Single droplet generation system for preheating liquid fuel under high-speed incoming flow condition

Abstract

The utility model belongs to the field of hypersonic propulsion, particularly relates to a preheated liquid fuel single droplet generation system under a high-speed incoming flow condition, and aims to solve the problem that in the prior art, a system capable of illustrating different broken forms of preheated liquid fuel single droplets and a droplet breaking kinetic model under the high-speed incoming flow condition is lacked. The kerosene instillation test bench comprises a test bench, a high-speed incoming flow generation system and a kerosene instillation controller, the high-speed incoming flow generation system and the kerosene instillation controller are both fixedly arranged on the test bench, and the input end of the high-speed incoming flow generation system is communicated with the output end of the kerosene instillation controller. According to the method, different broken forms of a single droplet of the preheated liquid fuel and a droplet breaking kinetic model under the high-speed incoming flow condition are clarified, the understanding of the physical process of secondary atomization of transverse injection of different preheated liquid fuels under the high-speed incoming flow condition can be deepened, and meanwhile, a reference is provided for engineering application of an engine injection scheme.

Description

Technical Field

[0001] This invention belongs to the field of hypersonic propulsion, specifically relating to a preheated liquid fuel single droplet generation system under high-speed incoming flow conditions. Background Technology

[0002] In the field of hypersonic propulsion, whether it's a subsonic ramjet engine or a scramjet engine based on detonation combustion, or a detonation engine with detonation combustion organization, such as a rotating detonation engine or a slant detonation engine, the vast majority of them operate on a two-phase propellant injection and mixing scheme. The fuel injection and mixing characteristics directly affect the subsequent propellant combustion effect and determine the engine's thrust performance. Only when the fuel and oxidizer achieve a good mixture can a stable combustion or detonation environment be established. In such engines, the airflow from the isolator section to the combustion chamber inlet is typically high-speed. The liquid fuel jet must be stripped, broken up, and evaporated within milliseconds; therefore, the key operating process of the engine is the mixing, evaporation, and combustion stage of the high-speed incoming flow and the liquid fuel jet in the combustion chamber.

[0003] Kerosene, with its high calorific value, excellent storage performance, and good low-temperature fluidity, is currently the primary fuel and engineering application trend for aerospace propulsion systems. Despite its numerous advantages, kerosene still faces challenges such as difficulty in igniting or detonating cold kerosene. Current experimental research involving liquid transverse jets typically uses room-temperature kerosene rather than preheated kerosene. Achieving active thermal management for engines is a key technology for the future. In active cooling schemes, kerosene absorbs sufficient heat as it flows through regenerative cooling channels, and after preheating, it is injected into the combustion chamber in a gas-liquid critical or even supercritical state. A significant advantage of using preheated liquid fuel injection is that it accelerates the atomization and vaporization process of the fuel in the combustion chamber, thus greatly shortening the fuel-air mixing time and improving the mixing level. Enhanced mixing helps extend the flameout limit, promote ignition, and improve combustion efficiency, thereby expanding the range of stable combustion.

[0004] Under high-speed incoming flow conditions, the droplets formed after the jet of liquid fuel breaks up are subject to strong aerodynamic forces. When these forces are strong enough to overcome the restoring force of the droplet surface tension, the droplet breaks into smaller droplets, a process known as secondary droplet breakup. Fuel droplets at different preheating temperatures may exhibit different morphologies. Current technology lacks a system capable of elucidating the different breakup morphologies of single preheated liquid fuel droplets and establishing droplet breakup dynamics models under high-speed incoming flow conditions. This system aims to deepen our understanding of the physical processes of secondary atomization in the lateral injection of different preheated liquid fuels under high-speed incoming flow conditions and provide a reference for the engineering application of engine injection schemes. Utility Model Content

[0005] To address the lack of a system in the existing technology capable of elucidating different fragmentation morphologies and droplet fragmentation dynamics models of preheated liquid fuel single droplets under high-speed inflow conditions, this utility model provides a preheated liquid fuel single droplet generation system under high-speed inflow conditions, including a test bench, a high-speed inflow generation system, and a kerosene drip controller.

[0006] The high-speed inflow generation system and the kerosene drip controller are both fixedly mounted on the test bench, and the input end of the high-speed inflow generation system is connected to the output end of the kerosene drip controller.

[0007] According to some embodiments of this application, a preheated liquid fuel single droplet generation system under high-speed incoming flow conditions is provided, wherein the test bench includes a test platform and a frame, and the test platform is fixedly mounted on the frame.

[0008] According to some embodiments of this application, a preheating liquid fuel single droplet generation system under high-speed incoming flow conditions is provided. The high-speed incoming flow generation system includes a transition section, a stabilization section, a nozzle section, a honeycomb unit, a damping net, a damping net ring pad, and a fixing seat.

[0009] The high-speed incoming flow generation system is fixedly connected to the test platform via the fixed base. One end of the transition section is fixedly connected to one end of the stabilizing section, and the other end of the stabilizing section is fixedly connected to one end of the nozzle section. The honeycomb, damping net, and damping net ring pad are disposed within the stabilizing section.

[0010] According to some embodiments of this application, a preheating liquid fuel single droplet generation system under high-speed inflow conditions is provided, wherein one end of the transition section is provided with an interface, the other end of the transition section is provided with a first flange, the first flange is provided with a first stop step, and the transition section is provided with a first pressure measuring hole.

[0011] According to some embodiments of this application, a preheated liquid fuel single droplet generation system under high-speed inflow conditions is provided, wherein both ends of the stable section are provided with second flanges, one end of which is provided with a sealing groove and a corresponding sealing ring and is sealed to a first flange provided with a first stop step, and the other end of which is provided with a second stop step.

[0012] According to some embodiments of this application, a preheated liquid fuel single droplet generation system under high-speed inflow conditions is provided, wherein a third flange is provided at one end of the nozzle section, the third flange is provided with a sealing groove and a sealing ring adapted to the second stop step, the other end of the nozzle section is provided with a characteristic surface nozzle, and a second pressure measuring hole is provided on the nozzle section.

[0013] According to some embodiments of this application, a preheating liquid fuel single droplet generation system under high-speed inflow conditions is provided. The stabilization section includes a honeycomb section, an intermediate section and a damping mesh section arranged sequentially. The inner wall of the stabilization section is provided with at least two positioning steps. The honeycomb end is adapted to the honeycomb. The damping mesh section is provided with a damping mesh and a damping mesh ring pad.

[0014] According to some embodiments of this application, a preheated liquid fuel single droplet generation system under high-speed inflow conditions is provided, wherein the kerosene dripping controller includes a housing assembly, a propellant assembly, and a temperature control assembly, wherein the propellant assembly and the temperature control assembly are connected and disposed within the housing assembly.

[0015] According to some embodiments of this application, a preheated liquid fuel single droplet generation system under high-speed incoming flow conditions is provided, wherein the output end of the propellant assembly is connected to one end of the inlet capillary, the other end of the inlet capillary is connected to the input end of the temperature control assembly, the output end of the temperature control assembly is connected to one end of the outlet capillary, and the other end of the outlet capillary is connected to the nozzle section through a fixing block.

[0016] According to some embodiments of the application, a preheating liquid fuel single droplet generation system under high-speed inflow conditions is provided, wherein the frame is made of aluminum profiles and multiple reinforcing beams and diagonal braces are provided inside the frame.

[0017] The beneficial effects of this utility model are:

[0018] In the kerosene droplet injector, the propellant generates droplets of the required diameter via a droplet size control needle valve. These droplets are then heated to the desired temperature by ceramic heating elements on the upper, lower, left, and right sides of the propellant heating chamber before entering the high-speed inflow generation system. This process elucidates the different fragmentation morphologies of preheated liquid fuel droplets under high-speed inflow conditions and establishes a droplet fragmentation kinetic model. This will deepen our understanding of the physical processes of secondary atomization in the lateral injection of different preheated liquid fuels under high-speed inflow conditions. The different fragmentation morphologies and corresponding deformation laws of fuel droplets are influenced by factors such as operating conditions, nozzle diameter and shape, and different preheating temperatures (corresponding to active cooling channel design). Clarifying the different fragmentation morphologies and corresponding deformation laws of different preheated liquid fuel droplets, combined with existing knowledge of droplet deformation and fragmentation, provides guidance for the selection of ignition positions and the optimized design of the injection system, thereby improving engine performance. Attached Figure Description

[0019] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the overall structure of some embodiments of this application;

[0021] Figure 2 This is a schematic diagram of the external structure of a high-speed incoming flow generation system according to some embodiments of this application;

[0022] Figure 3 This is a schematic diagram of the transition section structure of some embodiments of this application;

[0023] Figure 4 These are schematic diagrams of the stable segment structure of some embodiments of this application;

[0024] Figure 5 This is a schematic cross-sectional view of the stable section of some embodiments of this application;

[0025] Figure 6 These are schematic diagrams of nozzle section structures according to some embodiments of this application;

[0026] Figure 7 These are cellular devices according to some embodiments of this application;

[0027] Figure 8 This is a damping mesh in some embodiments of this application;

[0028] Figure 9 These are damping mesh ring pads in some embodiments of this application;

[0029] Figure 10 This is a schematic diagram of the external structure of a kerosene drip controller according to some embodiments of this application;

[0030] Figure 11 This is a schematic diagram of the internal structure of a kerosene drip controller according to some embodiments of this application;

[0031] Figure 12 This is a schematic diagram of the temperature control component structure according to some embodiments of this application;

[0032] Figure 13 These are schematic diagrams of protective casings according to some embodiments of this application;

[0033] Figure 14 These are schematic diagrams of the caps of some embodiments of this application;

[0034] Figure 15 These are schematic diagrams of threaded push rods according to some embodiments of this application;

[0035] Figure 16 These are schematic diagrams of pistons according to some embodiments of this application;

[0036] Figure 17 These are schematic diagrams of the propellant assembly structure according to some embodiments of this application;

[0037] Figure 18 This is a schematic cross-sectional view of the propellant heating chamber according to some embodiments of this application;

[0038] Figure 19 This is a schematic diagram of a fixed block according to some embodiments of this application.

[0039] In the diagram: 1. Test bench; 11. Test platform; 12. Frame;

[0040] 2. High-speed incoming flow generation system; 21. Transition section; 211. Interface; 212. First flange; 213. First stop step; 214. First pressure measuring hole; 22. Stabilizing section; 221. Second flange; 2211. Sealing groove; 2212. Second stop step; 222. Honeycomb section; 223. Intermediate section; 224. Damping mesh section; 225. Positioning step; 23. Nozzle section; 231. Third flange; 232. Characteristic surface nozzle; 233. Second pressure measuring hole; 24. Honeycomb; 25. Damping mesh; 26. Damping mesh ring gasket; 27. Fixing seat;

[0041] 3. Kerosene drip controller; 31. Housing assembly; 311. Protective housing; 3111. Connection hole; 3112. Cable plug hole; 3113. Control needle valve hole; 312. Cover; 3121. Connection threaded hole; 3122. Countersunk threaded hole; 3123. Square groove; 3124. Threaded hole; 313. Temperature display head mounting square groove; 314. Temperature display head; 315. Cable plug;

[0042] 32. Propellant assembly; 321. Threaded push rod; 3211. Threaded section; 3212. Manual knob; 3213. Positioning groove; 322. Piston; 3221. Positioning threaded hole; 3222. Piston sealing groove; 323. Cavity; 324. Connecting sealing cap; 325. Three-way adapter valve; 326. Control needle valve; 327. Control needle valve locking internal thread; 328. Connector lock nut;

[0043] 33. Temperature control assembly; 331. Propellant heating chamber; 3311. Liquid inlet; 3312. Liquid outlet; 3313. Coiled tubing; 332. Temperature probe; 333. Upper and lower ceramic heating elements; 334. Left and right ceramic heating elements; 335. Lower insulation cover; 336. Upper insulation cover;

[0044] 34. Inlet capillary tube; 35. Outlet capillary tube; 36. Fixing block; 361. Nozzle mating end; 362. Fixing block connection hole. Detailed Implementation

[0045] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the invention. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0046] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0047] like Figures 1 to 19 As shown, this utility model provides a preheated liquid fuel single droplet generation system under high-speed incoming flow conditions, including a test bench 1, a high-speed incoming flow generation system 2, and a kerosene drip controller 3;

[0048] Both the high-speed inflow generation system 2 and the kerosene drip controller 3 are fixedly mounted on the test bench 1, and the input end of the high-speed inflow generation system 2 is connected to the output end of the kerosene drip controller 3.

