CN112145316B - Liquid engine - Google Patents
Liquid engine Download PDFInfo
- Publication number
- CN112145316B CN112145316B CN202011094208.6A CN202011094208A CN112145316B CN 112145316 B CN112145316 B CN 112145316B CN 202011094208 A CN202011094208 A CN 202011094208A CN 112145316 B CN112145316 B CN 112145316B
- Authority
- CN
- China
- Prior art keywords
- liquid
- collecting structure
- thrust chamber
- gas
- storage device
- 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 216
- 238000002485 combustion reaction Methods 0.000 claims abstract description 9
- 239000003380 propellant Substances 0.000 claims description 14
- 239000002826 coolant Substances 0.000 claims description 13
- 239000012809 cooling fluid Substances 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims 1
- 239000000110 cooling liquid Substances 0.000 abstract description 29
- 238000004891 communication Methods 0.000 abstract description 4
- 238000001816 cooling Methods 0.000 description 14
- 230000000694 effects Effects 0.000 description 14
- 238000009833 condensation Methods 0.000 description 10
- 230000005494 condensation Effects 0.000 description 10
- 239000000446 fuel Substances 0.000 description 7
- 239000007800 oxidant agent Substances 0.000 description 6
- 230000001590 oxidative effect Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 2
- 238000007654 immersion Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000012546 transfer Methods 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
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- 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
- F02K9/62—Combustion or thrust chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust-Gas Circulating Devices (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
The invention discloses a liquid engine. The liquid engine comprises a thrust chamber, a first storage device for storing cooling liquid and a liquid collection structure arranged outside the thrust chamber; wherein the thrust chamber comprises a chamber and a housing forming the chamber, the liquid collection structure being disposed on the housing of the thrust chamber head, the liquid collection structure and the first storage device being in communication with one another. The liquid engine can actively cool the shell at the head part of the thrust chamber, thereby avoiding the phenomenon that the thrust chamber is damaged or burnt through due to combustion of the engine.
Description
The application is a divisional application of an invention patent with the name of 'a liquid engine and a carrier' and the application number of '201810061907.7', which is filed on 23.1.2018.
Technical Field
The invention relates to the technical field of spaceflight, in particular to a liquid engine.
Background
The engine is one of the key technologies in the aerospace field. After ignition of the engine, the liquid propellant may be converted to a gas by the high temperature, thereby creating a large hot back soak that may damage or even burn through the head of the thrust chamber. This is particularly true for combustors having a single wall construction.
It is highly desirable to design a safe and reliable liquid engine that is effectively resistant to thermal reverse immersion.
Disclosure of Invention
In view of the above technical problems in the related art, the present invention provides a liquid engine and a vehicle. The liquid engine can actively cool the shell of the thrust chamber, thereby avoiding the phenomenon that the thrust chamber is damaged or burnt through.
One aspect of the present invention provides a liquid engine. The liquid engine comprises a thrust chamber, a first storage device for storing cooling liquid and a liquid collection structure arranged outside the thrust chamber; wherein the thrust chamber comprises a chamber and a housing forming the chamber, the housing comprising a head housing at a head of the thrust chamber, the liquid collection structure being disposed on the head housing, the liquid collection structure and the first storage device being in communication with each other.
In one embodiment, the liquid collecting structure is circumferentially arranged at the outer side of the head shell, so that the inner surface of the liquid collecting structure and the outer surface of the head shell form an annular flow passage for cooling liquid to flow.
In one embodiment, the inner surface of the liquid collection structure includes a side surface disposed facing the outer surface of the housing and a bottom surface connecting the side surface and the outer surface.
In one embodiment, the distance from the side surface to the outer surface increases gradually in a first direction from the side surface to the bottom surface.
In one embodiment, the first storage device includes a first liquid inlet and a first liquid outlet, the liquid collecting structure includes a second liquid inlet and a second liquid outlet, the first liquid outlet is used for communicating with the second liquid inlet, the second liquid outlet is used for communicating with the first liquid inlet, and the second liquid inlet and the second liquid outlet are arranged away from each other outside the housing.
