CN113090415B - Variable flow solid-liquid mixing engine - Google Patents
Variable flow solid-liquid mixing engine Download PDFInfo
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- CN113090415B CN113090415B CN202110391958.8A CN202110391958A CN113090415B CN 113090415 B CN113090415 B CN 113090415B CN 202110391958 A CN202110391958 A CN 202110391958A CN 113090415 B CN113090415 B CN 113090415B
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- venturi
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention relates to a variable flow solid-liquid hybrid engine, belonging to the field of solid-liquid hybrid engines; the device comprises an oxidant storage tank, a thrust chamber, a control valve and an adjustable cavitation venturi, wherein the oxidant storage tank is communicated with the thrust chamber through a pipeline and the adjustable cavitation venturi to realize the input of an oxidant into the thrust chamber, and the control valve arranged on the pipeline controls the on-off of the oxidant; the adjustable cavitation venturi comprises a stepping motor, a fixed flange, a venturi press screw, a venturi inlet joint, an adjustable cavitation venturi shell, a cavitation venturi and a needle cone; the axial movement of the needle cone is controlled by the stepping motor, the gap between the needle cone and the throat diameter of the cavitation venturi is changed, and then the flow of the oxidant supply is changed, so that the thrust adjustment is realized. The adjustable cavitation venturi tube adopted by the invention can simply realize large-scale flow adjustment.
Description
Technical Field
The invention belongs to the field of solid-liquid mixed engines, and particularly relates to a variable flow solid-liquid mixed engine.
Background
The rocket engine is a power system of a rocket, a missile and various spacecrafts, the content and the form of the spaceflight task are gradually increased along with the development of the spaceflight industry, and particularly, the rocket engine has higher requirements on the thrust adjusting capability of the rocket engine in the fields of orbital maneuver, round trip and intersection butt joint of the spaceflight and the like. Because long-time thrust adjustment is generally required in the aerospace mission, the reliability requirement of the engine is high; while being limited by the overall design of the aircraft, the system installation space is often not large, which also places a demand on the miniaturization of the propulsion system.
Rocket engines are often classified into solid rocket engines, liquid rocket engines, solid-liquid hybrid engines and the like according to different physical states of propellants, and all have thrust adjustment capability. The solid engine mainly adopts structures such as throat bolts and the like to adjust throat area to change thrust, but the problem of needle bolt heat protection is more remarkable, and the reliability is not high; the liquid rocket engine is easy to realize thrust adjustment by controlling the flow rate to change through a valve, but the engine has a complex structure and is difficult to realize miniaturization; the solid-liquid hybrid engine is a rocket engine with the oxidant and the fuel stored separately, has the advantages of high safety and reliability, convenient energy management, miniaturization and the like, is easy to change the thrust by adjusting the flow, and has wide application prospect in the field of thrust-variable power systems.
Solid-liquid hybrid engines typically employ methods of varying the mass flow of the oxidizer to achieve variable thrust. Journal "Flow Measurement & Instrumentation" 2014, document Application of variable area cavitating venturi as a dynamic Flow controller discloses a method of regulating oxidant Flow using an adjustable cavitation venturi and studies the effect of regulating cone travel on venturi performance, which shows that the venturi can regulate Flow when the position of the needle cone and upstream pressure are determined. But the needle cone of the device is easy to wear, needs to be frequently disassembled and replaced, and has lower service life.
Disclosure of Invention
The technical problems to be solved are as follows:
in order to avoid the defects of the prior art, the invention provides a variable flow solid-liquid mixed engine, which adopts an adjustable cavitation venturi tube and a control valve to be matched for use so as to realize the flow regulation of an oxidant; and the structure of the oxidizer storage tank is optimized to be spherical.