[0049] like Figure 1 As shown, in specific implementation, the kerosene drip controller 3 and the high-speed inflow generation system 2 are both fixedly placed on the test bench 1, and the test bench 1 is connected and fixed to the ground by anchor bolts.

[0050] In some embodiments, the test bench 1 includes a test platform 11 and a frame 12. The test platform 11 is fixedly mounted on the frame 12, and the frame 12 is provided with a plurality of reinforcing beams and diagonal braces.

[0051] The frame 12 is constructed from aluminum profiles, which are lightweight yet strong, making them an ideal material for constructing test benches. To further enhance the structural strength of the test bench 1, an aluminum profile is added to both the upper and lower parts as reinforcing beams. Additionally, two 45-degree reinforcing aluminum profiles are added at each corner as diagonal braces. Anchor bolts are installed under the four bottom shelves to connect the test bench 1 to the laboratory floor for secure installation. An optical platform is selected as the test platform 11 on the test bench 1. The standard bolt holes on the platform facilitate the placement and fixing of the kerosene drip controller 3 and the high-speed inflow generation system 2.

[0052] like Figures 2 to 9 As shown, in some embodiments, the high-speed incoming flow generation system 2 includes a transition section 21, a stabilization section 22, a nozzle section 23, a honeycomb unit 24, a damping net 25, a damping net ring pad 26, and a mounting base 27.

[0053] The high-speed incoming flow generation system 2 is fixedly connected to the test platform 11 via the fixed base 27. One end of the transition section 21 is fixedly connected to one end of the stabilization section 22, and the other end of the stabilization section 22 is fixedly connected to one end of the nozzle section 23. The honeycomb unit 24, the damping net 25, and the damping net ring pad 26 are disposed in the stabilization section 22.

[0054] In practice, the mounting base 27 consists of two parts, upper and lower. After being installed into the stabilizing section 22, they are connected and locked with bolts. The lower part is connected and fixed to the standard bolt holes on the optical platform selected on the test bench 1 by bolts. The two mounting bases 27 are distributed on both sides of the stabilizing section 22 to fix the entire high-speed incoming flow generation system 2 on the optical platform selected on the test bench 1.

[0055] like Figure 3 As shown, in some embodiments, one end of the transition section 21 is provided with an interface 211, the other end of the transition section 21 is provided with a first flange 212, the first flange 212 is provided with a first stop step 213, and the transition section 21 is provided with a first pressure measuring hole 214.

[0056] In specific implementation, the front end interface 211 of the transition section 21 is a welded interface, where a straight-through connector is welded and connected to the main air pipeline via a metal flexible hose. The rear end of the transition section 21 is a matching first flange 212, which is bolted to the front flange of the stabilizing section 22. Simultaneously, a first stop step 213 is machined on the first flange 212, which mates with the sealing groove on the front flange of the stabilizing section 22, serving to tighten the sealing ring and facilitate assembly positioning. Furthermore, the face of the first flange 212 at the rear end of the transition section 21 also functions as a clamping device for the honeycomb unit 24. A first pressure measuring hole 214 is also provided in the transition section 21 to measure the pressure of the incoming flow before it enters the stabilizing section for rectification.

[0057] like Figures 2-4 As shown, in some embodiments, both ends of the stabilizing section 22 are provided with second flanges 221. One end of the second flange 221, which is provided with a sealing groove 2211 and a corresponding sealing ring, is sealed to the first flange 212, which is provided with a first stop step 213. The other end of the second flange 221 is provided with a second stop step 2212.

[0058] In practice, the stabilizing section 22 is placed after the transition section 21, mainly to rectify the turbulent incoming airflow. The second flange 221 at the front end of the stabilizing section 22 is bolted to the first flange 212 at the rear end of the transition section 21, and the second flange 221 at the rear end of the stabilizing section 22 is also bolted to the third flange 231 at the front end of the nozzle section 23. The second flange 221 at the front end of the stabilizing section 22 has a sealing groove 2211, in which a sealing ring is fitted. This ring mates with the first stop step 213 on the first flange 212 at the rear end of the transition section 21, ensuring a seal between the two. The second stop step 2212 at the rear end of the stabilizing section 22 has a second stop step 2212, which mates with the sealing groove on the third flange 231 at the front end of the nozzle section 23, both to tighten the sealing ring and to facilitate assembly and positioning.

