particle size of the reference particle; Y dr is the mass fraction of particles having a size d that is greater than the reference particle size d; d mr D is the average particle diameter; N is a propagation coefficient; The throat of the nozzle is a circular through hole or an elliptical through hole; the method for dividing the throat into multiple small areas is as follows: The center of the throat is a circular small area; multiple annular small areas are divided from the center along the radial direction outward; The determination method of the molar mass of the particle phase is as follows: Particle phase molar mass C mr Linearly distributed from the circular small area in the radial outward direction; the flow is highest on the throat axis and gradually decreases along the radial outward direction; the particle phase molar mass C of each small area mr Load according to the actual flow data of the engine.
2. The method of claim 1, wherein: The radius of the circular small area and the width of each annular small area are the same.
3. The method of claim 2, wherein: The determination method of the particle phase temperature is as follows: The particle phase temperature is the melting point temperature of the particle.
4. The method of claim 3, wherein: The particle phase velocity c is the sound velocity of the engine temperature, and is specifically as follows: In the formula, k is the gas specific heat ratio of the engine jet flow; R is the gas constant of the engine jet flow; T is the temperature of the engine jet flow.