CN112196699B - Gas guide pipe integrated structure of liquid rocket engine - Google Patents
Gas guide pipe integrated structure of liquid rocket engine Download PDFInfo
- Publication number
- CN112196699B CN112196699B CN202011119670.7A CN202011119670A CN112196699B CN 112196699 B CN112196699 B CN 112196699B CN 202011119670 A CN202011119670 A CN 202011119670A CN 112196699 B CN112196699 B CN 112196699B
- Authority
- CN
- China
- Prior art keywords
- gas
- collecting ring
- thrust chamber
- guide pipe
- integrated structure
- 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
- 239000007788 liquid Substances 0.000 title claims abstract description 18
- 229910045601 alloy Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 238000010146 3D printing Methods 0.000 claims description 3
- 238000005266 casting Methods 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims 1
- 230000010354 integration Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 63
- 239000002737 fuel gas Substances 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
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
- F02K9/60—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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a gas conduit integrated structure of a liquid rocket engine, which comprises the following components in sequential connection: a turbine casing, a gas duct collector, a flow straightener, and a thrust chamber head inlet; the gas guide pipe collector is provided with a gas collecting ring, a gas guide pipe, a collecting ring and a flow guide column, and the gas guide pipes are symmetrically dispersed on two sides of the gas collecting ring and the dispersing ring and are in a flat structure. The high-temperature gas enters the head of the thrust chamber uniformly after sequentially passing through the turbine shell, the gas collecting ring, the gas guide pipe, the collecting ring, the flow guide column, the flow guide grid and the inlet of the head of the thrust chamber. The technical scheme adopted by the invention has high integration level, can obviously improve the compactness of the connecting structure, reduces the overall height of the engine, further reduces the height of the engine connecting cabin body, further reduces the height of the rocket, reduces the weight of the rocket on one hand, and reduces the control difficulty of the rocket on the other hand. For the engine used in the swing, the control torque of the engine servo mechanism is also reduced.
Description
Technical Field
The invention relates to the technical field of rocket engine equipment, in particular to a gas guide pipe integrated structure of a liquid rocket engine.
Background
The air inlet guide pipe and the turbine exhaust pipe of the head part of the thrust chamber of the traditional pumping pressure type liquid rocket engine are of independent structures respectively, the air inlet guide pipe and the turbine exhaust pipe are connected through flanges at butt joint positions, a gas sealing structure is arranged at the joint, and the air inlet guide pipe and the turbine exhaust pipe form a gas guide pipe structure after being connected. Generally, the air inlet guide pipe at the head of the thrust chamber is in a quarter-circle elbow shape, so that the conversion of the horizontal direction to the vertical direction of fuel gas is completed, the overall height of the engine is larger due to the structure of the fuel gas guide pipe, and the overall height of the engine can be reduced by adopting the fuel gas guide pipe with an integrated structure, so that the height of a rocket engine cabin body is reduced, the height of the whole rocket is further reduced, the weight of the rocket is reduced on one hand, and the control difficulty of the rocket is reduced on the other hand; a sealing structure is cancelled, and the reliability is improved; for the engine used in the swing, the control torque of the engine servo mechanism is reduced.
At present, no description or report of similar technologies to the technology of the invention is found at home, and similar data at home and abroad is not collected.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a gas guide pipe integrated structure of a liquid rocket engine, so that the connection structure of a thrust chamber head and a turbine shell is more compact.
In order to achieve the aim, the invention provides a gas guide pipe integrated structure of a liquid rocket engine, which comprises a turbine shell, a gas guide pipe collector, a flow straightener and a thrust chamber head inlet;
the gas guide pipe collector comprises a gas collecting ring, a gas guide pipe, a collecting ring and a flow guide column; the gas collecting ring annularly coats the side wall of the turbine shell; the gas guide pipe is a channel connected between the gas collecting ring and the collecting ring; the collecting ring is connected to the inlet of the head of the thrust chamber, and the flow guide columns are arranged in the collecting ring and connected with the upper wall surface and the lower wall surface of the collecting ring; the flow straightener is positioned between the collector ring and the thrust chamber head inlet; the inlet of the thrust chamber head is connected with the thrust chamber head;
the gas enters the gas collecting ring after being rectified by the lateral blades on the side wall of the turbine shell, enters the collecting ring through the gas guide pipe, and enters the head of the thrust chamber from the inlet of the head of the thrust chamber after being rectified by the flow guide column and the rectifying grid.
Further, the gas guide pipe is transversely connected between the gas collecting ring and the collecting ring; the gathering ring is longitudinally connected with the thrust chamber head inlet.
Furthermore, the flow guide columns are longitudinally arranged along the circumferential direction of the collecting ring at intervals and used for rectifying the fuel gas entering the collecting ring through the fuel gas guide pipe.
Further, the flow straightener is transversely arranged between the collecting ring and the inlet of the thrust chamber head and comprises uniformly distributed longitudinal through holes.
Further, the gas guide pipe collector is welded with the rectifying grid and the inlet of the head of the thrust chamber, then the gas guide pipe collector is welded with the turbine shell, and the integrated structure of the gas guide pipes forms an integral structure.
Further, the gas conduit integrated structure is manufactured by casting or 3D printing.
Further, the material of the gas conduit collector is stainless steel, GH4202 alloy or GH4169 alloy.
Furthermore, the gas collecting ring and the collecting ring are two annular cavities, the gas guide pipe comprises two symmetrical straight arms which are respectively connected with the two annular cavities, and the excircle of each straight arm is tangent to the excircle wall surface of each annular cavity.
The technical scheme of the invention has the following beneficial technical effects:
(1) the technical scheme adopted by the invention has high integration level, can obviously improve the compactness of the connecting structure, reduces the overall height of the engine, further reduces the height of the engine connecting cabin body, further reduces the height of the rocket, reduces the weight of the rocket on one hand, and reduces the control difficulty of the rocket on the other hand.
(2) The invention also reduces the control moment of the engine servo mechanism for the engine used in the swinging way.
Drawings
FIG. 1 is a schematic longitudinal sectional view of a gas duct integrated structure of a liquid rocket engine according to the present invention;
FIG. 2 is a structural view taken along A of FIG. 1;
FIG. 3 is a front view of the material of the gas conduit manifold;
fig. 4 is an isometric view of a gas conduit manifold.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The invention provides a gas conduit integrated structure of a liquid rocket engine, which combines the following components in a figure 1 and a figure 2 and comprises the following components in sequential connection: a turbine casing 1, a gas duct collector 2, a flow straightener 3 and a thrust chamber head inlet 4.
With reference to fig. 3 and 4, the gas conduit collector 2 is provided with a gas collecting ring 21, a gas conduit 22, a collecting ring 23 and a flow guiding column 24, the gas conduit 22 is symmetrically distributed on two sides of the gas collecting ring 21 and the collecting ring 23, and the gas conduit collector 2 is an integral and flat structure. The gas collecting ring 21 annularly coats the side wall of the turbine housing 1, so that the gas discharged from the side wall of the turbine housing 1 completely enters the gas collecting ring 21; the gas guide pipe 22 is a channel connected between the gas collecting ring and the collecting ring, is symmetrically arranged at two sides and is horizontally arranged, and the cross section of the gas guide pipe is in a runway shape; the collecting ring 23 is longitudinally connected to the thrust chamber head inlet 4, the top end of the collecting ring is flat, and spoke-shaped reinforcing ribs are transversely arranged; the flow straightener 3 is mounted between the collector ring 23 and the thrust chamber head inlet 4; the thrust chamber head inlet 4 is connected with the thrust chamber head.
The guide columns 24 are arranged along the circumferential direction of the collecting ring at intervals, are longitudinally connected with the upper wall surface and the lower wall surface of the collecting ring, and disperse the fuel gas entering the collecting ring through the fuel gas guide pipe.
High-temperature and high-pressure gas after the precombustion chamber enters the turbine shell 1, enters the gas collecting ring 21 after rectification, is conveyed to the collecting ring 23 through the gas guide pipes 22 on two sides after the gas collecting ring 21 collects the gas, is dispersed through the flow guide columns 24, is uniformly sprayed out after passing through the rectification grids 3, and enters the inlet 4 at the head of the thrust chamber.
As shown in fig. 4, the collector ring 21 and the collector ring 23 are two ring cavities, and the structural size is set according to the structure of the turbine and the thrust chamber. The gas conduit 22 comprises two symmetrical straight arms respectively connected with the two annular cavities, and the excircle of each straight arm is tangent to the excircle wall surface of each annular cavity.
Further, the gas guide pipe collector 2 is welded with the flow straightener 3 and the thrust chamber head inlet 4 and then welded with the turbine shell 1 to form an integral structure.
In the gas conduit integrated structure, the upper part of a turbine shell 1 is connected with a precombustion chamber (not shown in the figure), the lower part of a thrust chamber head inlet 4 is connected with a thrust chamber head middle sole (not shown in the figure), and the upper part of the left end of a gas conduit collector 2 is connected with a flat seat (not shown in the figure).
Further, the processing method of the gas conduit collector comprises casting or 3D printing, and the material of the gas conduit collector can be selected from stainless steel, GH4202 or GH 4169.
In summary, the invention provides a gas conduit integrated structure of a liquid rocket engine, which comprises the following components in sequential connection: a turbine casing, a gas duct collector, a flow straightener, and a thrust chamber head inlet; the gas guide pipe collector is provided with a gas collecting ring, a gas guide pipe, a dispersing ring and a flow guide column, and the gas guide pipes are symmetrically dispersed on two sides of the gas collecting ring and the dispersing ring and are in a flat structure. The high-temperature gas enters the head of the thrust chamber uniformly after sequentially passing through the turbine shell, the gas collecting ring, the gas guide pipe, the dispersing ring, the flow guide column, the flow guide grid and the inlet of the head of the thrust chamber. The technical scheme adopted by the invention has high integration level, can obviously improve the compactness of the connecting structure, reduces the overall height of the engine, further reduces the height of the engine connecting cabin body, further reduces the height of the rocket, reduces the weight of the rocket on one hand, and reduces the control difficulty of the rocket on the other hand. For the engine used in the swing, the control torque of the engine servo mechanism is also reduced.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (8)
1. A gas guide pipe integrated structure of a liquid rocket engine is characterized by comprising a turbine shell, a gas guide pipe collector, a flow straightener and a thrust chamber head inlet;
the gas guide pipe collector comprises a gas collecting ring, a gas guide pipe, a collecting ring and a flow guide column; the gas collecting ring annularly coats the side wall of the turbine shell; the gas guide pipe is a channel connected between the gas collecting ring and the collecting ring; the collecting ring is connected to the inlet of the head of the thrust chamber, and the flow guide columns are arranged in the collecting ring and connected with the upper wall surface and the lower wall surface of the collecting ring; the flow straightener is positioned between the collector ring and the thrust chamber head inlet; the inlet of the thrust chamber head is connected with the thrust chamber head;
the gas enters the gas collecting ring after being rectified by the lateral blades on the side wall of the turbine shell, enters the collecting ring through the gas guide pipe, and enters the head of the thrust chamber from the inlet of the head of the thrust chamber after being rectified by the flow guide column and the rectifying grid.
2. The liquid rocket engine gas duct integrated structure of claim 1, wherein the gas duct is connected laterally between a gas collecting ring and a gathering ring; the gathering ring is longitudinally connected with the thrust chamber head inlet.
3. The liquid rocket engine gas duct integrated structure of claim 2, wherein the flow guiding columns are longitudinally spaced along the circumference of the gathering ring to rectify the gas entering the gathering ring through the gas duct.
4. A liquid rocket engine gas duct integrated structure as claimed in claim 3, wherein said flow straightener is transversely disposed between said collector ring and said thrust chamber head inlet and comprises uniformly distributed longitudinal through holes.
5. The liquid rocket engine gas duct integrated structure of claim 1 or 2, wherein the gas duct manifold is welded to the flow straightener, the thrust chamber head inlet, and then the gas duct manifold is welded to the turbine casing, the gas duct integrated structure forming a unitary structure.
6. The liquid rocket engine gas duct integrated structure of claim 5, wherein the gas duct integrated structure is obtained by casting or 3D printing manufacturing.
7. The liquid rocket engine gas duct integrated structure of claim 1 or 2, wherein the material of the gas duct collector is stainless steel, GH4202 alloy or GH4169 alloy.
8. The liquid rocket engine gas conduit integrated structure of claim 1 or 2, wherein the gas collecting ring and the collecting ring are two annular cavities, the gas conduit comprises two symmetrical straight arms respectively connecting the two annular cavities, and the outer wall surfaces of the straight arms are tangent to the outer circular wall surfaces of the annular cavities.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011119670.7A CN112196699B (en) | 2020-10-19 | 2020-10-19 | Gas guide pipe integrated structure of liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011119670.7A CN112196699B (en) | 2020-10-19 | 2020-10-19 | Gas guide pipe integrated structure of liquid rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112196699A CN112196699A (en) | 2021-01-08 |
| CN112196699B true CN112196699B (en) | 2021-07-30 |
Family
ID=74009333
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011119670.7A Active CN112196699B (en) | 2020-10-19 | 2020-10-19 | Gas guide pipe integrated structure of liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112196699B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3040695B2 (en) * | 1995-06-09 | 2000-05-15 | 三菱重工業株式会社 | Liquid rocket engine |
| FR2915245A1 (en) * | 2007-04-20 | 2008-10-24 | Pratt Whitney Rocketdyne Inc | EXPANSION CYCLE ROTOR MOTOR WITH MULTIPLE PUSH CHAMBERS WITH COMMON TURBOGENERATOR |
| CN108953003B (en) * | 2018-06-28 | 2021-03-23 | 西安航天动力研究所 | Engine system for realizing afterburning cycle and thrust depth adjusting method |
| CN109915280A (en) * | 2019-03-14 | 2019-06-21 | 北京星际荣耀空间科技有限公司 | A kind of electronic variable thrust rocket engine and the rocket with it |
| CN111720238B (en) * | 2019-07-03 | 2021-08-10 | 西安航天动力研究所 | Liquid oxygen expansion cycle-based depth variable-thrust multi-start liquid rocket engine |
| CN111692014A (en) * | 2020-06-18 | 2020-09-22 | 安徽九州云箭航天技术有限公司 | Liquid rocket engine, thrust control method and device thereof and carrier rocket |
-
2020
- 2020-10-19 CN CN202011119670.7A patent/CN112196699B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN112196699A (en) | 2021-01-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112196699B (en) | Gas guide pipe integrated structure of liquid rocket engine | |
| CN112727860B (en) | Structure for high-Mach-number molded surface spray pipe water-cooling throat of hypersonic wind tunnel | |
| CN107165739A (en) | Solid-liquid rocket circular seam type plug nozzle | |
| CN213117927U (en) | Water inlet pipe of supercharger | |
| CN113588233B (en) | Exhaust back pressure adjusting system and method suitable for turbine test bed | |
| CN113738536B (en) | Integrated force-bearing flow-equalizing top cover device | |
| CN111577494B (en) | Intake manifold with waste gas inlet hole | |
| CN202361353U (en) | Nuclear power horizontal type high-pressure feed-water heater | |
| CN220078679U (en) | Atomizing deaerator | |
| CN210460822U (en) | Exhaust system of Y5 series airplane turboprop engine | |
| CN204152631U (en) | A kind of marine diesel engine inlet and exhaust system | |
| CN107726412B (en) | Swimming ring type side-suction type range hood | |
| CN209197252U (en) | A kind of cyclic water tank silencer mechanism | |
| CN218847637U (en) | Exhaust system with noise reduction function of hydrogen gas turbine test bed | |
| CN219974919U (en) | Turbocharger compressor housing with air inlet compensation structure | |
| CN201935593U (en) | Steam exhaust header pipe of steam turbine | |
| CN216642287U (en) | Boundary layer air suction structure with angular separation structural characteristics under multiple working conditions | |
| CN112796844B (en) | Connecting structure of single valve and air cylinder of supercritical carbon dioxide power generation system | |
| CN219424099U (en) | Aluminum profile casting waste gas treatment mechanism | |
| CN214701830U (en) | Normal-temperature normal-pressure water mist mixing tank | |
| CN218011964U (en) | Piston smelting furnace tail gas treatment system | |
| CN208816218U (en) | A kind of exhaust manifold | |
| CN219638930U (en) | Exhaust manifold of integrated exhaust gas recirculation passageway | |
| CN113446268B (en) | Sleeve type pneumatic conveying slurry pump | |
| CN216447000U (en) | A grab steel machine exhaust apparatus for taking shelter from rain |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240320 Address after: Room 602, Jintong Building, No. 9 Guotai North Road, Zhangjiagang Economic and Technological Development Zone, Suzhou City, Jiangsu Province, 215638 Patentee after: Tianjin Tianbing Aerospace Technology Co.,Ltd. Country or region after: Zhong Guo Address before: 100076 a401, floor 4, 101, floor 1-4, building 4, yard 36, Second District, heyixili, Fengtai District, Beijing Patentee before: Beijing Tianbing Technology Co.,Ltd. Country or region before: Zhong Guo |