CN216767592U - Flow equalizer for liquid rocket engine - Google Patents
Flow equalizer for liquid rocket engine Download PDFInfo
- Publication number
- CN216767592U CN216767592U CN202220667376.8U CN202220667376U CN216767592U CN 216767592 U CN216767592 U CN 216767592U CN 202220667376 U CN202220667376 U CN 202220667376U CN 216767592 U CN216767592 U CN 216767592U
- Authority
- CN
- China
- Prior art keywords
- rocket engine
- liquid rocket
- flow equalizer
- equalizer
- fixed
- 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.)
- Active
Links
Images
Landscapes
- Branch Pipes, Bends, And The Like (AREA)
Abstract
The utility model discloses a flow equalizer for a liquid rocket engine, which comprises a main flow pipe, wherein the bottom of the main flow pipe is connected with a communicating seat, the top of the main flow pipe is connected with a flange joint, the outer side of the communicating seat is connected with a plurality of shunt pipes, the end positions of the shunt pipes are connected with arc joints, the end positions of the arc joints are connected with a connector, a steering adjusting mechanism is connected between the arc joints and the shunt pipes, a main channel is arranged inside the main flow pipe, a shunt channel is arranged inside the communicating seat, and the inner surface of the main flow pipe is connected with a separation mechanism; the flow equalizer for the liquid rocket engine can conveniently adjust the connecting direction of the output end of the flow equalizer, is convenient for the flow equalizer to convey propellants to thrust chambers in different directions, can stably equally divide a main flow pipe into a plurality of conveying channels, and can conveniently and accurately divide the flow equalizer.
Description
Technical Field
The utility model relates to the field of flow equalizers, in particular to a flow equalizer for a liquid rocket engine.
Background
The liquid rocket engine is a liquid propellant rocket engine, namely a chemical rocket propulsion system using liquid chemical substances as energy sources and working media, common liquid oxidants comprise liquid oxygen, dinitrogen tetroxide and the like, combustion agents comprise liquid hydrogen, unsymmetrical dimethylhydrazine, kerosene and the like, the liquid hydrogen, the unsymmetrical dimethylhydrazine, the kerosene and the like are stored in different storage tanks, and a flow equalizer for the liquid rocket engine is a common device for shunting the propellant to different thrust chambers; however, the existing flow equalizer for the liquid rocket engine has certain disadvantages to be improved when in use, firstly, the output end connection direction of the flow equalizer is inconvenient to adjust, the flow equalizer is inconvenient to convey propellant to thrust chambers in different directions, secondly, a main flow pipe can not be stably divided into a plurality of conveying channels, and the flow equalizer is inconvenient to accurately divide the flow.
SUMMERY OF THE UTILITY MODEL
The utility model mainly aims to provide a flow equalizer for a liquid rocket engine, which can effectively solve the technical problems in the background art.
In order to realize the purpose, the utility model adopts the technical scheme that:
the utility model provides a liquid rocket is flow equalizer for engine, includes the mainstream pipe, the bottom of mainstream pipe is connected with the intercommunication seat, and the top of mainstream pipe is connected with the flange joint, the outside of intercommunication seat is connected with a plurality of shunt tubes, and is a plurality of the end position of shunt tubes all is connected with the arc and connects, the end position that the arc connects is connected with the connector, and is connected with between arc joint and the shunt tubes and turns to adjustment mechanism, the main entrance has been seted up to the inside of mainstream pipe, the reposition of redundant personnel passageway has been seted up to the inside of intercommunication seat, the internal surface connection of mainstream pipe has the partition mechanism.
As a further scheme of the utility model, the steering adjusting mechanism comprises an adjusting disc, a fixed disc, a limiting ring, a limiting pin and a limiting groove, the adjusting disc is fixed at the end position of the arc-shaped joint, the fixed disc is fixed at the end position of the shunt tube, the limiting ring is arranged at the joint of the adjusting disc and the fixed disc, the limiting pin penetrates through the adjusting disc, and the limiting groove is uniformly formed in the fixed disc.
As a further scheme of the utility model, the adjusting disc is inserted into the limiting groove through the limiting pin and is fixedly connected with the fixing disc.
As a further aspect of the present invention, the partition mechanism includes a connecting seat, a cross isolation plate, a fixing ring, and a fixing pin, the connecting seat is fixed to an inner surface of the main flow pipe, the cross isolation plate is clamped inside the connecting seat, the fixing ring is disposed at an end of the connecting seat, the fixing pin penetrates through the fixing ring, and the end of the fixing pin is screwed into the connecting seat.
As a further scheme of the utility model, the fixing ring is fixedly connected with the connecting seat through a fixing pin.
As a further scheme of the utility model, the positions, close to the periphery, inside the communication seat are provided with mounting grooves matched with the flow dividing pipes, and the inner surfaces of the mounting grooves are tangent to the outer surfaces of the flow dividing pipes.
Compared with the prior art, the utility model has the following beneficial effects: through the steering adjusting mechanism who sets up, can conveniently adjust the output connection direction of current equalizer to can make things convenient for the current equalizer to carry the propellant to the thrust chamber of equidirectional not, through the partition mechanism who sets up, can be stable divide into a plurality of delivery channel with mainstream pipe etc. to can make things convenient for the current equalizer to carry out accurate reposition of redundant personnel.
Drawings
FIG. 1 is a schematic view of the overall structure of a flow equalizer for a liquid rocket engine according to the present invention;
FIG. 2 is a schematic view of the internal structure of a main flow pipe and a communicating seat of a flow equalizer for a liquid rocket engine according to the present invention;
FIG. 3 is a schematic structural diagram of a steering adjustment mechanism of a flow equalizer for a liquid rocket engine according to the present invention;
fig. 4 is a schematic structural diagram of a partition mechanism of a flow equalizer for a liquid rocket engine according to the present invention.
In the figure: 1. a main flow pipe; 2. a communication base; 3. a flange joint; 4. a shunt tube; 5. an arc-shaped joint; 6. a connector; 7. a steering adjustment mechanism; 701. an adjusting disk; 702. fixing the disc; 703. a limiting ring; 704. a spacing pin; 705. a limiting groove; 8. a main channel; 9. a flow dividing channel; 10. a separation mechanism; 1001. a connecting seat; 1002. a cross-shaped isolation plate; 1003. a stationary ring; 1004. and fixing the pin.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the utility model easy to understand, the utility model is further described with the specific embodiments.
As shown in fig. 1-4, a flow equalizer for a liquid rocket engine includes a main flow pipe 1, a communication base 2 is connected to the bottom of the main flow pipe 1, a flange joint 3 is connected to the top of the main flow pipe 1, a plurality of shunt tubes 4 are connected to the outer side of the communication base 2, arc joints 5 are connected to the end positions of the shunt tubes 4, a connector 6 is connected to the end position of the arc joint 5, a steering adjustment mechanism 7 is connected between the arc joint 5 and the shunt tubes 4, a main passage 8 is formed inside the main flow pipe 1, a shunt passage 9 is formed inside the communication base 2, and a separation mechanism 10 is connected to the inner surface of the main flow pipe 1;
in this embodiment, a steering adjustment mechanism 7 is provided for conveniently adjusting the output end connection direction of the current equalizer, the steering adjustment mechanism 7 includes an adjusting disk 701, a fixed disk 702, a limiting ring 703, a limiting pin 704 and a limiting groove 705, the adjusting disk 701 is fixed at the end position of the arc joint 5, the fixed disk 702 is fixed at the end position of the shunt tube 4, the limiting ring 703 is arranged at the connection position of the adjusting disk 701 and the fixed disk 702, the limiting pin 704 runs through the inside of the adjusting disk 701, the limiting groove 705 is uniformly arranged in the fixed disk 702, the steering adjustment mechanism 7 can conveniently adjust the output end connection direction of the current equalizer, and therefore the current equalizer can conveniently convey propellants to thrust chambers in different directions.
In this embodiment, in order to fix the adjusting disk 701 after rotation, the adjusting disk 701 is fixedly connected to the fixing disk 702 by inserting the limit pin 704 into the limit groove 705.
In this embodiment, in order to divide the main flow pipe 1 into a plurality of transfer passages equally stably, the partition mechanism 10 is provided, the partition mechanism 10 includes a connecting seat 1001, a cross partition plate 1002, a fixing ring 1003 and a fixing pin 1004, the connecting seat 1001 is fixed on the inner surface of the main flow pipe 1, the cross partition plate 1002 is clamped on the inner side of the connecting seat 1001, the fixing ring 1003 is disposed at the end position of the connecting seat 1001, the fixing pin 1004 penetrates through the inside of the fixing ring 1003, and the end of the fixing pin 1004 is screwed into the inside of the connecting seat 1001, the partition mechanism 10 can stably divide the main flow pipe 1 into a plurality of transfer passages equally, thereby facilitating the flow equalizer to perform accurate flow division.
In this embodiment, in order to improve the connection stability of the connection socket 1001, the fixing ring 1003 is fixedly connected with the connection socket 1001 by the fixing pin 1004, and the cross isolation plate 1002 can be prevented from displacement when the connection stability of the connection socket 1001 is improved.
In this embodiment, for the convenience shunt tubes 4 are connected with the seat of intercommunication 2, the inside of the seat of intercommunication 2 is close to all around the position all offer with shunt tubes 4 assorted mounting groove, the internal surface of mounting groove is tangent with shunt tubes 4's surface.
In addition, the utility model is a flow equalizer for a liquid rocket engine, when in use, a main flow pipe 1, a communicating seat 2 and a shunt pipe 4 form the main body part of the flow equalizer for the whole liquid rocket engine, the main flow pipe 1 is connected with a propellant chamber of a liquid rocket engine through a flange joint 3, the shunt pipe 4 is connected with a thrust chamber of the liquid rocket engine through an arc joint 5 and a connector 6, a fixed ring 1003 is fixed with a connecting seat 1001 through a fixed pin 1004, a cross partition plate 1002 equally divides the main flow pipe 1 into a plurality of conveying channels, through the even transport propellant of mainstream pipe 1, intercommunication seat 2 and shunt tubes 4 to thrust chamber, the adjusting disk 701 inserts spacing groove 705 through spacer pin 704 and fixed disk 702 and carries out the fixed after rotating, can conveniently adjust the output connection direction of current equalizer to can make things convenient for the current equalizer to carry the propellant to the thrust chamber of equidirectional not.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the utility model as claimed. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (6)
1. The utility model provides a flow equalizer for liquid rocket engine which characterized in that: including mainstream pipe (1), the bottom of mainstream pipe (1) is connected with intercommunication seat (2), and the top of mainstream pipe (1) is connected with flange joint (3), the outside of intercommunication seat (2) is connected with a plurality of shunt tubes (4), and is a plurality of the end position of shunt tubes (4) all is connected with arc joint (5), the end position of arc joint (5) is connected with connector (6), and is connected with between arc joint (5) and shunt tubes (4) and turns to adjustment mechanism (7), main entrance (8) have been seted up to the inside of mainstream pipe (1), reposition of redundant personnel passageway (9) have been seted up to the inside of intercommunication seat (2), the internal surface connection of mainstream pipe (1) has partition mechanism (10).
2. The flow equalizer for a liquid rocket engine according to claim 1, wherein: turn to adjustment mechanism (7) including adjusting disk (701), fixed disk (702), spacing collar (703), spacer pin (704) and spacing groove (705), end position that arc joint (5) was fixed in adjusting disk (701), the end position of shunt tubes (4) is fixed in fixed disk (702), spacing collar (703) set up the linking department at adjusting disk (701) and fixed disk (702), inside in adjusting disk (701) is run through in spacer pin (704), the inside at fixed disk (702) is evenly seted up in spacing groove (705).
3. The flow equalizer for a liquid rocket engine according to claim 2, wherein: the adjusting disc (701) is inserted into the limiting groove (705) through a limiting pin (704) and is fixedly connected with the fixed disc (702).
4. The flow equalizer for a liquid rocket engine according to claim 1, wherein: the partition mechanism (10) comprises a connecting seat (1001), a cross isolation plate (1002), a fixing ring (1003) and a fixing pin (1004), the connecting seat (1001) is fixed on the inner surface of the main flow pipe (1), the cross isolation plate (1002) is clamped on the inner side of the connecting seat (1001), the fixing ring (1003) is arranged at the end position of the connecting seat (1001), the fixing pin (1004) penetrates through the inner portion of the fixing ring (1003), and the end of the fixing pin (1004) is screwed into the inner portion of the connecting seat (1001).
5. The flow equalizer for a liquid rocket engine according to claim 4, wherein: the fixing ring (1003) is fixedly connected with the connecting seat (1001) through a fixing pin (1004).
6. The flow equalizer for a liquid rocket engine according to claim 1, wherein: the inside of intercommunication seat (2) is close to all around the position all seted up with shunt tubes (4) assorted mounting groove, and the internal surface of mounting groove is tangent with the surface of shunt tubes (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220667376.8U CN216767592U (en) | 2022-03-25 | 2022-03-25 | Flow equalizer for liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220667376.8U CN216767592U (en) | 2022-03-25 | 2022-03-25 | Flow equalizer for liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216767592U true CN216767592U (en) | 2022-06-17 |
Family
ID=81959481
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220667376.8U Active CN216767592U (en) | 2022-03-25 | 2022-03-25 | Flow equalizer for liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216767592U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115176741A (en) * | 2022-07-05 | 2022-10-14 | 湖北海洋工程装备研究院有限公司 | Adjustable aerodynamic surface area fodder scattering device |
-
2022
- 2022-03-25 CN CN202220667376.8U patent/CN216767592U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115176741A (en) * | 2022-07-05 | 2022-10-14 | 湖北海洋工程装备研究院有限公司 | Adjustable aerodynamic surface area fodder scattering device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN216767592U (en) | Flow equalizer for liquid rocket engine | |
| JP3310078B2 (en) | Liquid propellant rocket engine with parallel auxiliary flow and integrated gas generator | |
| CN215370065U (en) | Rotary thrust vectoring nozzle of engine | |
| CN113871678B (en) | Fluid confluence distribution manifold for hydrogen fuel cell | |
| WO2017197544A1 (en) | Four aeronautic/astronautic turbofan engines | |
| CN110043390B (en) | Satellite bipropellant parallel storage tank balanced discharge synchronous valve and application thereof | |
| CN113074064A (en) | NOFBX thrust chamber based on microchannel regenerative cooling technology | |
| CN110159456B (en) | Rocket engine thrust chamber | |
| CN109441666B (en) | Tail vortex centrifugal injection type solid-liquid hybrid rocket engine | |
| CN211230644U (en) | Flow equalizer for liquid rocket engine | |
| CN214889536U (en) | Gas pipeline of high-speed joint | |
| CN205503192U (en) | Whole impeller of turbine binary channels of can backing a car | |
| CN211624515U (en) | Heat supply pipeline connecting piece | |
| CN109162830A (en) | It is a kind of can gimbaled rocket engine novel rotating shaft structure | |
| CN202007952U (en) | Pressure balancing type expansion joint of bypass straight tube | |
| CN217538871U (en) | Multi-spray-pipe liquid oxygen methane engine system | |
| CN111750938B (en) | Large-scale high accuracy owner feedwater venturi subassembly | |
| CN206280967U (en) | A kind of directrix plane or the high-power static surface burner head gas pipe of planar rondure | |
| CN115263607A (en) | Combustion control method for solid-liquid rocket engine and variable-thrust solid-liquid rocket engine | |
| CN212107019U (en) | High-precision oil-leakage-proof copper valve body | |
| CN113190913B (en) | Matching design method for axisymmetric cross-medium water-air amphibious aircraft power system | |
| CN114856863B (en) | Injector for spirally nested type explosive column | |
| CN212492443U (en) | Jet flow medicine adding device in pipeline | |
| CN110242439B (en) | Engine injector based on laminate diffusion welding, manufacturing method and engine | |
| CN217979917U (en) | Integrated heat exchanger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221114 Address after: 710000 C409-C30, Floor 4, Building 1, Huigu Commercial Street, Southeast Silk Road, Cross of Shenzhou 6th Road and Hangtuo Road, Xi'an National Civil Aerospace Industry Base, Shaanxi Province Patentee after: Xi'an Tanhuo Aerospace Technology Co.,Ltd. Address before: No. 29, Qinhuai District, Qinhuai District, Nanjing, Jiangsu Patentee before: Nanjing University of Aeronautics and Astronautics |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230309 Address after: 215000 158 Chengsi Road, Lili Town, Wujiang District, Suzhou City, Jiangsu Province Patentee after: Aerospace Promotion (Suzhou) Aerospace Technology Co.,Ltd. Address before: 710000 C409-C30, Floor 4, Building 1, Huigu Commercial Street, Southeast Silk Road, Cross of Shenzhou 6th Road and Hangtuo Road, Xi'an National Civil Aerospace Industry Base, Shaanxi Province Patentee before: Xi'an Tanhuo Aerospace Technology Co.,Ltd. |