The technical scheme of the invention is as follows: the variable flow solid-liquid mixing engine comprises an oxidant storage tank, a thrust chamber and a control valve, wherein the oxidant storage tank is communicated with the thrust chamber through a pipeline to realize the input of an oxidant into the thrust chamber, and the control valve arranged on the pipeline controls the on-off of the oxidant; the method is characterized in that: the adjustable cavitation venturi is connected between the control valve and the thrust chamber through a pipeline;
the adjustable cavitation venturi comprises a stepping motor, a fixed flange, a venturi pressure screw, a venturi inlet joint, an adjustable cavitation venturi shell, a cavitation venturi and a needle cone; the stepping motor is coaxially arranged on the fixed flange, and an output shaft of the stepping motor is coaxially connected with the needle cone; the adjustable cavitation venturi casing is of a columnar structure, one end of the columnar structure is provided with a flange plate, a stepped through hole is formed along the central line, a venturi press screw is arranged in the hole at one end of the flange plate through threads, a cavitation venturi is arranged at the other end of the columnar structure through threads, and an outlet of the cavitation venturi is communicated with an inlet of the thrust chamber through a pipeline and is used as an output channel of an oxidant; the side wall of the adjustable cavitation venturi tube shell is provided with a vent hole communicated with the stepped through hole in the radial direction, and the outlet of the vent hole is communicated with the oxidant storage tank through a venturi tube inlet joint and a pipeline to be used as an input channel of the oxidant; the needle cone coaxially and sequentially passes through the venturi press screw and the central through hole of the adjustable cavitation venturi shell, then is inserted into the throat diameter of the cavitation venturi central hole, the needle cone is driven by the stepping motor to reciprocate, the gap between the needle cone and the throat diameter of the cavitation venturi is changed, the flow of oxidant supply is changed, and thrust adjustment is realized.
The invention further adopts the technical scheme that: the oxidant storage tank is of a spherical structure and comprises a pressurizing joint, an upper storage tank shell, a lower storage tank shell and a supply joint; the upper shell and the lower shell of the storage tank are hemispherical shells with flange structures on the peripheral surfaces of ports, and are fastened into hollow spherical cavities through bolts and nuts; the top end of the upper shell of the storage tank is provided with a through hole which is fixedly connected with a pressurizing connector and is used for connecting high-pressure gas to pressurize; the bottom of the lower shell of the storage tank is provided with a through hole which is connected with a supply joint and used for conveying an oxidant to the thrust chamber.
The invention further adopts the technical scheme that: the flange structure of the upper shell of the storage tank is an upper flange of the storage tank, the flange structure of the lower shell of the storage tank is a lower flange of the storage tank, the mounting surfaces of the upper flange of the storage tank and the lower flange of the storage tank are sealed by adopting a tongue-and-groove structure, and a flange sealing ring is placed in the groove.
The invention further adopts the technical scheme that: the inner peripheral surface in the venturi press screw is coaxially provided with a guide ring, so that the needle cone is prevented from directly contacting with the inner surface of the venturi press screw, and abrasion is reduced; the venturi pressure screw and the adjustable cavitation venturi shell are sealed through the venturi pressure screw sealing ring, and the adjustable cavitation venturi shell is sealed through the venturi sealing ring with the needle cone and the cavitation venturi.
The invention further adopts the technical scheme that: the device also comprises adjusting screw rods and adjusting nuts, wherein one ends of the four adjusting screw rods are respectively arranged on the fixed flange plate along the circumferential direction through the adjusting nuts, and the other ends of the four adjusting screw rods are respectively arranged on the flange plate of the adjustable cavitation venturi tube shell along the circumferential direction through the adjusting nuts; and the axial directions of the four adjusting screw rods are parallel to the output shaft of the stepping motor, and the distance between the fixed flange plate and the flange plate of the adjustable cavitation venturi tube shell is adjusted by screwing the adjusting nuts, so that the distance between the stepping motor and the adjustable cavitation venturi tube shell is adjusted.
The invention further adopts the technical scheme that: the needle cone is connected with the output shaft of the stepping motor through threads, and a limiting ring is sleeved on the needle cone and is arranged on the outer side of the venturi pressing screw and used for limiting axial displacement of the needle cone.
The invention further adopts the technical scheme that: the two ends of the cavitation venturi are respectively connected with the adjustable cavitation venturi shell and the pipeline through threads, the part from the inner inlet of the central hole to the throat diameter is of a convergent structure, and the part from the throat diameter to the outlet is of an expansion structure; the convergence angle range is 40-60 degrees, and the divergence angle range is 6-8 degrees; the axial length of the equal diameter section of the throat part is 0.25-1 times of the throat diameter.
The invention further adopts the technical scheme that: the convergence angle and the divergence angle are respectively 50 degrees and 6 degrees, the equal diameter sections of the throat diameter and the throat are 2mm, and the transition fillet of the throat is 1mm; the inlet and outlet diameters of the cavitation venturi tube are 10mm, the axial length of the converging section is 8.57mm, the axial length of the diverging section is 76.32mm, and the total length is 86.89mm.
The invention further adopts the technical scheme that: the taper angle of the conical part of the needle cone is 10 degrees, and the axial length is 45.72mm; the diameter of the constant diameter cylindrical portion was 8mm.
The invention further adopts the technical scheme that: the thrust chamber comprises an ignition press screw, an ignition sealing cone, an ignition seat, a front combustion chamber heat insulation layer, a combustion chamber shell, a combustion chamber heat insulation layer, a fuel grain, a spray pipe sealing ring, a spray pipe shell, a graphite spray pipe, a graphite gasket, a front end cover, an injector and a thrust chamber inlet joint, wherein the front end cover and the spray pipe shell are respectively and hermetically arranged at two ends of the combustion chamber shell; the center of the front end cover is provided with a through hole, a thrust chamber inlet joint and an injector are coaxially arranged, the thrust chamber inlet joint and the injector are communicated with the outlet end of the cavitation venturi through a pipeline, an ignition assembly is arranged on the wall surface of the front end cover, the ignition assembly comprises an ignition press screw, an ignition sealing cone and an ignition seat, the ignition press screw is in threaded connection with the ignition seat, and the ignition press screw is sealed through the conical ignition sealing cone; the front end cover is connected with the combustion chamber shell through threads and is sealed through a graphite gasket; a front combustion chamber heat insulation layer and a combustion chamber heat insulation layer are arranged in the combustion chamber shell, and fuel grains are poured into the combustion chamber heat insulation layer; the spray pipe shell is in threaded connection with the combustion chamber shell and is sealed by using a spray pipe sealing ring; the graphite spray pipe is arranged in the spray pipe shell.
Advantageous effects
The invention has the beneficial effects that:
1. compared with other shapes, the oxidant storage tank has smaller surface area when the volumes are the same, can effectively reduce the quality of the outer protective layer, has excellent pressure resistance and needs thinner wall thickness.
2. The oxidant storage tank comprises an upper part and a lower part, and a capsule or a membrane can be arranged in the storage tank to separate the pressurized gas from the oxidant, so that the phenomenon of air blockage between the pressurized gas and the oxidant can be effectively overcome, and the stable transportation of the oxidant is ensured.
3. The upper flange and the lower flange of the oxidant storage tank adopt tongue-and-groove sealing surfaces. The flange sealing ring is not extruded in the groove, the compression area is minimum, and the gasket is uniformly stressed. And because the flange sealing ring is not in direct contact with the oxidant, the oxidant corrosion and pressure permeation have little influence, and high-pressure sealing can be realized.
4. The adjustable cavitation venturi tube adopted by the invention can simply realize large-scale flow adjustment. The stroke of the needle cone is regulated by the stepping motor, and the precision can reach 0.005mm. Experiments show that under different inlet pressures, the change of the position of the needle cone can realize the change range of 0-250g/s of flow, the flow of the oxidant can be accurately controlled by the control of the stepping motor, and the engine work is not influenced due to the flow control problem. And the stepping motor is connected with the adjustable cavitation venturi shell through the screw rod, and the distance between the stepping motor and the adjustable cavitation venturi shell can be conveniently adjusted by using the adjusting nut, so that the movement range of the needle cone is long, and the adjustable cavitation venturi can adapt to various flow adjusting conditions. When the replacement is needed, the disassembly process is also more convenient.
5. The invention is designed with the venturi pressure screw, and the coaxiality of the needle cone and the cavitation venturi can be ensured after the venturi pressure screw is screwed. The guide ring is arranged between the venturi pressure screw and the needle cone, so that the needle cone can be prevented from being in direct contact with the molded surface, and the service life of the adjustable cavitation venturi is greatly prolonged. The expanding angle of the cavitation venturi is 6 degrees, and the pressure loss is small; the axial length of the throat design is equal to the throat diameter, so that a stable flow coefficient can be obtained. The diameter of the cylindrical part of the needle cone is 8mm, so that the strength can be ensured; the taper angle is 10 degrees, so that the processing difficulty is reduced on the basis of ensuring the accurate adjustment of the flow, and the material cost is further saved; the needle cone adopts a polishing process, the surface finish is 0.2, and the friction between the needle cone and the guide ring and the first venturi sealing ring is also small.
6. The thrust chamber is provided with the heat insulation layer protection, effectively prevents that high temperature high pressure gas from causing the ablation to the casing, and reuse rate is high. The junction of the front combustion chamber heat insulation layer and the combustion chamber heat insulation layer is of a step structure, a certain sealing effect is achieved, the front part of the graphite spray pipe is directly connected with the combustion chamber heat insulation layer, and the effect of the rear combustion chamber heat insulation layer can be achieved.
7. The front end cover of the thrust chamber, the combustion chamber shell and the spray pipe shell can be separately processed, and are connected through threads, so that the thrust chamber is easy to manufacture; by changing the graphite spray pipes with different throat diameters, different combustion chamber pressures can be obtained, so that various engine working conditions can be met.
8. The injector of the thrust chamber adopts a direct current-centrifugal combined injector, can generate stronger rotational flow and has longer injection distance, and is beneficial to improving the combustion efficiency of the engine.
Drawings
FIG. 1 is a general schematic of a variable flow solid-liquid hybrid engine of the present invention.
Fig. 2 is a schematic view of the structure of the oxidizer tank in fig. 1.
Fig. 3 is a schematic view of the adjustable cavitation venturi structure of fig. 1.
Fig. 4 is a schematic view of the three-dimensional structure of the adjustable cavitation venturi of fig. 1.
Fig. 5 is a schematic view of the thrust chamber of fig. 1.
Fig. 6 is an enlarged view at I of fig. 2.
Fig. 7 is an enlarged view at ii of fig. 3.
Fig. 8 is a cross-sectional view and a left side view of a cavitation venturi.
Fig. 9 is a cross-sectional view and a left side view of an adjustable cavitation venturi housing.
Fig. 10 is a cross-sectional view and a left side view of a venturi compression screw.
Fig. 11 is a cross-sectional view and a left side view of the needle cone.
Fig. 12 is a cross-sectional view and a left side view of the fixing flange.
Fig. 13 is a cross-sectional and right side view of the injector.
Fig. 14 is a cross-sectional and left side view of the ignition seal cone.
Reference numerals illustrate: 1-an oxidant tank; 101-a pressurizing joint; 102-a tank upper housing; 103-flange bolts; 104-a tank upper flange; 105-flange sealing rings; 106, a lower flange of the storage tank; 107-flat gasket; 108-flange nuts; 109-a tank lower housing; 110-a supply connection;
2-an adjustable cavitation venturi; 201-a stepper motor; 202-fixing a flange plate; 203-adjusting a screw rod; 204-venturi press screw; 205-a first venturi sealing ring; 206-venturi inlet fitting; 207-an adjustable cavitation venturi housing; 208-a second venturi sealing ring; 209-cavitation venturi; 210-high flexibility cable; 211-adjusting nuts; 212-limiting rings; 213-guide ring; 214-venturi press screw sealing ring; 215-needle cone;
3-a thrust chamber; 301-igniting and pressing the screw; 302-ignition sealing cone; 303-an ignition seat; 304-a pre-combustor insulation; 305-a combustion chamber housing; 306-a combustion chamber insulation; 307-fuel cartridge; 308-a spray pipe sealing ring; 309-a spout housing; 310-graphite spray pipe; 311-graphite gasket; 312-front end cap; 313-injector; 314-thrust chamber inlet fitting;
4-a first pipeline; 5-controlling a valve; 6-a second pipeline.
Detailed Description
The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1, the invention mainly comprises six parts of an oxidant storage tank 1, an adjustable cavitation venturi tube 2, a thrust chamber 3, a first pipeline 4, a control valve 5 and a second pipeline 6.
The oxidant storage tank 1 is in threaded connection with the first pipeline 4 through the supply joint 110, the first pipeline 4 is provided with a control valve 5 for controlling the on-off of the oxidant, and the other end of the first pipeline 4 is in threaded connection with the venturi inlet joint 206, so that the oxidant can flow into the adjustable cavitation venturi 2. The second conduit 6 is then threaded at one end to the cavitation venturi 209 and at the other end to the thrust chamber inlet fitting 314, whereby the oxidant may flow into the thrust chamber 3.
The oxidant storage tank 1 is a place for storing the oxidant and can be divided into an upper part and a lower part, the main body of the upper part is a hemispherical storage tank upper shell 102, a pressurizing connector 101 is welded at the top of the upper part and is used for connecting a pipeline for pressurizing gas to flow, a storage tank upper flange 104 is welded at the lower part of the upper part, and 12 holes are uniformly distributed on the upper flange and are used for being connected with the lower part through bolts. The main body of the lower part of the storage tank is a hemispherical lower shell 109 of the storage tank, a supply joint 110 is welded at the bottom and used for supplying the oxidant, a lower flange 106 of the storage tank is welded at the upper part, 12 holes are uniformly distributed on the lower flange, and the upper part and the lower part can be connected through a flange bolt 103, a flat gasket 107 and a flange nut 108. Meanwhile, the upper flange 104 of the storage tank is provided with a circular boss, the corresponding position of the lower flange 104 of the storage tank is provided with a circular groove, and the middle of the upper flange is provided with a flange sealing ring 105, namely, the upper flange is sealed by a mortise type structure, so that high-pressure sealing can be realized.
The adjustable cavitation venturi tube 2 is a key component for flow regulation, and the principle is that the rotation of a motor is converted into the axial movement of a needle cone 215 through a ball screw structure in a stepping motor 201, and the motor is connected with a driver through a high-flexibility cable 210, so that the size of a throat gap of the cavitation venturi tube 209 can be changed, and the variable flow is realized. A venturi inlet fitting 206 is welded to the adjustable cavitation venturi housing 207 for connection to the first conduit 4. The assembly process is as follows: the venturi pressure screw 204 is connected with the adjustable cavitation venturi housing 207 through threads, the center of the venturi pressure screw 204 is penetrated, the size is slightly larger than the diameter of the needle cone 215, the reciprocating motion is convenient, three grooves are formed in the venturi pressure screw, the front two parts are used for installing the guide ring 213, abrasion of the needle cone 215 is reduced, and the back one part is used for placing the first venturi sealing ring 205 to seal the needle cone 215. The front part is also provided with a circular groove, the adjustable cavitation venturi housing 207 at the corresponding position is provided with a circular boss, and the adjustable cavitation venturi housing 207 is sealed by placing a venturi press screw sealing ring 214 in the concave-convex surface. Then the front part of the stepping motor 201 is connected with a needle cone 215 through threads, a limiting ring 212 is sleeved on the needle cone 215, screw rods extending out of the motor are connected to 4 holes in the horizontal direction and the vertical direction of the fixed flange 202 through nuts, and the needle cone 215 is inserted into the venturi press screw 204. The fixed flange 202 and the adjustable cavitation venturi housing 207 are provided with four through holes at four corners of a square, and are connected through 4 adjusting screw rods 203 and 16 adjusting nuts 211, so that the needle cone 215 reaches an initial position. Finally, a second venturi sealing ring 208 is placed in the step surface of the front center of the adjustable cavitation venturi housing 207, the cavitation venturi 209 is connected with the adjustable cavitation venturi housing 207 through threads, and the adjustable cavitation venturi 2 is assembled. At a total pressure of 7MPa, the oxidant flow rate may range from 2.76g/s to 220g/s when the full stroke of the needle cone 215 is 9.2 mm.
Referring to fig. 8, the two ends of the cavitation venturi 209 are respectively connected with the adjustable cavitation venturi housing 206 and the pipeline through threads, the part from the inner inlet of the central hole to the throat diameter is in a convergent structure, and the part from the throat diameter to the outlet is in an expanded structure; the general range of convergence angle at the inlet is 40-60 deg., the range of divergence angle at the outlet is 6-8 deg., the embodiment takes the convergence angle and divergence angle as 50 deg. and 6 deg., respectively. The throat diameter is generally determined by the flow rate of the oxidant, the flow coefficient, the stagnation pressure of the oxidant, the density of the oxidant and the saturated vapor pressure, and different throat diameters can be designed according to different oxidant supply conditions. The throat diameter is 2mm, the throat transition fillet is 1mm, the axial length of the straight line segment of the throat is (0.25-1) times the throat diameter, and the throat diameter is 2mm. The axial length of the convergent section is calculated and determined by the diameter of the inlet, the convergence angle and the throat diameter, the axial length of the divergent section is calculated and determined by the diameter of the outlet, the divergence angle and the throat diameter, the inlet and outlet diameters are generally the same and are consistent with the pipeline, for example, when the inner diameter of the pipeline is 10mm, the inlet and outlet diameters of the cavitation venturi are also 10mm, the convergent section is 8.57mm, the divergent section is 76.32mm, and the total length is 86.89mm.
Referring to fig. 11, the taper angle of the taper 215 is 10 °, the diameter of the constant diameter cylindrical portion is 8mm, and the axial length of the taper angle portion is 45.72mm.
The thrust chamber 3 is a place where the propellant burns and generates thrust, and the invention adopts a three-section scheme of the front end cover 312, the combustion chamber shell 305 and the spray pipe shell 309, which are all connected through threads, and the structure is easy to process and manufacture. The front end cap 312 is an oval head, the center of the head is provided with a hole, the outside is welded with a thrust chamber inlet connector 314, and the oxidant can flow into the thrust chamber 3. The injector 313 is welded on the inner side of the opening, and an injection array is formed by 8 uniformly distributed tangential holes, 4 uniformly distributed straight flow holes and a central straight flow hole together, so that the oxidant is atomized and evaporated. The front end cover 312 is also welded with an ignition seat 303 which is connected with the ignition press screw 301 through threads, and an ignition sealing cone 302 is placed in a conical hole between the two, and two holes are formed on the ignition sealing cone for passing through an ignition wire. A graphite gasket 311 is placed between the end surface of the front end cover 312, which is matched with the combustion chamber shell 305, and a groove is formed in the front part of the spray pipe shell 309 for placing a spray pipe sealing ring 308 so as to realize sealing with the combustion chamber shell 305. The assembly process is as follows: firstly, a front combustion chamber heat insulation layer 304 is arranged on the inner side of a front end cover 312 with all parts welded, a graphite gasket 311 is placed on the inner side end surface, a combustion chamber shell 305 is screwed in, then a fuel grain 307 which is closely cast on the combustion chamber heat insulation layer 306 is placed, finally a graphite spray pipe 310 is placed in a spray pipe shell 309 provided with a spray pipe sealing ring 308, and the graphite spray pipe is connected with the combustion chamber shell 305 through threads, so that the assembly of a thrust chamber 3 can be completed.
The working process of the variable flow solid-liquid hybrid engine is as follows: after the pressurized gas flows into the oxidizer storage tank 1, the control valve 5 on the first pipeline 4 is opened, the oxidizer flows out from the supply joint 110 under the extrusion action of the pressurized gas, passes through the first pipeline 4, enters the passage inside the adjustable cavitation venturi housing 207 from the venturi inlet joint 206, and flows out from the cavitation venturi 209 along the direction of the needle cone 215, and at the moment, the position of the needle cone 215 determines the initial flow. The oxidant flows into the thrust chamber 3 from the thrust chamber inlet connector 314 through the second pipeline 6, the oxidant rapidly completes the processes of atomization, mixing, evaporation and the like after passing through the injector 313, meanwhile, the ignition head is ignited by the ignition wire inserted from the ignition pressure screw 301, the fuel grain 307 is instantaneously ignited, and the generated fuel gas is expanded and accelerated through the graphite spray pipe 310 and then converted into heat energy and kinetic energy, so that the engine generates thrust. At this time, the motor driver can remotely control the stepper motor 201 to act to push the needle cone 215 to move according to the designed working condition, the reciprocating travel of the needle cone 215 changes the throat diameter of the cavitation venturi 209, the flow of the oxidant supply is further changed, and the thrust adjustment of the solid-liquid hybrid engine is realized.
Example 1:
the fuel of the solid-liquid mixed engine is paraffin, the fuel type is tubular, the fuel type is filled into the thrust chamber in a free filling mode, the oxidant is nitrous oxide, the nitrous oxide is filled into the oxidant storage tank in advance, and the pressurized gas is nitrogen. The flow is regulated by the movement of the adjustable cavitation venturi needle cone, the flow of the oxidant is changed from small to large and is divided into 3 stages, the flow of each stage is respectively 30g/s, 50g/s and 80g/s, the initial position of the specified needle cone is a zero position, the positions of the corresponding needle cone are respectively 0mm, 1mm and 2mm, the supply time is 5s, the working condition conversion time is 1s, the movement speed of the needle cone is 1mm/s, and the variable flow time is required to be 17s.
After all parts of the solid-liquid mixed engine are assembled, a control valve on a first pipeline is opened, under the extrusion action of pressurized gas, an oxidant flows through an adjustable cavitation venturi tube to be limited, then reaches an inlet of a thrust chamber through two pipelines, is sprayed into a combustion chamber through an injector in a swirling flow manner, atomization and evaporation are rapidly completed, meanwhile, an ignition wire on an ignition seat on the thrust chamber is electrified to ignite an ignition powder, paraffin powder is ignited, and fuel gas is expanded and accelerated through a spray pipe to generate thrust. At this time, the flow of the oxidant is 30g/s, after the engine works for 5s, the needle cone moves towards the direction far away from the throat under the driving action of the stepping motor, the flow is changed to 50g/s after 1s, after the engine continues to work for 5s, the needle cone continues to move towards the direction far away from the throat, the flow is changed to 80g/s after 1s, after the engine works for 5s, the control valve on the first pipeline is closed, the oxidant stops supplying, the thrust chamber is flameout, and the engine completes the working condition of changing the flow from small to large.
Example 2:
the fuel of the solid-liquid mixed engine selects HTPB (hydroxyl-terminated polybutadiene), the fuel type is star-shaped, the fuel type is filled into a thrust chamber in a free filling mode, the oxidant is nitrous oxide, the oxidant is filled into an oxidant storage tank in advance, and the pressurized gas is nitrogen. The flow is regulated by the movement of the adjustable cavitation venturi needle cone, the flow of the oxidant is changed from large to small and then is changed into 3 stages, the flow in each stage is respectively 50g/s, 30g/s and 80g/s, the initial position of the specified needle cone is a zero position, the positions of the corresponding needle cone are respectively 0mm, -1mm and 1mm, the supply time is 3s, the working condition conversion time is 1s, the movement speed of the needle cone is 1mm/s when the flow is changed from large to small, the movement speed of the needle cone is 2mm/s when the flow is changed from small to large, and the flow conversion time is 11s.
After all parts of the solid-liquid mixed engine are assembled, a control valve on a first pipeline is opened, under the extrusion action of pressurized gas, an oxidant flows through an adjustable cavitation venturi tube to be limited, then reaches an inlet of a thrust chamber through a second pipeline, is sprayed into a combustion chamber through an injector in a swirl way, atomization and evaporation are rapidly completed, meanwhile, an ignition wire on an ignition seat on the thrust chamber is electrified to ignite an ignition powder, HTPB powder is ignited, and the gas is expanded and accelerated through a spray pipe to generate thrust. At this time, the flow of the oxidant is 50g/s, after the engine works for 3s, the needle cone moves towards the direction close to the throat under the driving action of the stepping motor, 1s later moves to the position of minus 1mm, the flow becomes 30g/s at this time, after the engine continues to work for 3s, the needle cone continues to move towards the direction far away from the throat, 1s later moves to the position of 1mm, the flow becomes 80g/s at this time, after the engine works for 3s, the control valve on the first pipeline is closed, the oxidant stops supplying, the thrust chamber is flamed out, and the engine completes the changing working condition that the flow is changed from big to small again.
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.
Claims (8)
1. The variable flow solid-liquid mixing engine comprises an oxidant storage tank, a thrust chamber and a control valve, wherein the oxidant storage tank is communicated with the thrust chamber through a pipeline to realize the input of an oxidant into the thrust chamber, and the control valve arranged on the pipeline controls the on-off of the oxidant; the method is characterized in that: the adjustable cavitation venturi is connected between the control valve and the thrust chamber through a pipeline;
the adjustable cavitation venturi comprises a stepping motor, a fixed flange, a venturi pressure screw, a venturi inlet joint, an adjustable cavitation venturi shell, a cavitation venturi and a needle cone; the stepping motor is coaxially arranged on the fixed flange, and an output shaft of the stepping motor is coaxially connected with the needle cone; the adjustable cavitation venturi casing is of a columnar structure, one end of the columnar structure is provided with a flange plate, a stepped through hole is formed along the central line, a venturi press screw is arranged in the hole at one end of the flange plate through threads, a cavitation venturi is arranged at the other end of the columnar structure through threads, and an outlet of the cavitation venturi is communicated with an inlet of the thrust chamber through a pipeline and is used as an output channel of an oxidant; the side wall of the adjustable cavitation venturi tube shell is provided with a vent hole communicated with the stepped through hole in the radial direction, and the outlet of the vent hole is communicated with the oxidant storage tank through a venturi tube inlet joint and a pipeline to be used as an input channel of the oxidant; the needle cone coaxially and sequentially passes through the venturi press screw and the central through hole of the adjustable cavitation venturi shell, then is inserted into the throat diameter of the cavitation venturi central hole, the needle cone is driven by the stepping motor to reciprocate, the gap between the needle cone and the throat diameter of the cavitation venturi is changed, the flow of oxidant supply is further changed, and thrust adjustment is realized;
the inner peripheral surface in the venturi press screw is coaxially provided with a guide ring, so that the needle cone is prevented from directly contacting with the inner surface of the venturi press screw, and abrasion is reduced; the venturi pressure screw and the adjustable cavitation venturi shell are sealed through a venturi pressure screw sealing ring, and the adjustable cavitation venturi shell is sealed through a venturi sealing ring;
the engine also comprises adjusting screw rods and adjusting nuts, one ends of the four adjusting screw rods are respectively arranged on the fixed flange plate along the circumferential direction through the adjusting nuts, and the other ends of the four adjusting screw rods are respectively arranged on the flange plate of the adjustable cavitation venturi tube shell along the circumferential direction through the adjusting nuts; and the axial directions of the four adjusting screw rods are parallel to the output shaft of the stepping motor, and the distance between the fixed flange plate and the flange plate of the adjustable cavitation venturi tube shell is adjusted by screwing the adjusting nuts, so that the distance between the stepping motor and the adjustable cavitation venturi tube shell is adjusted.
2. The variable flow rate solid-liquid hybrid engine according to claim 1, characterized in that: the oxidant storage tank is of a spherical structure and comprises a pressurizing joint, an upper storage tank shell, a lower storage tank shell and a supply joint; the upper shell and the lower shell of the storage tank are hemispherical shells with flange structures on the peripheral surfaces of ports, and are fastened into hollow spherical cavities through bolts and nuts; the top end of the upper shell of the storage tank is provided with a through hole which is fixedly connected with a pressurizing connector and is used for connecting high-pressure gas to pressurize; the bottom of the lower shell of the storage tank is provided with a through hole which is connected with a supply joint and used for conveying an oxidant to the thrust chamber.
3. The variable flow rate solid-liquid hybrid engine according to claim 2, characterized in that: the flange structure of the upper shell of the storage tank is an upper flange of the storage tank, the flange structure of the lower shell of the storage tank is a lower flange of the storage tank, the mounting surfaces of the upper flange of the storage tank and the lower flange of the storage tank are sealed by adopting a tongue-and-groove structure, and a flange sealing ring is placed in the groove.
4. The variable flow rate solid-liquid hybrid engine according to claim 1, characterized in that: the needle cone is connected with the output shaft of the stepping motor through threads, and is sleeved with a limiting ring which is arranged on the outer side of the venturi pressure screw and used for limiting axial displacement of the needle cone.
5. The variable flow rate solid-liquid hybrid engine according to claim 1, characterized in that: the two ends of the cavitation venturi are respectively connected with the adjustable cavitation venturi shell and the pipeline through threads, the part from the inner inlet of the central hole to the throat diameter is of a convergent structure, and the part from the throat diameter to the outlet is of an expansion structure; the convergence angle range is 40-60 degrees, and the divergence angle range is 6-8 degrees; the axial length of the equal diameter section of the throat part is 0.25-1 times of the throat diameter.
6. The variable flow rate solid-liquid hybrid engine according to claim 5, characterized in that: the convergence angle and the divergence angle are respectively 50 degrees and 6 degrees, the equal diameter sections of the throat diameter and the throat are 2mm, and the transition fillet of the throat is 1mm; the inlet and outlet diameters of the cavitation venturi tube are 10mm, the axial length of the converging section is 8.57mm, the axial length of the diverging section is 76.32mm, and the total length is 86.89mm.
7. The variable flow rate solid-liquid hybrid engine according to claim 1, characterized in that: the taper angle of the conical part of the needle cone is 10 degrees, and the axial length is 45.72mm; the diameter of the constant diameter cylindrical portion was 8mm.
8. The variable flow rate solid-liquid hybrid engine according to claim 1, characterized in that: the thrust chamber comprises an ignition press screw, an ignition sealing cone, an ignition seat, a front combustion chamber heat insulation layer, a combustion chamber shell, a combustion chamber heat insulation layer, a fuel grain, a spray pipe sealing ring, a spray pipe shell, a graphite spray pipe, a graphite gasket, a front end cover, an injector and a thrust chamber inlet joint, wherein the front end cover and the spray pipe shell are respectively and hermetically arranged at two ends of the combustion chamber shell; the center of the front end cover is provided with a through hole, a thrust chamber inlet joint and an injector are coaxially arranged, the thrust chamber inlet joint and the injector are communicated with the outlet end of the cavitation venturi through a pipeline, an ignition assembly is arranged on the wall surface of the front end cover, the ignition assembly comprises an ignition press screw, an ignition sealing cone and an ignition seat, the ignition press screw is in threaded connection with the ignition seat, and the ignition press screw is sealed through the conical ignition sealing cone; the front end cover is connected with the combustion chamber shell through threads and is sealed through a graphite gasket; a front combustion chamber heat insulation layer and a combustion chamber heat insulation layer are arranged in the combustion chamber shell, and fuel grains are poured into the combustion chamber heat insulation layer; the spray pipe shell is in threaded connection with the combustion chamber shell and is sealed by using a spray pipe sealing ring; the graphite spray pipe is arranged in the spray pipe shell.
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| CN113638823B (en) * | 2021-08-10 | 2022-06-17 | 北京理工大学 | Needle valve type flow-adjustable gas generator ground test device |
| CN114320667B (en) * | 2021-09-16 | 2023-06-20 | 西北工业大学 | Extrusion type oxidant supply solid-liquid mixed engine |
| CN114109655A (en) * | 2021-10-20 | 2022-03-01 | 余国平 | Variable thrust adjusting electromechanical servo mechanism of liquid rocket engine |
| CN115726902B (en) * | 2022-11-21 | 2024-05-14 | 北京中科宇航技术有限公司 | Solid rocket engine working for long time and throat bolt device thereof |
| CN116221777A (en) * | 2023-02-20 | 2023-06-06 | 中国船舶重工集团公司第七0三研究所 | Combustion chamber head structure with adjustable runner |
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