CN117846815A - Annular pneumatic plug type rocket engine thrust chamber - Google Patents
Annular pneumatic plug type rocket engine thrust chamber Download PDFInfo
- Publication number
- CN117846815A CN117846815A CN202310300127.4A CN202310300127A CN117846815A CN 117846815 A CN117846815 A CN 117846815A CN 202310300127 A CN202310300127 A CN 202310300127A CN 117846815 A CN117846815 A CN 117846815A
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- Prior art keywords
- pneumatic plug
- thrust chamber
- annular
- chamber
- rocket
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- 238000002485 combustion reaction Methods 0.000 claims description 20
- 239000007921 spray Substances 0.000 claims description 7
- 239000003380 propellant Substances 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims 1
- 238000005192 partition Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000035755 proliferation Effects 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
The invention provides an annular pneumatic plug type rocket engine thrust chamber, which is designed to reduce the comprehensive weight of the engine, effectively utilize the space of a rocket frame and adapt to high altitude performance.
Description
Technical Field
The invention relates to the technical field of liquid rocket engines, in particular to a pneumatic plug type rocket engine.
Background
The existing rocket is generally launched by adopting a mode that a plurality of circular jet pipe engines are arranged in parallel and simultaneously ignited, wherein each rocket engine is a circular jet pipe and is provided with an independent turbine pump. The combination of the engine and the rocket has the following problems:
1. rocket engines with circular nozzles cannot effectively utilize the internal space of the rocket and cannot arrange engines with larger thrust in the same diameter rocket body.
2. The rocket is internally provided with a plurality of starting structures with heavy weight and a plurality of redundant structures.
3. The multiple turbine pumps of the multiple engines have complex structure and high failure rate.
4. The engine with the circular spray pipe occupies the outer edge space of the rocket, which is not beneficial to the engine with larger spray pipe and vector thrust arranged in the middle of the rocket.
Therefore, there is a strong need for a rocket engine that is capable of adapting to the flying height without increasing the weight and has a simple structure.
Disclosure of Invention
The invention aims at solving the defects in the prior art and provides an annular pneumatic plug rocket engine thrust chamber device which aims at solving the problems;
unlike the earliest square pneumatic plug structure and the conventional conical pneumatic plug structure, the annular pneumatic plug structure is in a whole annular shape, and a space is reserved in the middle for installing a vector thrust engine of a rocket.
The annular pneumatic plug thrust chamber spray pipe is provided with a gas constraint wall surface in an annular inner measurement mode, and the outer side of the annular pneumatic plug thrust chamber spray pipe is provided with a gas constraint wall surface.
The annular pneumatic plug thrust chamber is divided into a plurality of combustion chambers by the partition plate, and the combustion chamber can stop the operation of the combustion chamber by cutting off the supply of the propellant when one combustion chamber fails, so that the overall reliability is improved. The turbine pump is shared by a plurality of combustion chambers or all the combustion chambers, so that the number of the turbine pumps can be reduced, the weight of the whole structure is reduced, and the inside of the partition plate is provided with a proliferation cooling pipeline structure like the wall of the combustion chamber.
The flame connecting area is arranged below the partition plate and acts like an aeroengine flame connecting device, flames of one combustion area are transmitted to the adjacent area, and flameout of a certain combustion chamber can be effectively prevented.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are only preferred embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a conventional pneumatic plug device;
FIG. 2 is a schematic view of a thrust chamber of an annular air plug rocket engine according to the present invention.
FIG. 3 is a schematic cross-sectional view of a thrust chamber of an annular air plug rocket engine according to the present invention;
FIG. 4 is a schematic view of a thrust chamber non-combustion chamber cover of an annular air plug rocket engine according to the present invention.
FIG. 5 is an enlarged schematic view of a portion of the combustion chamber baffle plate and flame connecting region of the present invention;
FIG. 6 is a schematic diagram of the thrust chamber of the annular air plug rocket engine without the combustion chamber and the turbo pump.
FIG. 7 is a schematic view of an annular air plug rocket engine thrust chamber of the present invention disposed at the bottom of a rocket;
reference numerals illustrate:
1-bell-shaped spray pipe; 2-a pneumatic plug nozzle; 3-combustion chamber; 4-dividing plates; 5-pneumatic plug cross section; 6-equivalent cross section; 7-a flame zone; 8-propellant lines; 9-annular pneumatic plug type engine thrust chamber.
Detailed Description
For a better understanding of the present invention, its construction, and the functional features and advantages attained by the same, reference should be made to the accompanying drawings in which:
as shown in fig. 2, the invention provides an annular pneumatic plug type rocket engine thrust chamber device, which comprises a divided combustion chamber 3 and a dividing plate 4.
As shown in fig. 3, the annular pneumatic plug thrust chamber section 5 and the equivalent section 6, the equivalent section 6 is a pneumatic plug section of a conventional structure, and each partition area corresponds to a single pneumatic plug thrust chamber, so that space and structural weight are saved.
As shown in fig. 6, each of the divided circular arc combustors is connected to a turbo pump through a pipe, and receives the pressurized propellant.
The high-temperature high-pressure gas in the combustion chamber is sprayed out through the pneumatic plug spray pipe, and the combustion chamber extinguished in the adjacent combustion area can be ignited in the continuous flame area, so that the overall reliability of the engine is improved.
As shown in fig. 7, the whole annular pneumatic plug engine is arranged at the lower part of the rocket, and a space is reserved in the middle of the annular pneumatic plug thrust chamber for the rocket to mount the vector thrust engine.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way. Many possible variations and modifications of the disclosed technology can be made by anyone skilled in the art, or equivalent embodiments with equivalent variations can be made, without departing from the scope of the disclosed technology. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technology of the present invention fall within the protection scope of the present invention.
Claims (6)
1. The annular pneumatic plug type rocket engine thrust chamber is characterized by comprising an annular pneumatic plug spray pipe, a divided combustion chamber, a separation plate, a continuous flame zone and a shared turbine pump.
2. The pneumatic plug thrust chamber of claim 1, wherein said annular pneumatic plug nozzle has a gas-confining wall on an inner side thereof and an annular gas-free outer side thereof.
3. A pneumatic plug thrust chamber according to claim 1, wherein the divided combustion chamber is divided into sections by a dividing plate.
4. The pneumatic plug thrust chamber of claim 1, wherein the divider plate has a regeneratively cooled inner structure.
5. The pneumatic plug thrust chamber of claim 1, wherein the flame-connecting region is an undivided portion of the dividing plate lower portion.
6. The pneumatic plug thrust chamber of claim 1 wherein the propellant for the common turbo pump being all or part of the split combustion chamber is from the same turbo pump.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310300127.4A CN117846815A (en) | 2023-03-27 | 2023-03-27 | Annular pneumatic plug type rocket engine thrust chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310300127.4A CN117846815A (en) | 2023-03-27 | 2023-03-27 | Annular pneumatic plug type rocket engine thrust chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117846815A true CN117846815A (en) | 2024-04-09 |
Family
ID=90527760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310300127.4A Pending CN117846815A (en) | 2023-03-27 | 2023-03-27 | Annular pneumatic plug type rocket engine thrust chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117846815A (en) |
-
2023
- 2023-03-27 CN CN202310300127.4A patent/CN117846815A/en active Pending
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |