CN112065605A - Variable thrust pump pressure type liquid rocket engine system - Google Patents
Variable thrust pump pressure type liquid rocket engine system Download PDFInfo
- Publication number
- CN112065605A CN112065605A CN202011046139.1A CN202011046139A CN112065605A CN 112065605 A CN112065605 A CN 112065605A CN 202011046139 A CN202011046139 A CN 202011046139A CN 112065605 A CN112065605 A CN 112065605A
- Authority
- CN
- China
- Prior art keywords
- valve body
- pump
- section
- venturi
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
- F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of aerospace power, and particularly relates to a variable thrust pump pressure type liquid rocket engine system. The fuel pump of the system is provided with an input end and two output ends, the input end of the fuel pump is connected with a fuel source, the oxidant pump is provided with an input end and two output ends, the input end of the oxidant pump is connected with an oxidant source, a thrust chamber is respectively connected with one output end of the fuel pump and one output end of the oxidant pump, a fuel gas generator is respectively connected with the other output end of the fuel pump and the other output end of the oxidant pump, a first adjustable cavitation venturi is arranged between the fuel gas generator and the other output end of the fuel pump, and a second adjustable cavitation venturi is arranged between the fuel gas generator and the other output end of the oxidant pump.
Description
Technical Field
The invention belongs to the technical field of aerospace power, and particularly relates to a variable thrust pump pressure type liquid rocket engine system.
Background
The liquid rocket engine is a main power device of an aerospace carrier rocket and has the characteristics of large thrust, high specific impulse, complex system structure and the like. In order to simplify the system constitution, reduce the development difficulty and improve the reliability, the traditional liquid rocket engine is usually designed to work only at rated thrust and has no capability of adjusting the thrust in real time in the working engineering.
With the increasing number and types of space loads and the increasing requirements on the task adaptability of the carrier rocket, the multi-rail and multi-star launching of one rocket gradually becomes the main working mode of the carrier rocket. On the other hand, the traditional disposable rocket is high in cost and gradually cannot meet the requirements of large-scale and low-cost launching of commercial aerospace, and the recovery and the repeated use after launching become the key direction of the development of the current carrier rocket.
The rocket engine is required to have the capability of real-time thrust adjustment whether the rocket is recovered or the load is put into orbit.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a variable thrust pump pressure type liquid rocket engine system, so that a rocket engine has the capability of real-time thrust adjustment.
The technical scheme of the invention is as follows:
a variable thrust pump pressure liquid rocket engine system, the system comprising:
a fuel pump having an input and two outputs, the input of the fuel pump being connected to a source of fuel;
an oxidant pump having an input and two outputs, the input of the oxidant pump being connected to an oxidant source;
a thrust chamber connected to an output of the fuel pump and an output of the oxidizer pump, respectively;
a fuel gas generator connected to the other output of the fuel pump and the other output of the oxidant pump, respectively;
a first adjustable cavitation venturi disposed between the gas generator and another output of the fuel pump;
a second adjustable cavitation venturi disposed between the gas generator and another output of the oxidant pump;
a turbine coupled to the gas generator.
Further, the turbine is also connected to the fuel pump and the oxidizer pump in sequence.
Further, a first control valve is provided between the thrust chamber and one output end of the fuel pump;
a second control valve is disposed between the thrust chamber and an output of the oxidant pump.
Further, a third control valve is arranged between the gas generator and the first adjustable cavitation venturi;
a fourth control valve is arranged between the fuel gas generator and the second adjustable cavitation venturi.
Further, the first adjustable cavitation venturi and the first adjustable cavitation venturi each include:
a first valve body;
the fixed end of the driving motor is fixedly arranged on the first valve body, and an output shaft of the driving motor can do telescopic motion along the axial direction of the first valve body;
the valve comprises a first valve body, a second valve body and a valve body, wherein the first valve body is provided with a first end and a second end which are opposite to each other;
the valve rod is sequentially provided with a first section, a second section and a third section along the axial direction, the first section of the valve rod is connected with an output shaft of the driving motor, the second section of the valve rod is cylindrical, the second section of the valve rod penetrates through the through hole in a clearance fit manner, the third section of the valve rod is a cone, and the diameter of the cone is gradually reduced from the second section to the third section;
the third valve body is arranged at the second end of the second valve body, a venturi is arranged in the third valve body, the inlet is communicated with the venturi, the venturi is provided with a contraction section, a throat part and an expansion section, the contraction section of the venturi is close to the second valve body, the throat part of the venturi is matched with the diameter of the second section of the valve rod, and the second section and the third section of the valve rod can be inserted into the venturi.
Further, the throat of the venturi is cylindrical.
Further, a cavity is arranged in the first valve body, one end of the cavity, facing the second valve body, is open, the side wall of the cavity is connected to the first end of the second valve body, and the driving motor is fixedly arranged in the cavity.
Still further, the valve further comprises a heating assembly for heating the first valve body;
a thermal insulation pad is disposed between the sidewall of the cavity and the first end of the second valve body.
Further, a groove is formed at the end of the first section of the valve rod, and an output shaft of the driving motor is detachably inserted into the groove;
and the output shaft of the driving motor is sleeved with a heat insulation sleeve.
Further, a mounting hole is formed in the second end of the second valve body;
the third valve body is inserted into the mounting hole in an interference fit mode, and the invention has the beneficial effects that:
when the variable thrust pump pressure type liquid rocket engine system provided by the invention is used, fuel enters the engine and is pressurized by the fuel pump, the pressurized fuel is divided into two paths, one path of the pressurized fuel enters the thrust chamber to participate in combustion, and the other path of the pressurized fuel enters the fuel generator to participate in combustion through the first adjustable cavitation venturi tube; after the oxidant enters the engine, the oxidant is firstly pressurized by the oxidant pump, the pressurized oxidant is divided into two paths, one path of the oxidant enters the thrust chamber to participate in combustion to generate thrust, the other path of the oxidant enters the fuel gas generator to participate in combustion after passing through the second adjustable cavitation venturi tube, high-pressure high-temperature fuel gas generated by reaction of the fuel and the oxidant in the thrust chamber is sprayed out, and the high-temperature fuel gas generated by the fuel gas generator drives the turbine to generate thrust.
When the thrust needs to be adjusted in the working process of the engine, the flow rates of fuel and oxidant entering the gas generator are changed by adjusting the throttling areas of the first adjustable cavitation venturi and the second adjustable cavitation venturi, namely the flow rate of a gas working medium of the turbine is changed, so that the input power of the turbine is changed, and the adjustment of the thrust of the engine is further realized to adapt to the recovery of a rocket and the entry of a load.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic diagram of an adjustable cavitation venturi according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a variable thrust pump pressure type liquid rocket engine system according to an embodiment of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Firstly, the embodiment of the invention discloses an adjustable cavitation venturi.
Fig. 1 is a schematic structural diagram of an adjustable cavitation venturi according to an embodiment of the present invention, which is combined with fig. 1, and includes a first valve body 1, a driving motor 8, a second valve body 3, a valve stem 6, and a third valve body 7.
Referring to fig. 1, in the embodiment of the present invention, a fixed end of the driving motor 8 is fixedly disposed on the first valve body 1, and an output shaft of the driving motor 8 can perform a telescopic motion along an axial direction of the first valve body 1.
Referring to fig. 1, a second valve body 3 according to an embodiment of the present invention has a first end and a second end opposite to each other, the first valve body 1 is mounted on the first end of the second valve body 3, a through hole is formed in the second valve body 3, the through hole is arranged to penetrate in an axial direction of the second valve body 3, an inlet 9 is formed in a circumferential surface of the second valve body 3, and fluid can flow into the second valve body 3 from the inlet 9.
Referring to fig. 1, in this embodiment, the valve rod 6 is sequentially provided with a first section, a second section and a third section along the axial direction thereof, and the first section of the valve rod 6 is connected with the output shaft of the driving motor 8, that is, the valve rod 6 can be driven to move under the driving of the driving motor 8. In the embodiment of the invention, the second section of the valve rod 6 is cylindrical, the second section of the valve rod 6 penetrates through the through hole in a clearance fit manner, a sealing ring can be arranged between the second section of the valve rod 6 and the through hole, when the valve rod 6 moves in the through hole, fluid flowing from the inlet 9 can be prevented from flowing into the first valve body 1, the third section of the valve rod 6 is a cone, and the diameter of the cone is gradually reduced from the second section to the third section.
The third valve body 7 of the embodiment of the present invention is installed on the second end of the second valve body 3, a venturi 10 is provided in the third valve body 7, the inlet 9 is communicated with the venturi 10, so that the fluid flowing into the second valve body 3 from the inlet 9 can be discharged through the venturi 10, the venturi 10 has a contraction section, a throat section and an expansion section, the contraction section of the venturi 10 is close to the second valve body 3, the throat section of the venturi 10 is matched with the diameter of the second section of the valve stem 6, and the second section and the third section of the valve stem 6 can be inserted into the venturi 10.
