CN114750965A - Cooling device based on bionic veins - Google Patents
Cooling device based on bionic veins Download PDFInfo
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- CN114750965A CN114750965A CN202210670813.6A CN202210670813A CN114750965A CN 114750965 A CN114750965 A CN 114750965A CN 202210670813 A CN202210670813 A CN 202210670813A CN 114750965 A CN114750965 A CN 114750965A
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- cooling
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- active cooling
- bottom edges
- flow
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/024—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising cooling means
Abstract
The invention belongs to the technical field of active cooling, and discloses a cooling device based on bionic veins. The cooling device comprises a fuel feeding cylinder, a cooling assembly and a fuel collecting cylinder which are sequentially connected from front to back, and further comprises a monitoring system; the two ends of the cooling component are provided with confluence cavities, the front end and the rear end of the cooling component are respectively connected with a cooling liquid inlet pipeline and a cooling liquid outlet pipeline, and the middle section of the cooling component is wrapped by a cooling section; the middle section is internally provided with an active cooling inner flow passage which comprises main cooling flow passages which are parallel to each other, and the main cooling flow passages are communicated through branch cooling flow passages. The main cooling flow channels are separated by intermittent partitions, the cross sections of the intermittent partitions are in the shape of alternately arranged isosceles trapezoids with the long upper bottom edge and the short lower bottom edge and isosceles trapezoids with the long upper bottom edge and the short lower bottom edge, and the adjacent main cooling flow channels are in staggered arrangement. The cooling device adopts fuel carried by the hypersonic aircraft as coolant, so that the temperature of a cold section is effectively reduced, and the cooling efficiency of an engine active cooling structure and the thermal safety of the engine structure are improved.
Description
Technical Field
The invention belongs to the technical field of active cooling, and particularly relates to a cooling device based on bionic veins.
Background
In the high-speed flight process of the hypersonic aircraft, the high-speed flow of the airflow can bring huge heat burden to the hypersonic aircraft, and at present, the heat protection schemes of the hypersonic aircraft mainly include three main categories, namely active heat protection, semi-active heat protection and passive heat protection. The convective cooling technique in the active thermal protection technique has attracted much attention in recent years, and one of them is active cooling. Active cooling takes away most of the heat through the coolant.
The coolant carried by the hypersonic aerocraft can greatly increase the load of the aerocraft, and the flight performance of the hypersonic aerocraft is influenced. In recent years, researches show that the engine body is provided with fuel as a coolant, and the coolant carried by the engine body is replaced by the coolant carried by the engine body, so that the engine has the following advantages: on the one hand, no additional load is added; on the other hand, the fuel enters the combustion chamber of the engine to be combusted after absorbing heat, the heat absorbed by the fuel is released again, the aerodynamic heat is converted into the thrust of the aircraft, and the fuel can be greatly saved or the weight of the hypersonic aircraft can be reduced.
The fuel carried by the engine body is used as the coolant, the convection cooling principle is utilized, the coolant flows through the cooling flow channel in the engine body to take away heat, the temperature of the fuel is increased, the fuel enters the engine system of the hypersonic aircraft again, the combustion efficiency of the engine system is improved, although the temperature of the fuel is increased, the engine system runs under a higher temperature condition, the fuel is still in the material temperature limit of the engine system, and the safety and the service life of the engine system are not influenced.
Currently, there is a need to develop a cooling device based on bionic veins, which can improve convection efficiency and control the temperature entering into the engine system.
Disclosure of Invention
The invention aims to solve the technical problem of providing a cooling device based on bionic veins.
The invention relates to a bionic vein-based cooling device, which is characterized by comprising a fuel feeding cylinder, a cooling component, a fuel collecting cylinder and a monitoring system, wherein the fuel feeding cylinder, the cooling component and the fuel collecting cylinder are sequentially connected from front to back;
the two ends of the cooling assembly are provided with confluence cavities, the confluence cavity at the front end is connected with a cooling liquid inlet pipeline, the confluence cavity at the rear end is connected with a cooling liquid outlet pipeline, and the middle section is an active cooling section; an active cooling inner runner is arranged in the active cooling section;
the active cooling inner flow channel comprises main cooling flow channels which are parallel to each other, and the main cooling flow channels are communicated through branch cooling flow channels; the main cooling flow channels are separated by intermittent partitions, the cross sections of the intermittent partitions are in the shapes of isosceles trapezoids with short upper bottom edges and short lower bottom edges and isosceles trapezoids with long upper bottom edges and short lower bottom edges which are alternately arranged from front to back, and the adjacent main cooling flow channels are in the shapes of corresponding staggered isosceles trapezoids with short upper bottom edges and short lower bottom edges or isosceles trapezoids with long upper bottom edges and short lower bottom edges;
The monitoring system comprises a pressure sensor, a temperature sensor, a flow sensor, a speed sensor, an AD converter and a control computer, wherein the pressure sensor, the temperature sensor, the flow sensor and the speed sensor are installed on the wall surface of the active cooling section to measure the pressure, the temperature, the flow and the flow speed of fuel in the active cooling section, and signals of the sensors are transmitted to the control computer of the monitoring system for acquisition and display through AD conversion.
Furthermore, turbulence protrusions are arranged at two ends of the long bottom side of the isosceles trapezoid, the cross section of each turbulence protrusion is circular, oval, rectangular, square or polygonal, the number of sides of each polygon is N, and N is not less than 5.
Furthermore, the thickness of the active cooling section is smaller by one order of magnitude than that of the section needing to be cooled, the active cooling section is in a strip shape, a flat plate shape or a cylinder shape matched with the surface shape of the section needing to be cooled, the strip-shaped active cooling section is wrapped on the surface of the cylinder-shaped section needing to be cooled in a winding mode, the flat plate-shaped active cooling section covers the surface of the flat section needing to be cooled, and the cylinder-shaped active cooling section is sleeved on the surface of the cylinder-shaped section needing to be cooled.
The active cooling inner flow channel in the bionic vein-based cooling device comprises a main cooling flow channel and a branch cooling flow channel, wherein the adjacent main cooling flow channels are not directly communicated and are connected through the branch cooling flow channel, the flow direction of the branch cooling flow channel and the flow direction in the main cooling flow channel form an acute angle alpha, and turbulent flow bulges are respectively arranged at the inlet of the branch cooling flow channel and the outlet of the branch cooling flow channel.
The active cooling inner flow channel in the cooling device based on the bionic veins has the following advantages:
1. the heat exchange can be enhanced more efficiently, and the maximum temperature and the average temperature of the cooled structure can be directly reduced.
2. And the branch cooling flow channel is adopted, so that the structural weight is reduced, and the structure is lighter.
3. The cross section of the turbulence protrusion can be in any shape such as round, oval, rectangular, square or polygonal with turbulence function, so that the turbulence protrusion is convenient for designers to select, and has more technical characteristics, namely, the machining manufacturability is outstanding.
The active cooling inner flow channel in the bionic vein-based cooling device increases the heat exchange area, changes the flowing condition of cooling liquid, increases the turbulence degree of the cooling liquid, improves the heat transfer coefficient, strengthens the heat transfer between the cooling liquid and a cooling structure, and simultaneously reduces the weight of the cooling flow channel structure.
According to the cooling device based on the bionic veins, the fuel feeding cylinder feeds high-pressure constant-temperature fuel into the cooling liquid inlet pipeline, the fuel carries out convection heat exchange with a section needing to be cooled through the active cooling section, the discharged high-pressure high-temperature fuel enters the fuel collecting cylinder to be collected and then enters the engine combustion chamber of the hypersonic aircraft to be combusted, and the monitoring system monitors the pressure, flow speed and temperature data of the fuel.
The cooling device based on the bionic veins adopts the fuel carried by the hypersonic aircraft as the coolant, can effectively reduce the temperature of a cold section, improves the cooling efficiency of an engine active cooling structure, improves the thermal safety of the engine structure, and has engineering popularization value.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other embodiments and drawings can be obtained according to the embodiments shown in the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a cooling device based on bionic veins;
FIG. 2 is a schematic view of a cooling assembly of the bionic vein-based cooling device of the present invention;
FIG. 3 is a perspective view of an active cooling inner flow passage of a cooling assembly in the bionic vein-based cooling device of the invention;
FIG. 4a is a schematic structural diagram of an active cooling inner flow passage of a cooling assembly in the bionic vein-based cooling device of the present invention;
FIG. 4b is a schematic structural diagram (partially enlarged view II) of the active cooling inner flow channel of the cooling assembly in the bionic vein-based cooling device of the present invention;
FIG. 5a is a schematic diagram of three configurations of actively cooled inner channels;
FIG. 5b is a comparison of cooling effects obtained for three configurations of actively cooled inner flow channel structures;
FIG. 5c is a temperature cloud of the heating surface obtained for three configurations of actively cooled inner flow channel structures.
In the figure, 1. a cooling liquid inlet pipeline; 2. a manifold chamber; 3. an active cooling section; 4. a coolant outlet conduit; 5. actively cooling the inner runner; 6. a fuel feed barrel; 7. a cooling assembly; 8. a fuel collection canister; 9. and (5) monitoring the system.
501. A primary cooling flow path; 502. a branch cooling channel; 503. the inlet turbulent flow bulge of the branch cooling flow channel; 504. the outlet of the branch cooling channel is provided with a turbulent flow bulge.
Detailed Description
The technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and fig. 2, the cooling device based on bionic veins comprises a fuel feeding cylinder 6, a cooling component 7, a fuel collecting cylinder 8 and a monitoring system 9, wherein the fuel feeding cylinder, the cooling component 7 and the fuel collecting cylinder are sequentially connected from front to back;
the two ends of the cooling assembly 7 are provided with confluence cavities 2, the confluence cavity 2 at the front end is connected with a cooling liquid inlet pipeline 1, the confluence cavity 2 at the rear end is connected with a cooling liquid outlet pipeline 4, and the middle section is an active cooling section 3; an active cooling inner runner 5 is arranged in the active cooling section 3;
as shown in fig. 3, 4a, and 4b, the active cooling inner channel 5 includes mutually parallel main cooling channels 501, and the main cooling channels 501 are communicated with each other through a branch cooling channel 502; the main cooling flow channels 501 are separated by intermittent partitions, the cross sections of the intermittent partitions are in the shape of isosceles trapezoids with short upper bottom edges and short lower bottom edges and isosceles trapezoids with short upper bottom edges and short lower bottom edges which are alternately arranged from front to back, and the adjacent main cooling flow channels 501 are in the shape of corresponding staggered isosceles trapezoids with short upper bottom edges and short lower bottom edges or isosceles trapezoids with short upper bottom edges and short lower bottom edges;
The monitoring system 9 comprises a pressure sensor, a temperature sensor, a flow sensor, a speed sensor, an AD converter and a control computer, wherein the pressure sensor, the temperature sensor, the flow sensor and the speed sensor are arranged on the wall surface of the active cooling section 3 to measure the pressure, the temperature, the flow and the flow speed of the fuel in the active cooling section 3, and the signals of the sensors are transmitted to the control computer of the monitoring system 9 for collection and display through AD conversion.
Furthermore, turbulence protrusions are arranged at two ends of the long bottom side of the isosceles trapezoid, the cross section of each turbulence protrusion is circular, oval, rectangular, square or polygonal, the number of sides of each polygon is N, and N is not less than 5.
Further, the thickness of the active cooling section 3 is one order of magnitude smaller than the dimension of the section which needs to be cooled, the shape of the active cooling section 3 is a strip type, a flat type or a cylinder type matched with the shape of the surface of the section which needs to be cooled, the strip type active cooling section 3 is wrapped on the surface of the cylinder type section which needs to be cooled in a winding mode, the flat type active cooling section 3 covers the surface of the plane section which needs to be cooled, and the cylinder type active cooling section 3 is sleeved on the surface of the cylinder section which needs to be cooled.
Example 1
FIG. 5a shows 3 configurations of the active cooling inner channel 5, where configuration 1 is a DC cooling channel; the configuration 2 is a first vein bionic cooling flow channel, which comprises main cooling flow channels 501 and branch cooling flow channels 502, wherein the adjacent main cooling flow channels 501 are not directly communicated and are connected through the branch cooling flow channels 502, and the branch cooling flow channels 502 form an acute angle alpha with the flowing direction in the main cooling flow channels 501; the configuration 3 is a second vein bionic cooling channel, a branch cooling channel inlet turbulent flow protrusion 503 and a branch cooling channel outlet turbulent flow protrusion 504 are added on the basis of the first vein bionic cooling channel, the direction of the branch cooling channel 502 which keeps an acute angle with the flow direction in the main cooling channel 501 is defined as the flow direction of the branch cooling channel 502, the branch cooling channel inlet turbulent flow protrusion 503 and the branch cooling channel outlet turbulent flow protrusion 504 are respectively arranged at the inlet and the outlet of the branch cooling channel 502 in the flow direction, namely, the branch cooling channel inlet turbulent flow protrusion 503 and the branch cooling channel outlet turbulent flow protrusion 504 are designed at the intersection of the main cooling channel 501 and the branch cooling channel 502.
The coolant of each main cooling channel 501 is mixed through the branch cooling channel 502, and the heat exchange area and the turbulence degree of the coolant are increased by the turbulence protrusions. As can be seen in fig. 5b, the maximum temperature and the average temperature of configuration 1, configuration 2 and configuration 3 are successively lower. Fig. 5c shows that the cooling effects of the configuration 1, the configuration 2 and the configuration 3 are sequentially enhanced, which proves that the vein bionic cooling flow channel has a more efficient enhanced heat exchange effect, and the maximum temperature and the average temperature of the cooled surface can be remarkably reduced.
The branch cooling flow channel 502 is arranged, so that the bionic vein-based cooling device is lighter, the shape of the turbulent flow protrusion is limited to be a round shape, an oval shape, a rectangular shape, a square shape or a polygonal shape with a wider range, the number of the sides of the polygonal shape is N, N is more than or equal to 5, so that designers can select a more appropriate shape according to processing conditions, and the machining process is more outstanding. The cooling device based on bionic veins has engineering practicability when being used for hypersonic aircrafts.
Claims (3)
1. The cooling device based on the bionic veins is characterized by comprising a fuel feeding cylinder (6), a cooling component (7), a fuel collecting cylinder (8) and a monitoring system (9), wherein the fuel feeding cylinder, the cooling component and the fuel collecting cylinder are sequentially connected from front to back;
the two ends of the cooling assembly (7) are provided with a converging cavity (2), the converging cavity (2) at the front end is connected with a cooling liquid inlet pipeline (1), the converging cavity (2) at the rear end is connected with a cooling liquid outlet pipeline (4), and the middle section is an active cooling section (3); an active cooling inner runner (5) is arranged in the active cooling section (3);
the active cooling inner flow channel (5) comprises main cooling flow channels (501) which are parallel to each other, and the main cooling flow channels (501) are communicated with each other through branch cooling flow channels (502); the main cooling channels (501) are separated by intermittent partitions, the cross sections of the intermittent partitions are isosceles trapezoids with short upper bottom edges and short lower bottom edges and isosceles trapezoids with short upper bottom edges and short lower bottom edges which are alternately arranged from front to back, and the adjacent main cooling channels (501) are corresponding staggered isosceles trapezoids with short upper bottom edges and short lower bottom edges or isosceles trapezoids with short upper bottom edges and short lower bottom edges;
The monitoring system (9) comprises a pressure sensor, a temperature sensor, a flow sensor, a speed sensor, an AD converter and a control computer, wherein the pressure sensor, the temperature sensor, the flow sensor and the speed sensor are installed on the wall surface of the active cooling section (3) to measure the pressure, the temperature, the flow and the flow speed of fuel in the active cooling section (3), and signals of the sensors are transmitted to the control computer of the monitoring system (9) for collection and display through AD conversion.
2. The cooling device based on the bionic veins of claim 1 wherein two ends of the long bottom side of the isosceles trapezoid are provided with turbulence protrusions, the cross-sectional shape of the turbulence protrusions is circular, elliptical, rectangular, square or polygonal, the number of sides of the polygon is N, and N is not less than 5.
3. The bionic vein-based cooling device according to claim 1, wherein the thickness of the active cooling section (3) is smaller by an order of magnitude than that of the section to be cooled, the shape of the active cooling section (3) is a strip shape, a flat plate shape or a cylinder shape matched with the shape of the surface of the section to be cooled, the strip-type active cooling section (3) is wrapped on the surface of the section to be cooled in a winding manner, the flat-type active cooling section (3) covers the surface of the flat section to be cooled, and the cylinder-type active cooling section (3) is sleeved on the surface of the cylinder section to be cooled.
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| CN202210670813.6A CN114750965B (en) | 2022-06-15 | 2022-06-15 | Cooling device based on bionic veins |
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| CN202210670813.6A CN114750965B (en) | 2022-06-15 | 2022-06-15 | Cooling device based on bionic veins |
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