[0059] like Figures 2-6As shown, in some embodiments, a third flange 231 is provided at one end of the nozzle section 23, the third flange 231 is provided with a sealing groove and a sealing ring adapted to the second stop step 2212, the other end of the nozzle section 23 is provided with a characteristic surface nozzle 232, and a second pressure measuring hole 233 is provided on the nozzle section 23.

[0060] In practical implementation, the third flange 231 at the front of nozzle section 23 is bolted to the second flange 221 at the rear of stabilizing section 22. The third flange 231 has a sealing groove machined on it, and a sealing ring is fitted inside. This ring mates with the second stop step 2212 on the second flange 221 at the rear of stabilizing section 22, ensuring a seal between the two. The flange face also serves to compress the damping mesh 25. The rear nozzle is designed with a characteristic curve to achieve the required specific exit Mach number. A second pressure measuring port 233 is also provided in nozzle section 23 to measure the pressure of the rectified incoming flow before it enters the nozzle.

[0061] like Figures 2-5 As shown, in some embodiments, the stabilizing section 22 includes a honeycomb section 222, an intermediate section 223 and a damping mesh section 224 arranged in sequence. The inner wall of the stabilizing section 22 is provided with at least two positioning steps 225. The honeycomb section 222 is adapted to the honeycomb 24. The damping mesh section 224 is provided with a damping mesh 25 and a damping mesh ring pad 26.

[0062] In practice, the stabilizing section 22 is divided into three sections: the honeycomb section 222, the intermediate section 223, and the damping mesh section 224. The honeycomb section 222 is used to house the honeycomb unit 24 and is also machined with honeycomb unit positioning steps. The damping mesh section 224 is used to house at least two damping meshes 25 and damping mesh ring pads 26.

[0063] The honeycomb unit 24 can transform large vortices in the airflow from the duct into smaller vortices and guide the airflow. The small vortices exiting the honeycomb unit 24 are damped and quickly disappear in the damping mesh section 224 after the stabilizing section 22, reducing airflow turbulence. Simultaneously, as the airflow passes through the honeycomb unit 24, the reduced lateral flow straightens the airflow direction, aligning it with the axis of the stabilizing section 22. The honeycomb unit 24 is made of S304 stainless steel, stamped into corrugated strips, and then resistance welded into a hexagonal honeycomb panel. A circular honeycomb piece is then cut using wire cutting and laser-welded into the circular ring. The honeycomb unit 24 is fitted into the honeycomb unit section 222 placed in the stabilizing section 22. One side of the honeycomb unit 24 is positioned by a positioning step on the honeycomb unit section 222, while the other side is pressed against the flange face at the rear end of the transition section 21.

[0064] To simulate the actual flight conditions of an aircraft, measures are needed to reduce airflow turbulence, with damping net 25 being the most effective. Since the airflow velocity in the stabilization section 22 is the lowest and losses are minimal, damping nets 25 are installed within the stabilization section 22, used simultaneously with the honeycomb unit 24, and positioned after the honeycomb unit 24. After passing through the damping net 25, large vortices are broken down into smaller vortices. Based on the existing structural dimensions, two damping nets 25 are selected and sequentially installed from the damping net section 224 of the stabilization section 22. The first net is installed and positioned using the positioning step in the damping net section 224 of the stabilization section. Then, the damping net ring gasket 26 is installed to press the first damping net and position the second damping net. Finally, the second damping net is installed and pressed against the third flange 231 at the front end of the nozzle section 23.

[0065] The damping mesh 25 is made by first weaving 1mm stainless steel into a cross-shaped mesh, then fixing it by pressure welding, and finally cutting it into the required pieces by laser. The damping mesh ring pad 26 is fitted into the damping mesh segment 224 of the stabilizing section 22 to press the first damping mesh piece and position the second damping mesh piece.

[0066] like Figures 10-19 As shown, in some embodiments, the kerosene dripping controller 3 includes a housing assembly 31, a propellant assembly 32, and a temperature control assembly 33, with the propellant assembly 32 and the temperature control assembly 33 connected and disposed within the housing assembly 31.