When the flow of the input fluid is adjusted by the adjustable cavitation venturi provided by the embodiment of the present invention, the fluid flows into the venturi 10 from the inlet 9 of the second valve body 3 and is input, the valve rod 6 is driven to move in the venturi 10 by controlling the extension and contraction of the output shaft of the driving motor 1, when the valve rod 6 is in the initial state, the valve rod 6 does not enter the venturi 10, the flow of the fluid is maximum, because the third section of the valve rod 10 is a cone, the diameter of the cone is gradually reduced from the second section to the third section, when the third section of the valve rod 10 moves at the throat of the venturi 10, the gap between the third section of the valve rod 6 and the throat of the venturi 10 is changed, thereby the flow can be controlled, when the second section of the valve rod 6 moves to the throat of the venturi 10, because the throat of the venturi 10 is matched with the diameter of the second section of the valve rod 6, no fluid is discharged from the venturi 10 and the flow of fluid is minimal.
Referring to fig. 1, in the embodiment of the present invention, a cavity is formed in the first valve body 1, one end of the cavity facing the second valve body 3 is open, a side wall of the cavity is connected to the first end of the second valve body 3, so as to mount the first valve body 1 on one end of the second valve body 3, and the driving motor 8 is fixedly disposed in the cavity.
In particular, in an embodiment of the present invention, the side wall of the cavity may be connected to the first end of the second valve body 3 by means of bolts.
The adjustable cavitation venturi tube provided by the embodiment of the invention can also comprise a heating component for heating the first valve body 1, and the heating component can be arranged to heat the first valve body 1 because the rocket engine works under an extremely cold working condition, so that the influence of a low-temperature medium on the working environment temperature of the driving motor 8 is avoided, and the working reliability of the motor can be effectively improved.
The heating element according to the embodiment of the present invention may be an electric heating wire or an electric heating sheet, which is not limited in this respect.
Further, referring to fig. 1, in the present embodiment, a thermal insulation pad 2 is disposed between a side wall of the cavity and the first end of the second valve body 3, so as to prevent the heated first valve body 1 from transferring heat to the second valve body 3, which affects the working temperature of the fluid.
The working environment temperature of the driving mechanism 1 is prevented from being influenced by low-temperature media, and the working reliability of the motor can be effectively improved.
In this embodiment, the material of the heat insulating pad 2 may be polyimide.
Referring to fig. 1, in the embodiment of the present invention, the end of the first segment of the valve stem 6 is provided with a groove 11, and the output shaft of the driving motor 8 is detachably inserted into the groove 11.
Further, the output shaft of the driving motor 8 can be connected to the groove 11 through the flaring pin 4, and the heat insulation sleeve 5 is sleeved on the output shaft of the driving motor 8, so that the valve body 6 can be prevented from being heated, and the heat insulation sleeve 5 can be prevented from being rubbed and scratched.
Similarly, the material of the heat insulation sleeve 5 of the embodiment of the present invention may also be polyimide.
In an embodiment of the present invention, a sealing ring may be disposed on the second section of the valve rod 6 to prevent fluid from leaking into the cavity in the first valve body 1 from between the second section of the valve rod 6 and the through hole in the second valve body 3.
In the embodiment of the invention, the end part of the third section of the valve rod 6 is arc-shaped, so that the end part of the third section of the valve rod 6 can be prevented from being damaged during assembly.
In the embodiment of the present invention, the throat of the venturi 10 is cylindrical, which can help to recover the pressure of the fluid and stabilize the flow rate.
In the embodiment of the present invention, a mounting hole is provided on the second end of the second valve body 3, and the third valve body 7 is inserted into the mounting hole in an interference fit manner, so as to achieve the assembly of the third valve body 7 on the second valve body 3.
Referring to fig. 1, in the embodiment of the present invention, a limiting ring 12 is disposed on the circumferential surface of the third valve body 3, and the limiting ring 12 is disposed closely to the second end of the second valve body 3, so as to improve the reliability of the assembly of the third valve body 7 on the second valve body 3.
Further, referring to fig. 1, in the embodiment of the present invention, the third valve body 3 may be integrally formed with the retainer ring 12, and the retainer ring may be bolted to the second end of the second valve body 3, so as to further improve the reliability of the assembly of the third valve body 7 on the second valve body 3.