In one embodiment, the liquid collection structure is a unitary structure with the thrust chamber.
In one embodiment, the liquid engine further comprises liquid propellant storage means and second storage means for storing gas; wherein the second storage means is adapted to compress the liquid propellant storage means by the gas stored therein to thereby cause liquid propellant to enter the combustion chamber;
and a gas collection structure is further arranged on the outer side of the liquid collection structure, and the gas collection structure is communicated with the second storage device.
In one embodiment, the gas collecting structure is circumferentially arranged on the outer surface of the head housing, and the gas collecting structure is circumferentially arranged on the outer surface of the liquid collecting structure, so that the inner surface of the gas collecting structure and the outer surface of the liquid collecting structure form an annular channel for gas to flow.
In one embodiment, the gas collection structure is coaxial with the liquid collection structure.
In one embodiment, the thrust chamber, the gas collection structure and the liquid collection structure are coaxial.
In one embodiment, the gas collection structure comprises a gas inlet end and a gas outlet end, and the liquid collection structure comprises a liquid inlet end and a liquid outlet end; the air inlet end and the liquid inlet end are located on the same side of the head shell, and the air outlet end and the liquid outlet end are located on the other side of the head shell.
In one embodiment, the gas collection structure has a smaller dimension than the liquid collection structure in an axial direction of the thrust chamber.
In one embodiment, the dimension of the gas collection structure is 1/3-1/2 of the dimension of the liquid collection structure in the axial direction of the thrust chamber.
Another aspect of the invention provides a vehicle comprising a liquid engine as described above.
The liquid engine of the embodiment of the invention has at least one of the following technical effects:
(1) according to the liquid engine provided by the invention, the active cooling structure is arranged on the shell of the head part of the thrust chamber, so that the damage of the hot back-dipping phenomenon to the shell of the head part of the thrust chamber is effectively relieved, and the safety of the engine is improved.
(2) According to the liquid engine provided by the invention, the liquid collecting structure is arranged in the circumferential direction of the thrust chamber head shell, so that the thrust chamber head shell can be uniformly cooled in the circumferential direction, the stress change caused by uneven temperature is avoided, and a better cooling effect is achieved.
(3) According to the liquid engine provided by the invention, the liquid collecting structure is arranged on the outer side of the head part of the thrust chamber, so that the excessive increase of the weight of the engine can be avoided, and the effective load throwing capacity of a carrier is further ensured.
(4) According to the liquid engine provided by the invention, the gas collection structure is arranged on the outer side of the head part of the liquid collection structure, so that on one hand, the heat of the liquid collection structure can be further taken away, and the cooling capacity of the liquid collection structure on the head part shell of the thrust chamber is further improved; on the other hand, since the gas entering the gas collecting structure is heated and returned to the gas storage device, the pressure of the gas rises, and therefore, the amount of gas in the gas storage device can be reduced, thereby indirectly reducing the weight of the engine.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described 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 without creative efforts.
Fig. 1-3 are schematic cross-sectional views of an engine thrust chamber according to an embodiment of the present invention.
Fig. 4a and 4b are schematic cross-sectional views of an engine thrust chamber according to an embodiment of the present invention.
FIG. 5a is a schematic top view of a thrust chamber of an embodiment of the present invention.
Fig. 5b is a cross-sectional view of fig. 5a taken along the direction a-a 1.
Fig. 6a is a schematic sectional view of a thrust chamber according to an embodiment of the present invention.
Figure 6b is a schematic view of the development of the components of the liquid collection structure provided with a gas collection structure.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
In liquid rocket engines, after the liquid propellant enters the thrust chamber, it may be possible that upon ignition, the liquid propellant is largely vaporized, resulting in uncontrolled combustion of this vaporized liquid, which in turn results in the thrust chamber head casing being burned through. Therefore, it is desirable to design a safe and reliable liquid engine.
One aspect of the present invention provides a liquid engine. Referring to fig. 1, the liquid engine comprises a thrust chamber, first storage means for storing a coolant (not shown, the location of the storage means is not particularly limited to minimize the arrangement of other components of the engine), and a liquid collection structure 4 provided at the head casing of the thrust chamber. Wherein the thrust chamber comprises a chamber 2 and a housing 3 forming the chamber 2, the housing 3 comprises a head housing located at a head position of the thrust chamber, the liquid collecting structure 4 is arranged on the head housing 3, and the liquid collecting structure 4 and the first storage device are communicated with each other. According to the invention, the liquid collecting structure is arranged outside the thrust chamber head shell, so that the temperature of the thrust chamber shell can be reduced, and the liquid gasification phenomenon of the thrust chamber head is weakened or eliminated, thereby preventing the thrust chamber head shell from being damaged or burnt through after the engine is ignited, and improving the working reliability of the engine.
In this embodiment, for example, a nozzle (not shown) is further included below the thrust chamber shown in fig. 1, so that after the combustion of the combustion chamber, the fuel and the oxidant are ejected downward through the nozzle communicating with the combustion chamber to generate the reverse thrust.
The liquid collecting structure 4 is provided in the thrust chamber head housing 3, and may be a condensation pipe directly contacting with the thrust chamber head housing 3, or may be a structure that forms a liquid flow channel together with the outer surface of the thrust chamber head housing 3. For example, in the case where the liquid collecting structure 4 is a condensation pipe, the number of the condensation pipe may be one or more. For example, the plurality of condensation tubes may be wound outside the thrust chamber head housing 3 in a parallel, overlapping, or intersecting manner. For example, the flow passage size of the same condensation tube may be the same or different, thereby achieving different cooling capacities. For example, a different number of condenser tubes may be provided at different locations outside the thrust chamber head housing 3. Specifically, more condensation pipes may be densely arranged at a portion where the thrust chamber head housing 3 is heated more, and fewer condensation pipes may be arranged at a position where the thrust chamber head housing 3 is heated less.
For example, as shown in fig. 1, in the case where the liquid collecting structure 4 forms a liquid flow passage together with the outer surface of the thrust chamber head housing 3 of the engine, the liquid collecting structure 4 may be, for example, a structure having a groove, so that the inner surface of the concave structure and the outer surface of the thrust chamber head housing 3 may form a passage suitable for the flow of the coolant together by disposing the side of the groove having the concave structure along the surface of the thrust chamber head housing (the liquid collecting structure shown in fig. 1 is formed in this manner). For example, for the liquid collecting structure with the concave structure, the concave part can be enlarged as much as possible, and the material of other parts can be thinned, so that the capacity of containing the cooling liquid is improved, and the weight of the engine is reduced. Further, for example, the notch can be a U-shaped notch or a V-shaped notch, so that the shape of the cooling liquid in the liquid collecting structure is improved, and the cooling effect on the engine thrust chamber head shell is improved. For example, the liquid collecting structure may be another structure as long as it is provided on the outer surface of the thrust chamber head housing 3 and then forms a flow passage suitable for the flow of liquid with the outer surface of the housing. For example, the flow passage may be a closed flow passage, that is, only including an inlet and an outlet of the coolant, so as to prevent the coolant from volatilizing or overflowing from the engine liquid when the engine is in operation, and ensure the cooling performance of the coolant and the safety of the engine.
Furthermore, the liquid collecting structure 4 may be in communication with the first storage means in, for example, a two-way communication. So that the cooling liquid in the storage device can flow out of the storage device along one of the branches and into the liquid collecting structure 4. For example, after the cooling liquid has cooled the thrust chamber head casing, the cooling liquid may flow out of the liquid collection structure and return to the storage device along another branch, thereby achieving circulation of the cooling liquid between the storage device and the liquid collection structure 3, and further reducing the temperature of the thrust chamber head casing 3 through circulation of the cooling liquid.
Referring to fig. 2, for example, the engine enters the liquid collection structure 4 through a coolant inlet 7 penetrating the thrust chamber connection surface 8 and flows along the inside of the liquid collection structure 4, thereby cooling the thrust chamber head housing 3, and then flows out from a coolant outlet 9 penetrating the thrust chamber connection surface 8 to return to the first storage device. Obviously, the inlet 7 of the cooling liquid may communicate with the interior of the liquid collecting structure 4, and the outlet 9 of the cooling liquid may communicate with the interior of the liquid collecting structure 4 from the other side of the liquid collecting structure 4. For example, a first storage means may be provided on the side of the thrust chamber connection face 8 remote from the thrust chamber (not shown in the figures) and connected by a pipe to the inlet 7 of the cooling liquid and by another pipe to the outlet 9 of the cooling liquid, so as to facilitate the circulation of the cooling liquid between the liquid collection structure 4 and the first storage means.
With continued reference to fig. 1 and 2, for example, in one embodiment, the liquid collecting structure 4 is circumferentially disposed on the outer side of the head housing 3, and the liquid collecting structure 3 is recessed from a side close to the head housing 3 to a side away from the head housing 3, so that an inner surface (a surface of the recessed portion) of the liquid collecting structure 4 and an outer surface of the thrust chamber head housing 3 may form an annular flow passage for the flow of the cooling liquid. In this case, the coolant flows through the entire annular flow passage after flowing from the storage device into the annular passage through the coolant inlet 7, thereby reducing the temperature of the thrust chamber head housing 3 through sufficient heat exchange with the outer surface of the thrust chamber head housing 3. The cooling fluid is then returned to the storage device through the cooling fluid outlet 9 for cooling. According to the embodiment of the invention, the annular flow channel is directly formed by the inner surface of the liquid collection structure and the outer surface of the head shell of the thrust chamber, so that the cooling liquid can directly exchange heat with the head shell, and the heat exchange effect of the head shell of the thrust chamber is improved.
In this embodiment, for example, the inner surface of the liquid collecting structure 4 may be an uneven structure. Specifically, the inner surface of the liquid collecting structure 4 may include a screw structure or a structure of a plurality of minute flow passages provided along the inner surface. Thereby slow down the velocity of flow of coolant liquid through collection liquid structure unevenness's internal surface, increase the heat exchange time of coolant liquid and casing 3, improve the heat exchange effect.
Referring to fig. 3, in one embodiment, the inner surface of the liquid collecting structure 4 comprises a side surface 41 and a bottom surface 42, wherein the side surface 41 is disposed facing the outer surface of the housing 3, and the bottom surface 42 connects the side surface 41 and the outer surface. That is, the side surface 41 is provided at a distance from the outer surface of the thrust chamber head housing 3, and the bottom surface 42 forms a passage for the flow of the cooling liquid by connecting the side surface 41 and the outer surface of the thrust chamber head housing 3. Because the liquid collecting structure 4 comprises the bottom surface 42, the distance between the part of the side surface 41 close to the bottom surface 42 and the outer surface of the thrust chamber head shell 3 is increased, so that the volume of the flow channel is increased, the amount of the cooling liquid contained in the flow channel is increased, and the cooling effect is improved.
It is noted that, as shown in fig. 3, the thrust chamber includes a connecting portion 8 (i.e., the connecting surface referred to above) for connecting with other components. For example, the transverse dimension of the connecting portion 8 (in the direction shown by C-C1 in the figures) is greater than the transverse dimension of the portion of the thrust chamber housing 3, so that one of the surfaces of the above-mentioned flow channels can be constituted by the surface of the connecting portion 8 close to the liquid collecting structure 4, so that the annular flow channel is constituted by the surface of the connecting portion 8, the inner surface of the liquid collecting structure 4 and the outer surface of the thrust chamber head housing 3 together. Further, as shown in fig. 3, the inlet 7 and the outlet 9 for the inlet and outlet of the cooling liquid are also communicated with the flow passage of the cooling liquid through the through connection portion.
In this embodiment, for example, the distance from the side surface 41 to the outer surface of the thrust chamber head housing 3 may gradually increase in a direction from the side surface 41 toward the bottom surface 42 (i.e., in a direction from top to bottom in the drawing). This is because, above the flow channels shown in the figures, the housing 3 is correspondingly less subject to hot back-immersion and therefore the cooling liquid can be relatively small. On the other hand, the amount of coolant can be relatively large because the heat sink is more exposed at the lower portion of the casing 3 constituting the flow path. According to the embodiment of the invention, the upper width and the lower width of the flow channel are different, so that the flow channel corresponding to the part of the shell which is heated and reversely soaked is wider, the temperature distribution of the head shell of the thrust chamber is more uniform through differential cooling of the head shell of the thrust chamber, and the safety of the head shell of the thrust chamber is protected.
In one embodiment, the first storage device includes a first liquid inlet and a first liquid outlet, the liquid collecting structure 4 includes a second liquid inlet and a second liquid outlet, the first liquid outlet is used for communicating with the second liquid inlet, the second liquid outlet is used for communicating with the first liquid inlet, and the second liquid inlet and the second liquid outlet are arranged far away from each other outside the thrust chamber housing 3. According to the embodiment of the invention, the liquid inlet and the liquid outlet of the liquid collecting structure arranged outside the thrust chamber shell are arranged far away from each other, so that the flow path of cooling liquid in the flow channel can be increased, the heat exchange time is prolonged, and the cooling effect on the thrust chamber shell is improved.
It should be noted that, in the case where the liquid collecting structure 4 disposed outside the thrust chamber head housing 3 is a condenser tube, the distance between the liquid inlet 7 and the liquid outlet 9 of the liquid collecting structure 4 has little influence. The arrangement of the condensation pipe should be based on increasing the flowing time of the cooling liquid in the condensation pipe and the contact area of the condensation pipe and the thrust chamber head shell 3, so as to improve the cooling effect.
In one embodiment, for example, the liquid collection structure 4 and the thrust chamber may be a unitary structure. For example, the liquid collection structure 4 may be welded to the thrust chamber head casing 3 or formed integrally therewith, so as to avoid damage to the liquid collection structure during operation of the vehicle, particularly when subjected to severe disturbances such as in rocket flight.
In one embodiment, the liquid engine further comprises a liquid propellant and fuel storage means and a second storage means for storing gas. Wherein the second storage means is adapted to compress the liquid propellant storage means by gas stored therein so that liquid propellant enters the combustion chamber through the propellant inlet. Specifically, as shown in fig. 4a, the liquid engine includes an oxidant inlet 11 and a fuel inlet 12, and for example, the oxidant or the fuel may be pressed by the gas stored in the second storage device to enter the thrust chamber through the oxidant inlet 11 and the fuel inlet 12. For example, oxidant is injected into the thrust chamber by the injector 10 to be mixed with fuel for combustion. As shown in fig. 4a, a gas collecting structure 5 is further provided outside the liquid collecting structure 4, and the gas collecting structure 5 and the second storage device are communicated with each other. According to the embodiment of the invention, the gas collection structure is arranged on the outer side of the liquid collection structure, so that on one hand, the heat of the cooling liquid after heat exchange with the thrust chamber head shell 3 can be further taken away, and the cooling effect of the cooling liquid on the thrust chamber shell 3 is improved. On the other hand, after the heated gas is returned to the second storage device, the pressure is increased due to the increase in the temperature of the gas, so that the capability of the liquid propellant storage device to be squeezed by the same amount of gas is improved, i.e., the same squeezing effect on the oxidizer or fuel can be achieved by only using less gas. The mass of gas stored by the second storage means is reduced relative to the vehicle, and the overall mass of the engine may also be reduced, thereby indirectly improving the launch capability of the vehicle.
Referring to fig. 4b, in one embodiment, the liquid collecting structure 4 is circumferentially disposed on the outer surface of the thrust chamber head housing 3, and the gas collecting structure 5 is circumferentially disposed on the outer surface of the liquid collecting structure 4, so that the inner surface of the gas collecting structure 5 and the outer surface of the liquid collecting structure 4 form an annular channel for gas to flow. For example, the annular channel is formed entirely by the inner surface of the gas collecting structure 5 and the outer surface of the liquid collecting structure 4, and one end of the annular channel comprises the gas inlet 6 and the other end is provided with the gas outlet 13. For example, as shown in fig. 4b, the gas inlet 6 and the gas outlet 13 of the annular channel are respectively located at two sides of the thrust chamber head housing 3 (for example, the connecting line of the gas inlet and the gas outlet is just the diameter of the annular channel, that is, the gas inlet and the gas outlet are arranged at two end points of the diameter of the annular channel), so that the gas released from the gas storage device can move from the gas inlet 6 of the annular channel to the gas outlet 13 from two directions, thereby improving the uniformity of heat exchange between the gas and the liquid collecting structure.
As shown in fig. 4a and 4b, in this embodiment, for example, the gas collecting structure 5 may be an annular body structure comprising a groove recessed from an inner ring to an outer ring, and the inner ring of the annular body has dimensions matching the outer dimensions of the liquid collecting structure 4, so that the gas collecting structure may be welded to the outer side of the liquid collecting structure, for example. After the gas collecting structure 5 is installed on the outer side of the liquid collecting structure 4, the inner surface of the groove of the gas collecting structure 5 and the outer surface of the liquid collecting structure 4 form a gas flowing channel. In engineering, for example, the liquid collecting structure 4 and the gas collecting structure 5 having an integral structure may be formed first and then outside the casing 3 integrally connected to the thrust chamber.
In this embodiment, for example, the gas collection structure 5 is coaxial with the liquid collection structure 4. Or the thrust chamber, the gas collection structure 5 and the liquid collection structure 4 are all coaxial. Thereby ensure the effect of the heat exchange of collection liquid structure 4 and thrust room casing 3 to and the heat transfer effect between collection liquid structure 4 and the gas collecting structure 5, improve collection liquid structure 4 to the refrigerated homogeneity of thrust room head casing 3, and the homogeneity of collection liquid structure 4 to the gas heating in the gas collecting structure 5. In addition, through with album of liquid structure 4 and the coaxial setting of gas collection structure 5, or with album of liquid structure 4, gas collection structure 5 and the equal coaxial setting of thrust chamber, can improve the stability of engine structure to further improve the performance of engine.
Referring to fig. 5a and 5b, in one embodiment, the gas collection structure 5 includes a gas inlet end 6 and a gas outlet end 13, and the liquid collection structure 4 includes a liquid inlet end 7 and a liquid outlet end 9; and the air inlet end 6 and the liquid inlet end 7 are positioned on the same side of the head shell 3, and the air outlet end 13 and the liquid outlet end 9 are positioned on the other side of the head shell 3. According to the embodiment of the invention, the inlets of the cooling liquid and the gas are arranged on the same side, and the outlets of the cooling liquid and the gas are arranged on the other side, so that the cooling liquid and the gas can be synchronously heated, the severe thermal convection is avoided, and the safety and the reliability of the engine are improved.
Referring to fig. 6a and 6B, in one embodiment, the dimension h1 of the plenum structure 5 is smaller than the dimension h2 of the plenum structure 4 in the axial direction of the thrust chamber (i.e., the direction B-B1 in fig. 6a and 6B). For example, as mentioned above, the gas collecting structure 5 and the liquid collecting structure 4 are both annular structures, and the dimension h2 of the liquid collecting structure 4 in the axial direction thereof is larger than the dimension h1 of the gas collecting structure in the axial direction. For example, the dimension h1 of the gas collecting structure 5 in the axial direction is 1/3-1/2 of the dimension h2 of the liquid collecting structure 4. Thus, the gas collecting mechanism 5 can be in contact with only a part of the outside of the liquid collecting structure 4, thereby avoiding the problem of too high air pressure caused by too much temperature rise in the gas collecting structure.
It should be pointed out that, the outside of thrust chamber head shell still can be for multilayer collection liquid structure, can set up the multilayer outside the thrust chamber shell and be used for refrigerated collection liquid structure promptly, and then improves collection liquid structure's cooling effect. In the case of a multilayer liquid collecting structure. For example, the gas collection structure may be disposed between two layers of the liquid collection structure.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
Another aspect of the invention provides a vehicle comprising at least one liquid engine as above.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011094208.6A CN112145316B (en) | 2018-01-23 | 2018-01-23 | Liquid engine |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011094208.6A CN112145316B (en) | 2018-01-23 | 2018-01-23 | Liquid engine |
| CN201810061907.7A CN108119260B (en) | 2018-01-23 | 2018-01-23 | Liquid engines and carriers |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810061907.7A Division CN108119260B (en) | 2018-01-23 | 2018-01-23 | Liquid engines and carriers |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112145316A CN112145316A (en) | 2020-12-29 |
| CN112145316B true CN112145316B (en) | 2021-07-23 |
Family
ID=62233238
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810061907.7A Active CN108119260B (en) | 2018-01-23 | 2018-01-23 | Liquid engines and carriers |
| CN202011094208.6A Active CN112145316B (en) | 2018-01-23 | 2018-01-23 | Liquid engine |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810061907.7A Active CN108119260B (en) | 2018-01-23 | 2018-01-23 | Liquid engines and carriers |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN108119260B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108119260A (en) * | 2018-01-23 | 2018-06-05 | 北京蓝箭空间科技有限公司 | Liquid Engines and Vehicles |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109595097B (en) * | 2018-10-29 | 2020-04-24 | 上海空间推进研究所 | Liquid oxygen and methane engine adopting plug-in valve and control method |
| CN113565652B (en) * | 2021-07-27 | 2022-08-19 | 中国人民解放军国防科技大学 | Multilayer fixed high-temperature fluid channel |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104632467A (en) * | 2015-01-12 | 2015-05-20 | 葛明龙 | Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof |
| CN104948347A (en) * | 2014-03-31 | 2015-09-30 | 北京航天动力研究所 | Thrust chamber collector with flow uniformizing function |
| CN105089852A (en) * | 2014-05-06 | 2015-11-25 | 中国航天科技集团公司第六研究院第十一研究所 | Combustion chamber inner liner cooling structure |
| CN105971768A (en) * | 2016-06-10 | 2016-09-28 | 中国人民解放军国防科学技术大学 | Self-pressurization supply system based on regenerative cooling |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1475163A1 (en) * | 1964-10-19 | 1969-01-23 | Dynamit Nobel Ag | Method and device for atomizing liquids, solutions, suspensions or solids in the form of dust, powder or the like. |
| CA945123A (en) * | 1970-12-11 | 1974-04-09 | Bernard Doin | Pyrotechnic gas generator |
| FR2893086B1 (en) * | 2005-11-09 | 2008-01-25 | Onera (Off Nat Aerospatiale) | HIGH PERFORMANCE THERMAL MACHINE |
| CN100570147C (en) * | 2008-01-17 | 2009-12-16 | 清华大学 | A Sweating Cooling Structure Using Laminates Using Strong Endothermic Reaction |
| CN208073634U (en) * | 2018-01-23 | 2018-11-09 | 陕西蓝箭航天技术有限公司 | Liquid engine and vehicle |
| CN108119260B (en) * | 2018-01-23 | 2023-12-05 | 陕西蓝箭航天技术有限公司 | Liquid engines and carriers |
-
2018
- 2018-01-23 CN CN201810061907.7A patent/CN108119260B/en active Active
- 2018-01-23 CN CN202011094208.6A patent/CN112145316B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104948347A (en) * | 2014-03-31 | 2015-09-30 | 北京航天动力研究所 | Thrust chamber collector with flow uniformizing function |
| CN105089852A (en) * | 2014-05-06 | 2015-11-25 | 中国航天科技集团公司第六研究院第十一研究所 | Combustion chamber inner liner cooling structure |
| CN104632467A (en) * | 2015-01-12 | 2015-05-20 | 葛明龙 | Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof |
| CN105971768A (en) * | 2016-06-10 | 2016-09-28 | 中国人民解放军国防科学技术大学 | Self-pressurization supply system based on regenerative cooling |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108119260A (en) * | 2018-01-23 | 2018-06-05 | 北京蓝箭空间科技有限公司 | Liquid Engines and Vehicles |
| CN108119260B (en) * | 2018-01-23 | 2023-12-05 | 陕西蓝箭航天技术有限公司 | Liquid engines and carriers |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108119260A (en) | 2018-06-05 |
| CN108119260B (en) | 2023-12-05 |
| CN112145316A (en) | 2020-12-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US3024606A (en) | Liquid cooling system for jet engines | |
| CN112145316B (en) | Liquid engine | |
| US11952965B2 (en) | Rocket engine's thrust chamber assembly | |
| US6481641B1 (en) | Fuel injector assembly having a heat exchanger for fuel preheating | |
| US2958183A (en) | Rocket combustion chamber | |
| CN108138697B (en) | Improved liquid oxygen-liquid propylene rocket engine | |
| US20110005193A1 (en) | Method and apparatus for simplified thrust chamber configurations | |
| US5832719A (en) | Rocket thrust chamber | |
| JP5685250B2 (en) | Rocket engine using cryogenic propellant | |
| JP2008513654A (en) | Heat exchanger for hydrogen-operated fuel supply system | |
| JPH08327050A (en) | Enclosure cooled by transpiration and manufacture of said enclosure | |
| WO2020154809A1 (en) | Rocket engines | |
| CN208073634U (en) | Liquid engine and vehicle | |
| RU124320U1 (en) | MIXING HEAD OF A LIQUID ROCKET ENGINE COMBUSTION CHAMBER | |
| CN118111120B (en) | Gas generator for aerospace engine combustion-heat exchange integrated helium heater | |
| KR102468746B1 (en) | Combustor inclduing heat exchanging structure and rocket including the same | |
| RU2171388C2 (en) | Chamber of liquid-prpellant rocket engine | |
| CN111237087B (en) | Micro-pore plate active and passive composite cooling structure for aerospace power and cooling method | |
| US3439502A (en) | Cooling of gas generators | |
| US3029602A (en) | Combustion chambers | |
| RU2728657C1 (en) | Chamber of liquid-propellant rocket engine operating on gas-free generator circuit (embodiments) | |
| RU2841343C1 (en) | Modular liquefied gas gasifier, embodiments | |
| JP2845563B2 (en) | Heat exchanger | |
| JPH04167A (en) | Heat exchanger | |
| FR3106373A1 (en) | INJECTOR FOR A TURBOMACHINE |
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: 20240517 Address after: 100076 H1, AVIC International Plaza, No.13 Ronghua South Road, Daxing District, Beijing Economic and Technological Development Zone Patentee after: Blue Arrow Space Technology Co.,Ltd. Country or region after: China Address before: 710077 East Building, four floor, aerospace science and technology, civil and integration innovation center, 32 United South Road, Xi'an, Shaanxi Patentee before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Country or region before: China |