[0067] In specific implementation, the kerosene drip controller 3 adopts a compact integrated layout. The housing assembly 31 includes a protective shell 311 and a cover 312. The protective shell 311 serves a protective function. The connection hole on the protective shell 311 is fixedly connected to the cover 312 by screws. The temperature display head mounting slot 313 is used to install and fix the temperature display head 314. The cable plug hole 3112 is used to fit the cable plug 315, and a heat dissipation vent is provided on this side. The control needle valve hole 3113 is used to fit the control needle valve 326.

[0068] The connecting threaded hole 3121 on the cover 312 is connected to the connecting hole 3111 on the protective shell 311 by screws. The countersunk threaded hole 3122 is connected to the upper insulation cover 336 and the lower insulation cover 335 by bolts. The square groove 3123 is positioned and fits to place one end of the upper insulation cover 336 and the lower insulation cover 335. The threaded hole 3124 is adapted to and fixed to the left external thread section of the connecting sealing cover 324.

[0069] In some embodiments, the output end of the propellant assembly 32 is connected to one end of the inlet capillary 34, the other end of the inlet capillary 34 is connected to the input end of the temperature control assembly 33, the output end of the temperature control assembly 33 is connected to one end of the outlet capillary 35, and the other end of the outlet capillary 35 is connected to the nozzle section 23 through the fixing block 36.

[0070] In some embodiments, the propellant assembly 32 includes a threaded push rod 321, a piston 322, a cavity 323, a connecting sealing cap 324, a three-way adapter valve 325, a control needle valve 326, a control needle valve locking internal thread 327, and a connector locking nut 328.

[0071] One end of the cavity 323 is fixedly connected to the housing assembly 31 via a connecting sealing cap 324. One end of the threaded push rod 321 is located inside the cavity 323 via a piston 322. The other end of the cavity 323 is connected to the control needle valve 326 via a three-way adapter valve 325 and a control needle valve locking thread 327 located inside the three-way adapter valve 325. The outlet of the three-way adapter valve 325 is connected to one end of the liquid inlet capillary tube 34 via a connector locking nut 328. The other end of the liquid inlet capillary tube 34 is connected to the temperature control assembly 33.

[0072] In specific implementation, the threaded push rod 321 is a propellant threaded push rod, and its threaded section 3211 mates with the internal threaded section on the left side of the connecting sealing cover 324, so that the threaded push rod 321 can move freely forward and backward. The gear-shaped manual knob 3212 facilitates manual feeding. The three positioning threaded holes 3221 on the piston 322 are positioned and locked with the positioning grooves 3213 on the threaded push rod 321 by positioning screws, which can ensure that the threaded push rod 321 can rotate freely during manual feeding. The two piston sealing grooves 3222 are fitted with sealing rings to seal with the inside of the propellant cavity 323.

[0073] The cavity 323 is a propellant cavity. The top and bottom of the outer side of the cavity are threaded to be fixedly connected to the connecting sealing cap 324 and the three-way transition valve 325, respectively. The sealing grooves at the top and bottom of the cavity 323 are fitted with sealing rings to seal the connection between the cavity 323 and the connecting sealing cap 324 and the three-way transition valve 325. To facilitate the tightening of the cavity 323 and the connecting sealing cap 324, a hexagonal clamping area is designed and machined at the bottom of the cavity 323.

[0074] The connecting sealing cap 324 is a sealing cap for connecting the propellant chamber and the push rod. The internal thread on one side is adapted to connect with one end of the chamber 323, and the external thread on the other side is adapted to connect with the cap 312. The internal thread on this side is engaged with the threaded section of the threaded push rod 321. In order to facilitate the tightening of the connecting sealing cap 324 and the propellant chamber, a hexagonal clamping area is designed and machined on the right side of the connecting sealing cap 324.

[0075] One side of the three-way adapter valve 325 is threaded to one end of the cavity 323, and the connection is equipped with a sealing groove and a sealing ring. The other side is threaded to the locking internal thread 327 of the control needle valve. The internal tapered mating surface and the tapered needle surface of the control needle valve are controlled by rotating the manual knob of the control needle valve to control the distance between them, thereby controlling the size of the generated droplets. The upper part of the three-way adapter valve 325 is threaded to the connector locking nut 328, and a sealing groove and a sealing ring are provided at its connection.

[0076] The control needle valve 326 is a droplet size control needle valve, one end of which is a control needle valve tapered needle surface, which is used to match the mating surface of the three-way adapter valve 325. The distance between the control needle valve tapered needle surface and the mating surface of the three-way adapter valve 325 is controlled by manually feeding the control needle valve through the manual knob, thereby controlling the size of the generated droplets. The threaded section in the middle of the control needle valve 326 is threaded to the control needle valve locking internal thread 327.

[0077] The locking internal thread 327 of the control needle valve is adapted to the control needle valve 326. The locking internal thread of the control needle valve and the three-way adapter valve 325 are positioned and fixed by the positioning step on the locking internal thread of the control needle valve. The locking internal thread of the control needle valve 327 is locked by the locking groove on the control needle valve. The internal thread of the locking internal thread of the control needle valve is connected to the threaded section of the control needle valve.

[0078] One end of the connector locking nut 328 has an internal thread, which is connected to the external thread on the upper side of the three-way adapter valve. The connector locking nut and the upper side of the three-way adapter valve are sealed by placing a sealing ring on the upper side of the three-way adapter valve. The other end has a liquid inlet capillary mating hole that can be inserted into the liquid inlet capillary 34.

[0079] The liquid inlet capillary tube 34 is used to connect the upper side of the three-way adapter valve 325 to the propellant heating chamber 331, and to introduce the fuel liquid in the chamber 323 into the propellant heating chamber 331. The liquid inlet capillary tube 34 and the three-way adapter valve 325 are connected together and sealed by the joint locking nut 328. After the liquid inlet capillary tube 34 is inserted into the liquid inlet 3311 of the propellant heating chamber, it is welded to the propellant heating chamber 331.

[0080] After the propellant heating chamber outlet 3312 is inserted into the propellant heating chamber connection end of the outlet capillary tube 35 and welded to it, the internal pipeline is a coiled pipeline 3313 to facilitate rapid and uniform heating of the ceramic heating element. The temperature probe connection threaded hole is connected to the temperature probe threaded section.

[0081] The outlet capillary 35 connects the propellant heating chamber 331 and the fixing block 36, guiding the fuel liquid heated to different temperatures from the propellant chamber to the outlet of the high-speed incoming flow generation system nozzle section 23. Corresponding suspended droplets are generated at the outlet of the fixing block connection end. To ensure the liquid temperature remains constant during flow through the outlet capillary 35, it needs to be covered with insulation material. The propellant heating chamber connection end of the outlet capillary 35 is inserted into the propellant heating chamber outlet and welded to the propellant heating chamber 331. The fixing block connection end of the outlet capillary 35 is inserted into the fixing block connection hole 362 and welded to the fixing block 36.

[0082] After the nozzle mating end 361 of the fixing block 36 is mated with the outlet of the nozzle section of the high-speed incoming flow generation system, it is welded to ensure that the lower surface is tangent to the upper surface of the outlet of the nozzle section of the high-speed incoming flow generation system; after the connecting hole 362 of the fixing block is inserted into the liquid outlet capillary, it is welded to the liquid outlet capillary.

[0083] The temperature probe 332 is an existing product with a threaded section and a terminal block. The threaded section connects to the threaded hole on the propellant heating chamber, and the terminal block connects to the corresponding terminal on the temperature display head, which can display the liquid temperature in the propellant heating chamber pipeline in real time.

[0084] The upper and lower ceramic heating elements 333 are made of aluminum silicate ceramic fiber board as insulation material. The upper and lower ceramic heating elements are installed on the upper and lower sides of the propellant heating chamber and are positioned and clamped together by the upper and lower insulation covers and the left and right ceramic heating elements. The wiring terminals of the upper and lower ceramic heating elements are integrated into the cable connection port of the cable plug 315.

[0085] Left and right ceramic heating elements 334: These are made of aluminum silicate ceramic fiber board, an insulating material. The left and right ceramic heating elements are installed on the left and right sides of the propellant heating chamber, secured by mating bolts in the threaded holes on both sides of the lower insulation cover and by the mutual positioning and clamping of the upper and lower ceramic heating elements. The wiring terminals for the left and right ceramic heating elements are integrated into the cable connector.

[0086] The cable plug 315 is fitted into the cable plug hole of the protective housing. The cable terminal is used to connect the upper and lower ceramic heating elements and the left and right ceramic heating element terminals. The other end of the cable is connected to the power heater, which is existing technology and is not shown in the figure.

[0087] The lower insulation cover 335 and the upper insulation cover 336 are connected and fixed by bolts. The groove inside the cover fixes the left and right ceramic heating elements 334. Both the lower insulation cover 335 and the upper insulation cover 336 have sealing screw holes. The sealing screw holes are connected to the countersunk threaded holes of the sealing cover 312 by screws. The first step of the lower insulation cover 335 and the second step of the upper insulation cover 336 are positioned and fitted with the sealing square groove 3123.

[0088] The temperature display head is an optional existing product, which is installed in the temperature display head mounting slot 313 on the protective housing. The wiring port of the temperature display head is connected to the wiring post of the temperature probe to display the liquid temperature in the propellant heating chamber pipeline in real time on its display panel.

[0089] In the description of this utility model, terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," which indicate direction or positional relationships, are based on the direction or positional relationships shown in the accompanying drawings. These are used merely for ease of description and do not indicate or imply that the device or element must have a specific orientation, or be constructed and operated in a specific orientation; therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0090] Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0091] The term "comprising" or any other similar term is intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus / device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent in such process, method, article, or apparatus / device.

[0092] The technical solution of this utility model has been described above with reference to the preferred embodiments shown in the accompanying drawings. However, it will be readily understood by those skilled in the art that the protection scope of this utility model is obviously not limited to these specific embodiments. Without departing from the principle of this utility model, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of this utility model.

Claims

1. A preheated liquid fuel single droplet generation system under high speed incoming flow conditions, characterized by, The test bench, the high-speed airflow generating system and the kerosene dripping controller are provided. The high-speed airflow generating system and the kerosene dripping controller are fixedly arranged on the test bench, and the input end of the high-speed airflow generating system is in communication with the output end of the kerosene dripping controller.

2. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 1, characterized by, The test bench comprises a test platform and a frame, and the test platform is fixedly arranged on the frame.

3. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 2, characterized by, The high-speed airflow generating system comprises a transition section, a stabilizing section, a nozzle section, a honeycomb device, a damping net, a damping net ring pad and a fixing seat. The high-speed airflow generating system is fixedly connected with the test platform through the fixing seat, one end of the transition section is fixedly connected with one end of the stabilizing section, and the other end of the stabilizing section is fixedly connected with one end of the nozzle section.

4. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 3, characterized by, One end of the transition section is provided with an interface, the other end of the transition section is provided with a first flange, the first flange is provided with a first stop opening step, and a first pressure measuring hole is formed in the transition section.

5. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 4, characterized by, Both ends of the stabilizing section are provided with second flanges, the second flange of one end is provided with a sealing groove and is provided with a corresponding sealing ring, and the second flange of the other end is provided with a second stop opening step.

6. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 5, characterized by, One end of the nozzle section is provided with a third flange, the third flange is provided with a sealing groove and a sealing ring matched with the second stop opening step, the other end of the nozzle section is provided with a characteristic surface nozzle, and a second pressure measuring hole is formed in the nozzle section.

7. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 5, characterized by, The stabilizing section comprises a honeycomb device section, an intermediate section and a damping net section arranged in sequence, the inner wall of the stabilizing section is provided with at least two positioning steps, the honeycomb device end is matched with the honeycomb device, and the damping net section is provided with a damping net and a damping net ring pad.

8. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 3, characterized by, The kerosene dripping controller comprises a shell assembly, a propellant assembly and a temperature control assembly, the propellant assembly and the temperature control assembly are in communication and arranged in the shell assembly.

9. The preheated liquid fuel single droplet generation system under high speed inflow conditions according to claim 8, characterized by, One end of the liquid inlet capillary is in communication with the output end of the propellant assembly, the other end of the liquid inlet capillary is in communication with the input end of the temperature control assembly, the output end of the temperature control assembly is in communication with one end of the liquid outlet capillary, and the other end of the liquid outlet capillary is connected with the nozzle section through a fixing block.

10. The preheated liquid fuel single droplet generation system under high speed inflow conditions of claim 2, wherein, The frame is made of aluminum profiles, and a plurality of reinforcing beams and diagonal braces are arranged in the frame.

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