The working process of the adjustable cavitation venturi of the embodiment of the invention is as follows:
the fluid flows in from the inlet 9 of the second valve body 3, enters the contraction section to be accelerated after reaching the venturi 10, and the static pressure is reduced due to the increase of the fluid speed as known from the Bernoulli principle. Cavitation occurs in the pipe when the static pressure drops below the local temperature saturation vapor pressure, where the flow is only affected by the inlet pressure, throat diameter and saturation vapor pressure of the medium, and not by the downstream outlet pressure. Based on the principle, the flow can be controlled by adjusting the throat flow area. After passing through the throat part, the fluid firstly passes through a small segment of straight line segment, so that the cavitation is ensured to be more sufficient, and the stability of the flow is improved. Finally, the static pressure is increased through the deceleration of the expansion section, and the evaporated fluid is condensed again and flows out from the outlet pipeline after being more than the saturated vapor pressure.
This embodiment provides power through driving motor to drive valve rod 6 and remove, accessible control center sends the instruction to driving motor, and control valve rod 6 displacement is certain distance, and valve rod 6 stretches into the third section of throat for coniform, and the displacement can lead to valve rod 6 to be located the change of the cross-sectional area of throat, and the clearance area of valve rod 6 and throat changes correspondingly, and this has just realized the control to throat flow area.
The adjustable cavitation venturi provided by the embodiment of the invention can realize the flow of fluid by controlling the movement of the valve rod through the driving motor, and has the advantages of simple structure, high precision and good practicability.
In addition, based on the adjustable cavitation venturi, the embodiment of the invention also provides a variable thrust pump pressure type liquid rocket engine system.
Fig. 2 is a schematic structural diagram of a variable thrust pump pressure type liquid rocket engine system according to an embodiment of the present invention, and in conjunction with fig. 2, the engine system according to an embodiment of the present invention includes a fuel pump 13, an oxidant pump 14, a thrust chamber 15, a gas generator 16, a first adjustable cavitation venturi 17, a second adjustable cavitation venturi 18, and a turbine 19.
Referring to fig. 2, the fuel pump 13 has an input terminal and two output terminals, the input terminal of the fuel pump 13 is connected to a fuel source, the oxidant pump 14 has an input terminal and two output terminals, the input terminal of the oxidant pump 14 is connected to an oxidant source, the thrust chambers 15 are respectively connected to one output terminal of the fuel pump 13 and one output terminal of the oxidant pump 14, the gas generator 16 is respectively connected to the other output terminal of the fuel pump 13 and the other output terminal of the oxidant pump 14, the first variable cavitation venturi 17 is disposed between the gas generator 16 and the other output terminal of the fuel pump 13, the second variable cavitation venturi 18 is disposed between the gas generator 16 and the other output terminal of the oxidant pump 14, and the turbine 19 is connected to the gas generator 16.
In the embodiment of the invention, the first adjustable cavitation venturi 17 and the second adjustable cavitation venturi 18 are both the adjustable cavitation venturi, the inlet of the first adjustable cavitation venturi 17 is connected with the other output end of the fuel pump 13, the expansion section of the first adjustable cavitation venturi 17 is connected with the fuel gas generator 16, the inlet of the second adjustable cavitation venturi 18 is connected with the other output end of the oxidant pump 14, and the expansion section of the second adjustable cavitation venturi 18 is connected with the thrust chamber 15.
When the variable thrust pump pressure type liquid rocket engine system provided by the embodiment of the invention is used, fuel enters the engine and is pressurized by the fuel pump, the pressurized fuel is divided into two paths, one path of the pressurized fuel enters the thrust chamber to participate in combustion, and the other path of the pressurized fuel enters the fuel generator to participate in combustion through the first adjustable cavitation venturi tube; after the oxidant enters the engine, the oxidant is firstly pressurized by the oxidant pump, the pressurized oxidant is divided into two paths, one path of the oxidant enters the thrust chamber to participate in combustion to generate thrust, the other path of the oxidant enters the fuel gas generator to participate in combustion after passing through the second adjustable cavitation venturi tube, high-pressure high-temperature fuel gas generated by reaction of the fuel and the oxidant in the thrust chamber is sprayed out, and the high-temperature fuel gas generated by the fuel gas generator drives the turbine to generate thrust.
When the thrust needs to be adjusted in the working process of the engine, the flow rates of fuel and oxidant entering the gas generator are changed by adjusting the throttling areas of the first adjustable cavitation venturi and the second adjustable cavitation venturi, namely the flow rate of a gas working medium of the turbine is changed, so that the input power of the turbine is changed, and the adjustment of the thrust of the engine is further realized to adapt to the recovery of a rocket and the entry of a load.
Further, referring to fig. 2, the turbine 19 according to the embodiment of the present invention is further connected to the fuel pump 13 and the oxidizer pump 14 in turn, so as to drive the fuel pump 13 and the oxidizer pump 14 to operate.
Referring to fig. 2, in the embodiment of the present invention, a first control valve 20 is provided between the thrust chamber 15 and an output end of the fuel pump 13 to control the on/off of the two; a second control valve 21 is arranged between the thrust chamber 15 and one output end of the oxidant pump 14 to control the on-off between the thrust chamber and the oxidant pump; similarly, a third control valve 22 is provided between the gas generator 16 and the first variable cavitation venturi 17 to control the on/off between them, and a fourth control valve 23 is provided between the gas generator 16 and the second variable cavitation venturi 18 to control the on/off between them.
In conclusion, the variable thrust pump pressure type liquid rocket engine system based on the adjustable cavitation venturi can adjust the fuel flow and the oxidant flow of the fuel generator, further adjust the flow of the fuel pump and the oxidant pump, namely adjust the total flow of the engine, thereby achieving the purpose of adjusting the thrust of the engine and having good practical value.
The following embodiments are provided for the purpose of illustrating the present invention and are not to be construed as limiting the present invention in any way, and it will be apparent to those skilled in the art that the technical features of the present invention can be modified or changed in some ways without departing from the scope of the present invention.
Claims (10)
1. A variable thrust pump pressure liquid rocket engine system, the system comprising:
a fuel pump having an input and two outputs, the input of the fuel pump being connected to a source of fuel;
an oxidant pump having an input and two outputs, the input of the oxidant pump being connected to an oxidant source;
a thrust chamber connected to an output of the fuel pump and an output of the oxidizer pump, respectively;
a fuel gas generator connected to the other output of the fuel pump and the other output of the oxidant pump, respectively;
a first adjustable cavitation venturi disposed between the gas generator and another output of the fuel pump;
a second adjustable cavitation venturi disposed between said gas generator and another output of said oxidant pump;
a turbine coupled to the gas generator.
2. The variable thrust pump pressure liquid rocket engine system of claim 1 wherein said turbine is further connected in series to said fuel pump and said oxidizer pump.
3. A variable thrust pump pressure liquid rocket engine system according to claim 1 wherein a first control valve is disposed between said thrust chamber and an output of said fuel pump;
a second control valve is disposed between the thrust chamber and an output of the oxidant pump.
4. The variable thrust pump pressure liquid rocket engine system of claim 1 wherein a third control valve is disposed between said gas generator and said first adjustable cavitation venturi;
a fourth control valve is arranged between the fuel gas generator and the second adjustable cavitation venturi.
5. A variable thrust pump pressure liquid rocket engine system according to any one of claims 1-4, wherein said first adjustable cavitation venturi and said first adjustable cavitation venturi each comprise:
a first valve body;
the fixed end of the driving motor is fixedly arranged on the first valve body, and an output shaft of the driving motor can do telescopic motion along the axial direction of the first valve body;
the valve comprises a first valve body, a second valve body and a valve body, wherein the first valve body is provided with a first end and a second end which are opposite to each other;
the valve rod is sequentially provided with a first section, a second section and a third section along the axial direction, the first section of the valve rod is connected with an output shaft of the driving motor, the second section of the valve rod is cylindrical, the second section of the valve rod penetrates through the through hole in a clearance fit manner, the third section of the valve rod is a cone, and the diameter of the cone is gradually reduced from the second section to the third section;
the third valve body is arranged at the second end of the second valve body, a venturi is arranged in the third valve body, the inlet is communicated with the venturi, the venturi is provided with a contraction section, a throat part and an expansion section, the contraction section of the venturi is close to the second valve body, the throat part of the venturi is matched with the diameter of the second section of the valve rod, and the second section and the third section of the valve rod can be inserted into the venturi.
6. The variable thrust pump pressure liquid rocket engine system of claim 5, wherein the throat of the venturi is cylindrical.
7. The variable thrust pump pressure rocket engine system according to claim 5 wherein a cavity is formed in said first valve body, said cavity being open at an end facing said second valve body, a sidewall of said cavity being attached to a first end of said second valve body, said drive motor being fixedly disposed in said cavity.
8. The variable thrust pump pressure liquid rocket engine system of claim 7, further comprising a heating assembly for heating the first valve body;
a thermal insulation pad is disposed between the sidewall of the cavity and the first end of the second valve body.
9. The variable thrust pump pressure liquid rocket engine system according to claim 5, wherein the end of the first section of the valve stem is provided with a groove, and the output shaft of the driving motor is detachably inserted into the groove;
and the output shaft of the driving motor is sleeved with a heat insulation sleeve.
10. The variable thrust pump pressure liquid rocket engine system of claim 5, wherein a mounting hole is provided on the second end of the second valve body;
the third valve body is inserted into the mounting hole with an interference fit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011046139.1A CN112065605A (en) | 2020-09-29 | 2020-09-29 | Variable thrust pump pressure type liquid rocket engine system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011046139.1A CN112065605A (en) | 2020-09-29 | 2020-09-29 | Variable thrust pump pressure type liquid rocket engine system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112065605A true CN112065605A (en) | 2020-12-11 |
Family
ID=73683853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011046139.1A Pending CN112065605A (en) | 2020-09-29 | 2020-09-29 | Variable thrust pump pressure type liquid rocket engine system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112065605A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113110622A (en) * | 2021-05-21 | 2021-07-13 | 北京航空航天大学 | Cavitation venturi |
| CN113175532A (en) * | 2021-04-28 | 2021-07-27 | 北京航空航天大学 | Adjustable cavitation venturi |
| CN114370355A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军63921部队 | Differential variable thrust method and device, electronic equipment and storage medium |
-
2020
- 2020-09-29 CN CN202011046139.1A patent/CN112065605A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113175532A (en) * | 2021-04-28 | 2021-07-27 | 北京航空航天大学 | Adjustable cavitation venturi |
| CN113110622A (en) * | 2021-05-21 | 2021-07-13 | 北京航空航天大学 | Cavitation venturi |
| CN113110622B (en) * | 2021-05-21 | 2022-07-22 | 北京航空航天大学 | Cavitation venturi |
| CN114370355A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军63921部队 | Differential variable thrust method and device, electronic equipment and storage medium |
| CN114370355B (en) * | 2022-01-07 | 2023-01-17 | 中国人民解放军63921部队 | Differential variable thrust method and device, electronic equipment and storage medium |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112065605A (en) | Variable thrust pump pressure type liquid rocket engine system | |
| US10072574B2 (en) | System and method for generating power using a supercritical fluid | |
| US2916873A (en) | Jet deflecting apparatus | |
| US3516254A (en) | Closed-loop rocket propellant cycle | |
| KR830001267B1 (en) | Axial thrust bearing device | |
| RU2642938C2 (en) | Rocket engine assembly | |
| CN213478522U (en) | Adjustable cavitation venturi | |
| US2482394A (en) | Gas turbine | |
| CN113404621A (en) | Solid-liquid mixed engine and method for Mars ascending aircraft | |
| US3915222A (en) | Compressible fluid contact heat exchanger | |
| EP1134382A2 (en) | A gas turbine | |
| CN212615072U (en) | Variable thrust pump pressure type liquid rocket engine system | |
| US8631638B2 (en) | Method, system and apparatus for providing water to a heat engine via a dammed water source | |
| CN116080881A (en) | Two-phase stamping underwater propulsion system containing non-condensable gas | |
| CN114046213B (en) | Open type liquid oxygen kerosene engine system and thrust adjusting method thereof | |
| US2541532A (en) | Gas turbine power plant | |
| US4608945A (en) | Apparatus for recirculating boiler fluid | |
| CN112211751A (en) | Adjustable cavitation venturi | |
| CN114165356A (en) | Miniature ramjet engine | |
| RU2378166C1 (en) | Multi-stage rocket carrier, method of its launching and nuclear rocket engine | |
| RU2379532C1 (en) | Nuclear gas turbine aircraft engine | |
| RU2378527C1 (en) | Controlled liquid-propellant rocket engine | |
| CN116044610B (en) | Double-expansion circulation liquid rocket engine system | |
| RU2554392C1 (en) | Hydrogen gas turbine engine | |
| RU2381152C1 (en) | Multi-stage carrier rocket with nuclear rocket engines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |