CN117329740B - Injection assembly and aircraft thermal management system - Google Patents
Injection assembly and aircraft thermal management system Download PDFInfo
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- CN117329740B CN117329740B CN202311609302.4A CN202311609302A CN117329740B CN 117329740 B CN117329740 B CN 117329740B CN 202311609302 A CN202311609302 A CN 202311609302A CN 117329740 B CN117329740 B CN 117329740B
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- 238000002347 injection Methods 0.000 title claims abstract description 136
- 239000007924 injection Substances 0.000 title claims abstract description 136
- 230000007423 decrease Effects 0.000 claims abstract description 20
- 239000007788 liquid Substances 0.000 claims description 82
- 238000001816 cooling Methods 0.000 claims description 68
- 238000001704 evaporation Methods 0.000 claims description 53
- 230000008020 evaporation Effects 0.000 claims description 53
- 238000000926 separation method Methods 0.000 claims description 48
- 230000006835 compression Effects 0.000 claims description 44
- 238000007906 compression Methods 0.000 claims description 44
- 230000002093 peripheral effect Effects 0.000 claims description 18
- 238000005338 heat storage Methods 0.000 claims description 17
- 238000009833 condensation Methods 0.000 claims description 11
- 230000005494 condensation Effects 0.000 claims description 11
- 230000005540 biological transmission Effects 0.000 claims description 10
- 238000002156 mixing Methods 0.000 abstract description 15
- 239000002826 coolant Substances 0.000 abstract description 4
- 230000005514 two-phase flow Effects 0.000 description 66
- 239000007789 gas Substances 0.000 description 45
- 238000004891 communication Methods 0.000 description 21
- 230000001105 regulatory effect Effects 0.000 description 16
- 230000000694 effects Effects 0.000 description 12
- 230000001965 increasing effect Effects 0.000 description 11
- 230000003068 static effect Effects 0.000 description 8
- 239000000446 fuel Substances 0.000 description 4
- 238000002309 gasification Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000005057 refrigeration Methods 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
- 239000000110 cooling liquid Substances 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000013526 supercooled liquid Substances 0.000 description 2
- 238000009834 vaporization Methods 0.000 description 2
- 230000008016 vaporization Effects 0.000 description 2
- 239000002918 waste heat Substances 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000010365 information processing Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B41/00—Fluid-circulation arrangements
- F25B41/40—Fluid line arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B43/00—Arrangements for separating or purifying gases or liquids; Arrangements for vaporising the residuum of liquid refrigerant, e.g. by heat
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B5/00—Compression machines, plants or systems, with several evaporator circuits, e.g. for varying refrigerating capacity
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
- H05K7/20327—Accessories for moving fluid, for connecting fluid conduits, for distributing fluid or for preventing leakage, e.g. pumps, tanks or manifolds
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
- H05K7/20354—Refrigerating circuit comprising a compressor
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Power Engineering (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention relates to the technical field of aircraft thermal management, in particular to an injection assembly and an aircraft thermal management system. The injection assembly includes: the injection shell unit comprises a first shell part, a second shell part, a third shell part, a fourth shell part and a fifth shell part which are sequentially connected. The cross-sectional areas of the second and fifth shell portions decrease gradually in a direction in which the first shell portion extends toward the fifth shell portion (i.e., a first direction), and the cross-sectional area of the third shell portion increases gradually in the first direction. The first ejector tube extends into the internal cavity of the first shell portion. The first injection pipe is fixedly connected with the first shell part. The cross-sectional area of one end of the first ejector tube adjacent the open end of the first shell portion is greater than the cross-sectional area of the other end. The second ejector pipe penetrates through the side wall of the first shell part and is communicated with the inner cavity of the first shell part. The third injection pipe penetrates through the side wall of the joint of the second shell part and the third shell part and is communicated with the inner cavities of the second shell part and the third shell part. Thus, the problem of uneven mixing of the cooling medium is solved.
Description
Technical Field
The invention relates to the technical field of aircraft thermal management, in particular to an injection assembly and an aircraft thermal management system.
Background
In order to achieve high accuracy of an aircraft, various on-board electronic devices are provided in the aircraft. The onboard electronic equipment with high computing capability can inevitably generate heat in the information processing process, and if the equipment is overheated, the aircraft can be abnormal or even out of control. Limiting the heat of the on-board electronics by the thermal management system is one of the indispensable ways. For the heat generated by large-scale airborne electronic equipment during operation, the heat management system can generally adopt a liquid cooling mode, so that the cooling liquid in the heat dissipation device circularly absorbs the heat of the airborne electronic equipment, the cooling liquid after heat absorption is conveyed to the evaporation circulation refrigeration loop, and the evaporation circulation refrigeration loop dissipates the heat to fuel oil, air or other available heat sinks.
The aircraft has a plurality of parts which need to be cooled, the temperatures of the parts are different, and the pressure, the temperature and the humidity of the cooling medium after the cooling of the different parts are different. If the cooling medium is directly mixed and input into the gas-liquid separation unit, the gas-liquid separation is possibly incomplete, and the compressor is enabled to work with liquid, so that the refrigeration effect is affected and even the compressor is damaged.
Disclosure of Invention
The invention provides an injection assembly and an aircraft thermal management system for solving the problem of uneven mixing of cooling media.
In a first aspect, the present invention provides an ejector assembly comprising:
the injection shell unit comprises a first shell part, a second shell part, a third shell part, a fourth shell part and a fifth shell part; the first shell part, the second shell part, the third shell part, the fourth shell part and the fifth shell part are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the second shell portion gradually decreases in a first direction, the cross-sectional area of the third shell portion gradually increases in the first direction, and the cross-sectional area of the fifth shell portion gradually decreases in the first direction; wherein the first direction is a direction extending from the first shell portion to the fifth shell portion;
the first injection pipe extends into the inner cavity of the first shell part from the outside of the opening end of the first shell part; one end of the first injection pipe is fixedly connected with the opening end of the first shell part; the cross section area of one end of the first injection pipe close to the opening end of the first shell part is larger than that of the other end;
The second injection pipe penetrates through the side wall of the first shell part and is communicated with the inner cavity of the first shell part;
the third injection pipe penetrates through the side wall of the joint of the second shell part and the third shell part and is communicated with the inner cavity of the second shell part and the inner cavity of the third shell part.
In some embodiments, a centerline of the first ejector tube coincides with a centerline of the first shell portion; the center line of the second injection pipe is arranged at intervals with the center line of the first shell part.
In some embodiments, the cross-sectional area of the second ejector at one end of the exterior of the first shell portion is greater than the cross-sectional area of the other end.
In some embodiments, the second ejector tube extends from one end external to the first shell portion to the other end in a direction away from the first ejector tube.
In some embodiments, a centerline of the third ejector tube perpendicularly intersects a centerline of the second shell portion.
In some embodiments, the cross-sectional area of the third ejector at one end of the second shell portion is smaller than the cross-sectional area of the other end.
In some embodiments, the injection assembly further comprises a sixth shell portion, a seventh shell portion, a fourth injection conduit; the first shell part, the second shell part, the third shell part, the fourth shell part, the fifth shell part, the sixth shell part and the seventh shell part are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the sixth shell portion gradually increases in the first direction, and the cross-sectional area of the seventh shell portion decreases in the first direction; the fourth injection pipe passes through the side wall of the joint of the fifth shell part and the sixth shell part and is communicated with the internal cavities of the fifth shell part and the sixth shell part.
In some embodiments, a centerline of the fourth ejector tube perpendicularly intersects a centerline of the fifth shell portion.
In some embodiments, a cross-sectional area of the fourth ejector at one end of the fifth shell portion exterior is less than a cross-sectional area of the other end.
In a second aspect, the present invention provides an aircraft thermal management system comprising:
the compression assembly comprises a gas-liquid separation unit, a compression unit, a driving unit and a shaft cooling unit; the driving unit drives the compressing unit to compress a first temperature control medium; an inlet of the compression unit is communicated with the gas-liquid separation unit, and an opening end of the fifth shell part far away from the fourth shell part is communicated with the gas-liquid separation unit; the shaft cooling unit is arranged on the periphery of a transmission shaft of the driving unit, and an outlet of the shaft cooling unit is communicated with the third injection pipe;
a condensing assembly, an inlet of the first temperature control medium of the condensing assembly is communicated with an outlet of the compression unit;
the evaporation assembly comprises a heat regenerator, a first evaporation unit and a second evaporation unit; the outlet of the first temperature control medium of the condensation component is communicated with the liquid inlet of the heat regenerator; the liquid outlet of the heat regenerator is respectively communicated with the inlet of the shaft cooling unit, the inlet of the first evaporation unit and the inlet of the second evaporation unit; the outlet of the first evaporation unit is communicated with the first injection pipe; and the outlet of the second evaporation unit is communicated with the second injection pipe.
In some embodiments, the injection assembly further comprises a sixth shell portion, a seventh shell portion, a fourth injection conduit; the first shell part, the second shell part, the third shell part, the fourth shell part, the fifth shell part, the sixth shell part and the seventh shell part are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the sixth shell portion gradually increases in the first direction, and the cross-sectional area of the seventh shell portion decreases in the first direction; the fourth injection pipe passes through the side wall of the joint of the fifth shell part and the sixth shell part and is communicated with the internal cavities of the fifth shell part and the sixth shell part; the evaporation assembly further comprises a heat storage and exchange unit; the liquid outlet of the heat regenerator is respectively communicated with the inlet of the shaft cooling unit, the inlet of the first evaporation unit, the inlet of the second evaporation unit and the inlet of the first temperature control medium of the heat storage and exchange unit; and an outlet of the first temperature control medium of the heat storage and exchange unit is communicated with the fourth injection pipe.
In order to solve the problem of uneven mixing of cooling medium, the invention has the following advantages:
1. the first injection pipe can enable the first temperature control medium to rapidly expand and atomize after entering the first shell part, so that the temperature of the first temperature control medium is reduced.
2. The first temperature control medium from the first injection pipe and the second injection pipe can be mixed into a high-flow low Wen Jigao dryness two-phase flow, and the flow is accelerated to a first direction through the second shell part. The first temperature control medium from the first shell part is extruded along the inclined direction by the first temperature control medium from the second injection pipe at the arrangement angle of the second injection pipe, so that two first temperature control mediums collide back and forth on the inner peripheral wall of the first shell part, and full mixing is realized.
3. The high-flow low Wen Jigao dryness two-phase flow can reduce the temperature of the first temperature control medium in the third injection pipe, and the arrangement angle of the third injection pipe can enable the first temperature control medium in the first injection pipe, the second injection pipe and the third injection pipe to collide back and forth in the inner peripheral wall, so that the two-phase flow is fully mixed.
Drawings
FIG. 1 illustrates a schematic view of an ejector assembly of one embodiment;
FIG. 2 shows a schematic view of an ejector assembly of another embodiment;
FIG. 3 shows a schematic view of an ejector assembly of another embodiment;
FIG. 4 illustrates a schematic view of an aircraft thermal management system of an embodiment.
Reference numerals: 10 a compression assembly; 11 a compression unit; a 111 impeller inlet; 112 compressing the impeller; 113 impeller outlet; 12 a driving unit; 121 a stator; 122 a rotor; 123 drive shafts; 124 bearings; 13 shaft cooling units; a 131-axis cooling tube; 132 shaft cooling chamber; 14 a gas-liquid separation unit; 141 separation chamber; 142 separation inlet; 143 a first separation outlet; 144 a second separation outlet; 20 a condensing assembly; a 21 condenser; 22 cold source supply units; 221 a first pump; 222 cold source box; 30 an evaporation assembly; 31 a regenerator; 32 a first evaporation unit; 321 a first regulating valve; 322 a first expansion valve; 323 a first cold plate; 324 a first temperature equalization plate; a second evaporation unit 33; 331 a second regulating valve; 332 a second expansion valve; 333 second cold plate; 334 a second temperature equalization plate; 34 a heat storage and exchange unit; 341 a third regulating valve; 342 a third expansion valve; 343 a third cold plate; 344 a second pump; 345 effusion cell; 346 heat exchanger; 40, injecting an assembly; 41 an ejector housing unit; 411 a first shell portion; 412 a second shell portion; 413 a third shell portion; 414 a fourth shell portion; 415 a fifth shell portion; 416 a sixth shell portion; 417 a seventh shell portion; 4171 an isodiametric segment; 4172 a reducing section; 42 a first ejector tube; 43 a second ejector tube; 44 a third ejector tube; 45 a fourth ejector tube.
Detailed Description
The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.
As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment".
The embodiment discloses an injection assembly 40, as shown in fig. 1, 2 and 3, may include:
the injection housing unit 41, the injection housing unit 41 comprises a first housing part 411, a second housing part 412, a third housing part 413, a fourth housing part 414 and a fifth housing part 415; the first shell 411, the second shell 412, the third shell 413, the fourth shell 414 and the fifth shell 415 are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the second shell portion 412 gradually decreases in the first direction, the cross-sectional area of the third shell portion 413 gradually increases in the first direction, and the cross-sectional area of the fifth shell portion 415 gradually decreases in the first direction; wherein the first direction is a direction extending from the first shell portion 411 to the fifth shell portion 415;
The first injection pipe 42, the first injection pipe 42 extends into the inner cavity of the first shell 411 from the outside of the opening end of the first shell 411; one end of the first injection pipe 42 is fixedly connected with the opening end of the first shell 411; the cross-sectional area of one end of the first ejector tube 42 adjacent the open end of the first shell portion 411 is greater than the cross-sectional area of the other end;
the second injection pipe 43 penetrates through the side wall of the first shell 411 and is communicated with the cavity inside the first shell 411;
and the third injection pipe 44 penetrates through the side wall of the joint of the second shell part 412 and the third shell part 413, and is communicated with the inner cavities of the second shell part 412 and the third shell part 413.
In this embodiment, the aircraft is a modern device with extremely high precision, in which numerous on-board electronic devices are mounted. In order to ensure high accuracy of the aircraft, the operational capabilities of the on-board electronics may be very high. When these on-board electronic devices are operated, heat is inevitably generated. The heat generated by the equipment at different positions is different, and the temperature, the pressure and the humidity of the first temperature control medium after the cooling of the different equipment are also different. In order to avoid that the cooling effect is insufficient and even the compressor is damaged due to the operation of the compressor with liquid, an injection assembly 40 is further provided. As shown in fig. 1, 2, and 3, the injection assembly 40 may include an injection housing unit 41. The injection housing unit 41 may include a first housing part 411, a second housing part 412, a third housing part 413, a fourth housing part 414, and a fifth housing part 415 which are sequentially and fixedly connected, and may present a hollow tubular body with two open ends after connection is completed. The first shell portion 411 may be a hollow tubular body having a constant cross-sectional area. The cross-sectional area of the second shell portion 412 gradually decreases in a direction in which the first shell portion 411 extends toward the fifth shell portion 415 (i.e., a first direction), and when the first temperature control medium flows from an abutting end of the second shell portion 412 with the first shell portion 411 to an end of the second shell portion 412 away from the first shell portion 411, the gradually decreasing cross-sectional area can decrease the static pressure and increase the flow velocity of the first temperature control medium so as to pass through rapidly. The cross-sectional area of the third shell portion 413 may gradually increase in the first direction, and when the first temperature control medium flows from the end of the third shell portion 413 adjacent to the first shell portion 411 toward the end of the third shell portion 413 remote from the first shell portion 411, the gradually increasing cross-sectional area may slow down the flow rate of the first temperature control medium and increase the static pressure. The fourth shell portion 414 may be a tubular body having the same cross-sectional area as the end of the third shell portion 413 remote from the first shell portion 411, and may provide a buffer space for the first temperature control medium when the flow rate of the first temperature control medium is large. The cross-sectional area of the fifth shell portion 415 may gradually decrease in the first direction, and when the first temperature control medium flows from the abutting end of the fifth shell portion 415 with the first shell portion 411 to the end of the fifth shell portion 415 away from the first shell portion 411, the gradually decreasing cross-sectional area may decrease the static pressure of the first temperature control medium and increase the flow velocity, so as to pass through rapidly.
The injection assembly 40 may also include a first injection conduit 42. The first injection pipe 42 may be a tubular body having different diameters at both ends, and both ends have a smaller diameter than the first shell portion 411. The small diameter end of the first ejector tube 42 may extend into the interior cavity of the first shell portion 411 from an end of the first shell portion 411 remote from the fifth shell portion 415. The outer peripheral wall of the large diameter end of the first ejector tube 42 may be fixedly connected with the opening of the first shell portion 411 at the end far from the fifth shell portion 415, thereby improving the overall strength and enhancing the sealing property. When the large-flow high-dryness two-phase flow flows from the large-diameter end of the first injection pipe 42 to the small-diameter end of the first injection pipe 42, the flow speed and the pressure can be gradually increased, and a high-pressure state is formed. After flowing to the first shell 411 through the first ejector tube 42, the large space of the first shell 411 can allow the pressure of the high-dryness two-phase flow to be suddenly reduced, so that the two-phase flow is rapidly expanded and vaporized, and the temperature is reduced.
The injection assembly 40 may also include a second injection tube 43. One end of the second ejector tube 43 may extend from the outer peripheral wall of the first ejector tube 42 into the interior cavity of the first housing portion 411 so as to communicate with the interior cavity of the first housing portion 411. When the low-flow low-dryness low-temperature two-phase flow flows from the end of the second injection pipe 43 far away from the first shell 411 to the end of the second injection pipe 43 near the first shell 411, the flow speed and the pressure can be gradually increased, and a high-pressure state is formed. After flowing through the second ejector tube 43 to the first shell portion 411, the large space of the first shell portion 411 can allow the pressure of the low-dryness two-phase flow to be suddenly reduced, so that the two-phase flow is rapidly expanded and vaporized, and the temperature is reduced. The two-phase flow from the first eductor tube 42 may be mixed with the two-phase flow from the second eductor tube 43 into a high flow low Wen Jigao dryness two-phase flow. The central axis of the second ejector tube 43 can be obliquely arranged with the central axis of the first shell 411, and the low-flow low-dryness low-temperature two-phase flow from the second ejector tube 43 can extrude the high-flow high-dryness two-phase flow from the first shell 411 along the oblique direction, so that two first temperature control mediums collide back and forth on the inner peripheral wall of the first shell 411, complete mixing is realized, and the high-flow low-Wen Jigao dryness two-phase flow is formed.
The injection assembly 40 may also include a third injection conduit 44. The third ejector 44 may be a tubular body having a different diameter at each end. The large diameter end of the third ejector 44 may extend from the abutting portions of the second and third housing portions 412, 413 into the internal cavities of the second and third housing portions 412, 413 so as to communicate with the internal cavities of the second and third housing portions 412, 413. When the small-flow high-temperature and high-dryness superheated gas flows from the small-diameter end of the third injection pipe 44 to the large-diameter end of the third injection pipe 44, the flow speed of the superheated gas can be reduced, and the static pressure is increased. At the moment, the mixed high-flow low Wen Jigao dryness two-phase flow is mixed with the low-flow high-temperature high-dryness superheated gas, so that the temperature of the low-flow high-temperature high-dryness superheated gas is reduced. The low-flow high-temperature and high-dryness superheated gas is enabled to be low in flow speed, so that the low-flow high-dryness superheated gas and the high-flow low-Wen Jigao dryness two-phase flow can be promoted to be uniformly mixed. The third ejector pipe 44 may be disposed on the opposite side of the second ejector pipe 43, so that the low-flow high-temperature and high-dryness superheated gas from the third ejector pipe 44 may extrude the mixed high-flow low-Wen Jigao dryness two-phase flow to the inner peripheral wall of the third shell 413 far away from the side of the third ejector pipe 44, so that the mixed first temperature control medium from the first ejector pipe 42, the second ejector pipe 43 and the third ejector pipe 44 collides back and forth in the inner peripheral wall of the third shell 413, thereby further fully mixing.
In some embodiments, as shown in fig. 2 and 3, the centerline of the first ejector 42 coincides with the centerline of the first shell portion 411; the center line of the second ejector tube 43 is spaced from the center line of the first housing portion 411.
In this embodiment, as shown in fig. 2 and 3, when the high-flow rate and high-dryness two-phase flow flows from the large diameter end to the small diameter end of the first injection pipe 42, the pressure thereof gradually increases, and then flows to the large space first shell 411, the pressure of the high-flow rate and high-dryness two-phase flow suddenly decreases, so that the high-flow rate and high-dryness two-phase flow can be rapidly expanded and atomized and the temperature can be reduced. The central axis of the first ejector pipe 42 may coincide with the central axis of the first shell 411, so that the high-flow high-dryness two-phase flow may be fully and uniformly expanded and atomized in the first shell 411, so as to be convenient to mix with other first temperature control media. When the small-flow low-dryness low-temperature two-phase flow flows from the large-diameter end to the small-diameter end of the second injection pipe 43, the pressure of the small-flow low-dryness low-temperature two-phase flow gradually increases, and then flows to the large-space first shell 411, the pressure of the small-flow low-dryness low-temperature two-phase flow suddenly decreases, and the small-flow low-dryness low-temperature two-phase flow can be rapidly expanded and atomized and the temperature can be reduced. The center line of the second ejector tube 43 may be disposed at an interval from the center line of the first shell portion 411, so that the center line of the second ejector tube 43 may be parallel to the tangential direction of the inner peripheral surface of the first shell portion 411, and may be offset toward the center line of the first shell portion 411, and the center line of the second ejector tube 43 may be disposed obliquely to the center line of the first shell portion 411. The low-flow low-dryness low-temperature two-phase flow passes through the second injection pipe 43 and then collides with the high-flow high-dryness two-phase flow in a spiral state in a staggered way. In this way, the two first temperature control mediums can be uniformly mixed to form a high-flow low Wen Jigao dryness two-phase flow, and the two first temperature control mediums are mutually pulled to further break up, split and accelerate gasification, so that the mixing effect can be optimized.
In some embodiments, as shown in FIGS. 1 and 2, the cross-sectional area of the second ejector 43 at one end is greater than the cross-sectional area of the other end outside the first housing portion 411.
In this embodiment, as shown in fig. 1 and 2, the second ejector 43 may be a tubular body having different diameters at both ends, and the diameter of the second ejector 43 at one end outside the first casing 411 may be larger than the diameter of the other end. The large diameter end of the second ejector tube 43 may be connected to a large diameter cooling tube, thereby filling more of the first temperature control medium and improving cooling efficiency. When the high-flow high-dryness two-phase flow flows from the large-diameter end to the small-diameter end of the second ejector pipe 43, the pressure of the low-flow low-dryness low-temperature two-phase flow is gradually increased, and the flow speed is increased. When the low-flow low-dryness low-temperature two-phase flow reaches the first shell 411 of the large space, the pressure is suddenly reduced, the expansion and vaporization can be fast carried out, and the temperature is further reduced.
In some embodiments, as shown in FIGS. 1 and 2, the second ejector 43 extends from one end outside the first housing portion 411 to the other end in a direction away from the first ejector 42.
In this embodiment, as shown in fig. 1 and 2, when the low-flow low-dryness low-temperature two-phase flow flows from the second ejector tube 43 to the first shell 411, the second ejector tube 43 may extend from one end located outside the first shell 411 to the other end in a direction away from the first ejector tube 42, so that the low-flow low-dryness low-temperature two-phase flow and the high-flow high-dryness two-phase flow may be intersected to form a high-flow low Wen Jigao dryness two-phase flow close to pure gas, and rotate along the inner peripheral wall of the first shell 411, and flow to the third ejector tube 44, so that the low-flow high-dryness high-temperature superheated gas of the high-flow low Wen Jigao dryness two-phase flow close to pure gas is cooled efficiently and mixed with the low-flow high-dryness superheated gas of the third ejector tube 44.
In some embodiments, as shown in FIGS. 1 and 2, the centerline of the third ejector 44 perpendicularly intersects the centerline of the second shell portion 412.
In this embodiment, as shown in fig. 1 and 2, the center line of the third ejector pipe 44 may perpendicularly intersect with the center line of the second shell portion 412, so that the low-flow high-temperature and high-dryness superheated gas may be perpendicularly input into the cavities of the second shell portion 412 and the third shell portion 413, and thus the low-flow high-dryness superheated gas and the high-flow low-Wen Jigao dryness two-phase flow are mixed as much as possible, and rapid cooling is achieved. The mixed first temperature control medium from the first injection pipe 42, the second injection pipe 43 and the third injection pipe 44 can collide with the inner peripheral wall of the third shell 413 with larger force, so that the gasification effect is further optimized.
In some embodiments, as shown in FIGS. 1 and 2, the cross-sectional area of the third ejector 44 at one end of the exterior of the second housing portion 412 is smaller than the cross-sectional area of the other end.
In this embodiment, as shown in fig. 1 and 2, the third ejector 44 may be a tubular body having different diameters at both ends, and the diameter of the third ejector 44 at one end outside the second shell portion 412 and the third shell portion 413 may be smaller than the diameter of the other end. When the small-flow high-temperature superheated gas flows from the small-diameter end to the large-diameter end of the third injection pipe 44, the static pressure and the flow speed of the first temperature control medium are gradually increased and reduced, then the first temperature control medium of the incoming large-flow low Wen Jigao dryness (nearly pure gas state) two-phase flow is heated and extruded towards the opposite side direction of the third injection pipe 44, and the mixture is mixed in the inner cavities of the third shell 413 and the fourth shell 414, so that the subsequent steps are convenient to carry out.
In some embodiments, as shown in fig. 1 and 2, the injection assembly 40 further comprises a sixth housing portion 416, a seventh housing portion 417, and a fourth injection conduit 45; the first shell 411, the second shell 412, the third shell 413, the fourth shell 414, the fifth shell 415, the sixth shell 416 and the seventh shell 417 are fixedly connected in sequence to form a hollow tubular body with two open ends; the cross-sectional area of the sixth shell portion 416 increases gradually in the first direction, and the cross-sectional area of the seventh shell portion 417 decreases in the first direction; the fourth ejector 45 passes through the side wall of the junction of the fifth housing part 415 and the sixth housing part 416 and is communicated with the internal cavities of the fifth housing part 415 and the sixth housing part 416.
In this embodiment, as shown in fig. 1 and 2, the injection assembly 40 may further include a sixth shell portion 416, a seventh shell portion 417, and a fourth injection tube 45. The first, second, third, fourth, fifth, sixth and seventh shell portions 411, 412, 413, 414, 415, 416, 417 may be sequentially fixedly connected as one body and be hollow tubular bodies having both ends opened. In this way, the strength of the injection assembly 40 can be increased and the seal enhanced. The cross-sectional area of the sixth shell portion 416 may gradually increase in a direction in which the first shell portion 411 extends toward the fifth shell portion 415 (i.e., a first direction). The fourth ejector tube 45 may be disposed on a radially opposite side of the third ejector tube 44 and extend into the inner peripheral wall of the junction of the fifth housing portion 415 and the sixth housing portion 416 so as to communicate with the internal cavities of the fifth housing portion 415 and the sixth housing portion 416. When the intermittently existing medium-temperature superheated gas flows from the fourth ejector pipe 45 to the internal cavities of the fifth shell portion 415 and the sixth shell portion 416, the mixed first temperature-controlled medium from the first ejector pipe 42, the second ejector pipe 43 and the third ejector pipe 44 can be accelerated in the fifth shell portion 415 along the first direction to move towards the intermittently existing medium-temperature superheated gas from the fourth ejector pipe 45, and the intermittently existing medium-temperature superheated gas with the larger flow is driven to the sixth shell portion 416 along the first direction. In the process, the intermittent high-flow medium-temperature superheated gas can press the mixed first temperature control medium from the first injection pipe 42, the second injection pipe 43 and the third injection pipe 44 to the inner peripheral wall of the sixth shell 416, which is close to the side of the third injection pipe 44, so that four strands of first temperature control medium are further scattered, split and gasified in an accelerating way, and the four strands of first temperature control medium are fully mixed to form low-temperature low-pressure high-dryness two-phase flow. When the four strands of the first temperature control medium move from the small cross-sectional area end to the large cross-sectional area end of the sixth shell portion 416, the static pressure gradually increases and the flow velocity gradually decreases, so that sufficient time can be left for the four strands of the first temperature control medium to be fully mixed with the space, and the low-temperature low-pressure high-dryness two-phase flow is formed.
In some embodiments, as shown in FIGS. 1, 2, and 3, the centerline of the fourth ejector 45 perpendicularly intersects the centerline of the fifth shell portion 415.
In this embodiment, as shown in fig. 1, 2 and 3, the central axis of the fourth ejector tube 45 may vertically intersect with the central axis of the fifth shell 415, so that the intermittent medium-temperature superheated gas with a larger flow rate may be vertically input into the cavities of the fifth shell 415 and the sixth shell 416, so as to maximally diffuse, and make the first temperature control medium mix with the first temperature control medium from the first ejector tube 42, the second ejector tube 43 and the third ejector tube 44 as much as possible, thereby realizing rapid cooling. The four strands of first temperature control media can collide with the inner peripheral wall of the sixth shell portion 416 with a larger force, so that the gasification effect is further optimized, and finally, the low-temperature low-pressure high-dryness two-phase flow is formed.
In some embodiments, as shown in FIG. 2, the cross-sectional area of one end of the fourth ejector 45 external to the fifth housing portion 415 is smaller than the cross-sectional area of the other end.
In this embodiment, as shown in fig. 2, the fourth ejector 45 may be a tubular body having different diameters at both ends, and the diameter of the fourth ejector 45 at one end of the outside of the fifth and sixth shell portions 415 and 416 may be smaller than the diameter of the other end. When the intermittent medium-temperature superheated gas with larger flow flows from the small diameter end to the large diameter end of the third ejector pipe 44, the static pressure is gradually increased, the flow speed is gradually reduced, and then the first temperature control medium from the first ejector pipe 42, the second ejector pipe 43 and the third ejector pipe 44 is heated and extruded towards the opposite side direction of the fourth ejector pipe 45, and the low-temperature low-pressure high-dryness two-phase flow is formed in the inner cavity of the sixth shell 416.
In some embodiments, as shown in fig. 4, the compression assembly 10 includes a gas-liquid separation unit 14, a compression unit 11, a driving unit 12, and a shaft cooling unit 13; the driving unit 12 drives the compressing unit 11 to compress the first temperature control medium; an inlet of the compression unit 11 communicates with the gas-liquid separation unit 14, and an open end of the fifth shell portion 415 remote from the fourth shell portion 414 communicates with the gas-liquid separation unit 14; the shaft cooling unit 13 is arranged on the periphery of a transmission shaft 123 of the driving unit 12, and an outlet of the shaft cooling unit 13 is communicated with the third injection pipe 44; the condensing assembly 20, the inlet of the first temperature control medium of the condensing assembly 20 is communicated with the outlet of the compressing unit 11; an evaporation assembly 30, the evaporation assembly 30 including a regenerator 31, a first evaporation unit 32, and a second evaporation unit 33; the outlet of the first temperature control medium of the condensing assembly 20 is communicated with the liquid inlet of the regenerator 31; the liquid outlet of the heat regenerator 31 is respectively communicated with the inlet of the shaft cooling unit 13, the inlet of the first evaporation unit 32 and the inlet of the second evaporation unit 33; the outlet of the first evaporation unit 32 is in communication with a first ejector 42; the outlet of the second evaporation unit 33 communicates with a second ejector 43.
In this embodiment, as shown in FIG. 4, the aircraft thermal management system may include a compression assembly 10, a condensation assembly 20, and an evaporation assembly 30 in communication with one another. The compression assembly 10 may include a gas-liquid separation unit 14, a compression unit 11, a driving unit 12, and a shaft cooling unit 13. The two-phase flow can pass through the gas-liquid separation unit 14 before entering the compression unit 11, so that the compressor is prevented from carrying liquid to work under the drive of the driving unit 12. The shaft cooling unit 13 can make the driving unit 12 stably operate in an optimal operation temperature range.
The driving unit 12 may be disposed at one end of the compressing unit 11, and drive the compressing unit 11 to compress the first temperature-controlled medium. The inlet of the compression unit 11 may be in communication with the first separation outlet 143 of the gas-liquid separation unit 14, and the gas processed by the gas-liquid separation unit 14 may be compressed into a high-temperature and high-pressure gas and supplied to the condensation module 20 through a pipe for further processing. When the first temperature control mediums in each path are mixed in the injection housing unit 41 and discharged from the fifth housing unit 415, the opening end of the fifth housing unit 415 far away from the fourth housing unit 414 can be communicated with the separation inlet 142 of the gas-liquid separation unit 14, so that the mixed first temperature control mediums enter the gas-liquid separation unit 14 to further separate the liquid and the gas, thereby avoiding damage to the compressor and improving the cooling efficiency. In order to enable the driving unit 12 to continuously drive the compression unit 11 and maintain good compression efficiency, the shaft cooling unit 13 is disposed at the circumferential side of the transmission shaft 123 of the driving unit 12, and an outlet of the shaft cooling unit 13 may be communicated with the third injection pipe 44, so that the transmission shaft 123 may continuously operate in a suitable temperature interval. After the cooling of the driving shaft 123 by the first temperature control medium is finished, the first temperature control medium can enter the injection shell unit 41 through the third injection pipe 44, and flows to the gas-liquid separation unit 14 after being mixed with other first temperature control mediums, so that the gas and the liquid are separated, and the gas and the liquid can enter the compression unit 11 again conveniently to form a cooling cycle.
The inlet of the first temperature control medium of the condensation assembly 20 may be communicated with the outlet of the compression unit 11, when the compression assembly 10 compresses the first temperature control medium into high-temperature and high-pressure gas, the first temperature control medium can be communicated and conveyed to the inlet of the first temperature control medium of the condensation assembly 20 from the outlet of the compression unit 11 through a pipeline, so that the condensation assembly 20 cools the first temperature control medium, and the subsequent steps are convenient to process.
The evaporation assembly 30 may include a regenerator 31, a first evaporation unit 32, and a second evaporation unit 33, which are in communication with each other. The outlet of the first temperature control medium of the condensing assembly 20 may be in communication with the liquid inlet of the regenerator 31 through a pipe. After the cooling assembly cools the high-temperature and high-pressure first temperature control medium to a high-pressure and medium-temperature state, the first temperature control medium can be further cooled by flowing through the first temperature control medium outlet of the condensing assembly 20 to the liquid inlet of the regenerator 31.
The liquid outlet of the regenerator 31 may be in communication with the inlet of the shaft cooling unit 13, the inlet of the first evaporation unit 32, and the inlet of the second evaporation unit 33, respectively. The outlet of the first evaporation unit 32 may be in communication with a first ejector 42. The first temperature control medium can flow from the liquid outlet of the regenerator 31 to the first evaporation unit 32 to absorb heat generated by the airborne electronic equipment which runs for a long time and generates larger heat, and then flows back to the other liquid inlet of the regenerator 31 to cool the regenerator 31 again to form a large-flow high-dryness two-phase flow, and the large-diameter end of the first injection pipe 42 moves to the small-diameter end to form a large-flow high-dryness two-phase flow, and then enters the injection shell unit 41 to be mixed with other first temperature control mediums to form a low-temperature low-dryness two-phase flow, so that the burden of the gas-liquid separation unit 14 is reduced, and the probability of liquid entering the compression unit 11 is reduced.
The outlet of the second evaporation unit 33 may communicate with the large diameter end of the second ejector tube 43. The first temperature control medium can flow from the liquid outlet of the regenerator 31 to the second evaporation unit 33 to absorb heat generated by the airborne electronic equipment which runs for a long time and generates less heat, so as to form a low-flow low-dryness low-temperature two-phase flow, then flow to the large-diameter end of the second injection pipe 43, and enter the injection shell unit 41 through the second injection pipe 43 in an accelerating way to form a low-temperature low-dryness high-dryness two-phase flow with other first temperature control mediums, thereby reducing the burden of the gas-liquid separation unit 14, reducing the probability of liquid entering the compression unit 11, enabling the compressor to work normally and ensuring the cooling efficiency.
In other embodiments, the compression unit 11 may include an impeller inlet 111, a compression impeller 112, and an impeller outlet 113. The impeller inlet 111 may communicate with the first separation outlet 143, and the first temperature control medium for supplying pure gas to the compression unit 11 may improve cooling efficiency. The compression impeller 112 may be disposed between the impeller inlet 111 and the impeller outlet 113, compresses the first temperature-controlled medium into a high-temperature and high-pressure gas by centrifugal force generated by rotation, and then discharges the gas from the impeller outlet 113 to be supplied to the condensing assembly 20 for processing.
The drive unit 12 may further comprise a stator 121, a rotor 122, a bearing 124. The rotor 122 may be fixed to the outer circumferential wall of the driving shaft 123 to rotate in synchronization with the driving shaft 123. The stator 121 may be sleeved on the outer circumferential side of the rotor 122, and the outer circumferential wall of the stator 121 may be spaced apart from the inner circumferential wall of the rotor 122. The end of the drive shaft 123 adjacent to the compression unit 11 may also be detachably connected with the compression impeller 112. After the stator 121 is electrified, the transmission shaft 123 can be driven to rotate around the central axis thereof along with the rotor 122 according to the electromagnetic induction principle, and the compression impeller 112 connected with the transmission shaft 123 is driven to rotate, so that the first temperature control medium is compressed. Bearings 124 may be further sleeved on both ends of the rotor 122 on the outer peripheral wall of the transmission shaft 123, so that torque loss caused by rotation of the transmission shaft 123 is reduced, and compression efficiency is improved.
The shaft cooling unit 13 may include a shaft cooling tube 131, a shaft cooling chamber 132. The shaft cooling tube 131 may be sleeved on the outer circumferential side of the driving shaft 123, and the inner cavity may be filled with the first temperature control medium. The liquid inlet of the shaft cooling tube 131 may be in communication with the liquid outlet of the regenerator 31. The liquid outlet of the shaft cooling tube 131 may be in communication with the liquid inlet of the shaft cooling chamber 132. The liquid outlet of the shaft cooling chamber 132 may be in communication with the third ejector 44. After the first temperature control medium is cooled by the regenerator 31, it may enter the shaft cooling tube 131 from the liquid inlet of the shaft cooling tube 131 to effect cooling of the transmission shaft 123. The first temperature control medium after cooling is completed may be a low-flow high-temperature high-dryness superheated gas, and flows to the shaft cooling cavity 132 through the communication part between the shaft cooling pipe 131 and the shaft cooling cavity 132, and then flows from the liquid outlet of the shaft cooling cavity 132 to the small-diameter end of the third injection pipe 44, and enters the injection shell unit 41 to be mixed with other first temperature control mediums.
The condensing assembly 20 may include a condenser 21, a cold source supply unit 22, which are communicated with each other. The cold source supply unit 22 may cool the first temperature control medium in the condenser 21. The cold source supply unit 22 may include a first pump 221, a cold source tank 222. The cold source tank 222 may store a second temperature control medium, which may be a fuel. When the first temperature control medium flows in the condensation assembly 20, the first pump 221 may convey the second temperature control medium in the cold source tank 222 to the condenser 21, allow the second temperature control medium to absorb heat of the first temperature control medium, and then return to the condenser 21 again. In this way, cooling is achieved while the temperature of the fuel is raised, allowing the fuel to enter the engine for easy combustion.
The first evaporation unit 32 may include a first regulating valve 321, a first expansion valve 322, a first cold plate 323, and a first temperature equalizing plate 324. The first regulating valve 321, the first expansion valve 322, and the first cold plate 323 may be sequentially connected. The first regulating valve 321 may be in communication with a liquid outlet of the regenerator 31. The outlet of the first cold plate 323 may be in communication with a first ejector conduit 42. The first temperature equalizing plate 324 may be disposed at one side of the first cold plate 323, so that heat on the second cold plate 333 may be more uniform, thereby facilitating the improvement of cooling efficiency. When the first temperature control medium flows to the first regulating valve 321 through the condensation component 20 and the regenerator 31 in sequence, the first regulating valve 321 can regulate the flow of the first temperature control medium according to the instruction of the aircraft thermal management system so as to improve the cooling efficiency, and then flows to the first expansion valve 322, the first expansion valve 322 can change the first temperature control medium into low-pressure low-temperature high-dryness two-phase flow, flows to the first cold plate 323, absorbs the heat treated by the first temperature equalizing plate 324 to form high-flow high-dryness two-phase flow, moves to the first injection pipe 42, rapidly expands and vaporizes through the space difference between the first injection pipe 42 and the first shell 411, the temperature further drops, and then is fully mixed with other first temperature control mediums in the cavity of the injection shell unit 41 to form high-flow low-Wen Jigao dryness two-phase flow, so that the burden of the gas-liquid separation unit 14 is reduced, and the probability of liquid entering the compression unit 11 is reduced.
The second evaporation unit 33 may include a second regulating valve 331, a second expansion valve 332, a second cold plate 333, and a second temperature equalizing plate 334. The second regulating valve 331, the second expansion valve 332, and the second cold plate 333 may be sequentially communicated. The second regulating valve 331 may be in communication with a liquid outlet of the regenerator 31. The outlet of the second cold plate 333 may be in communication with the second ejector 43. The second temperature equalizing plate 334 may be disposed at one side of the second cold plate 333, so that heat on the second cold plate 333 may be more uniform, thereby facilitating improvement of cooling efficiency. When the first temperature control medium flows to the second regulating valve 331 through the condensation component 20 and the regenerator 31 in sequence, the second regulating valve 331 can regulate the flow of the first temperature control medium according to the instruction of the aircraft thermal management system, so as to improve the cooling efficiency, and then flows to the second expansion valve 332, the second expansion valve 332 can change the first temperature control medium into a low-pressure low-temperature low-dryness two-phase flow, flows to the second cold plate 333, absorbs the heat treated by the second temperature equalizing plate 334 to form a low-flow low-dryness low-temperature two-phase flow, and moves to the second injection pipe 43, and the space difference between the second injection pipe 43 and the first shell 411 is used for expansion and vaporization, so that the temperature is further reduced, and then the high-flow low-Wen Jigao dryness two-phase flow is formed by fully mixing the second temperature control medium with other first temperature control mediums in the cavity of the injection shell unit 41, so that the burden of the gas-liquid separation unit 14 is reduced, and the probability of liquid entering the compression unit 11 is reduced. The gas-liquid separation unit 14 may further include a separation chamber 141, a second separation outlet 144. The separation chamber 141 can be used to store a two-phase flow. The second separation outlet 144 may communicate with a lower end of the separation chamber 141. When the high-flow low Wen Jigao dryness two-phase flow enters the separation chamber 141, the gas can be delivered from the first separation outlet 143 communicated with the upper end of the separation chamber 141 to the inlet of the compression unit 11 for compression by the compression unit 11; if liquid can be separated, the liquid can be delivered from the second separation outlet 144 to the diversion portion of the compression assembly 10, through which the liquid is fed to the first cold plate 323 for over-feeding, thereby optimizing the cooling effect.
In some embodiments, as shown in fig. 1, 2, 3, the injection assembly 40 further comprises a sixth housing portion 416, a seventh housing portion 417, a fourth injection conduit 45; the first shell 411, the second shell 412, the third shell 413, the fourth shell 414, the fifth shell 415, the sixth shell 416 and the seventh shell 417 are fixedly connected in sequence to form a hollow tubular body with two open ends; the cross-sectional area of the sixth shell portion 416 increases gradually in the first direction, and the cross-sectional area of the seventh shell portion 417 decreases in the first direction; the fourth ejector pipe 45 passes through the side wall of the joint of the fifth shell part 415 and the sixth shell part 416 and is communicated with the internal cavities of the fifth shell part 415 and the sixth shell part 416; the evaporation assembly 30 further comprises a heat storage and exchange unit 34; the liquid outlet of the heat regenerator 31 is respectively communicated with the inlet of the shaft cooling unit 13, the inlet of the first evaporation unit 32, the inlet of the second evaporation unit 33 and the inlet of the first temperature control medium of the heat storage and exchange unit 34; the outlet of the first temperature control medium of the heat storage and exchange unit 34 is communicated with a fourth injection pipe 45.
In this embodiment, as shown in fig. 1, 2 and 3, the injection assembly 40 may further include a sixth shell portion 416, a seventh shell portion 417 and a fourth injection tube 45. The first, second, third, fourth, fifth, sixth and seventh shell portions 411, 412, 413, 414, 415, 416, 417 may be sequentially and fixedly connected as one body, and a hollow tubular body having both ends open may be presented after the connection is completed, so that the first temperature control medium may flow in the internal cavity as desired. The cross-sectional area of the sixth shell portion 416 may gradually increase in a direction in which the first shell portion 411 extends toward the fifth shell portion 415 (i.e., a first direction). When the high-flow low-temperature gas formed by mixing the first temperature control mediums from the first injection pipe 42, the second injection pipe 43 and the third injection pipe 44 flows towards the fourth injection pipe 45 along the first direction, the intermittent high-flow medium-temperature overheated gas flows out from the fourth injection pipe 45, the high-flow low-temperature gas is pressed to the inner peripheral wall of the sixth shell 416, which is far away from the fourth injection pipe 45, so that collision is generated, and liquid drops in the first temperature control mediums are scattered. The increasing cross-sectional area of the sixth shell portion 416 may allow for increased static pressure and reduced flow rate of each of the first temperature control media, and may allow sufficient space and time for intermixing to optimize the mixing effect. After the mixing of the first temperature control media is completed, the cross-sectional area of the seventh shell portion 417 may be reduced along the first direction, so that the mixed low-temperature low-pressure high-dryness two-phase flow may be output to the separation inlet 142 for gas-liquid separation, thereby improving the cooling efficiency. The fourth ejector 45 may be disposed on a radially opposite side of the third ejector 44 and extend into the inner peripheral wall of the junction of the fifth and sixth shell portions 415, 416 to communicate with the interior cavities of the fifth and sixth shell portions 415, 416. When the large flow of the low temperature gas moves from the large cross-sectional area end of the fifth shell portion 415 to the small area end of the fifth shell portion 415, the gradually reduced cross-sectional area can accelerate the large flow of the low temperature gas to the intermittently existing large flow of the medium temperature overheated gas, and the intermittently existing large flow of the medium temperature overheated gas can be accelerated by the large flow of the low temperature gas, so that the large flow of the medium temperature overheated gas is mutually mixed and collides with the inner peripheral wall of the sixth shell portion 416, the effect of scattering liquid drops is better, and the mixing effect is optimized. The droplets and gas after being dispersed can be decelerated in the space gradually enlarged by the sixth shell 416 in the first direction, so that the first temperature control mediums are fully mixed, the finally formed low-temperature low-pressure high-dryness two-phase flow is reduced, the liquid content in the first temperature control mediums is reduced, the burden of the gas-liquid separation unit 14 is reduced, the probability of liquid entering the compression unit 11 is reduced, the compressor works normally, and the cooling efficiency is ensured.
The evaporation assembly 30 may also include a heat storage and exchange unit 34. The heat storage and exchange unit 34 may be configured to cool ultra-high power electronics (e.g., weapon firing equipment). Because such on-board equipment will not continuously generate heat, the heat storage and exchange unit 34 may not continuously operate, so that the energy consumption of the aircraft is reduced and the effect of improving the endurance is achieved under the condition of ensuring the normal temperature of the aircraft. The liquid outlet of the regenerator 31 may be respectively in communication with the inlet of the shaft cooling unit 13, the inlet of the first evaporation unit 32, the inlet of the second evaporation unit 33, and the inlet of the first temperature control medium of the heat storage heat exchange unit 34. When the first temperature control medium passes through the condensation component 20, the first temperature control medium can be changed into a high-pressure medium-temperature supercooled liquid state, and the high-pressure medium-temperature supercooled liquid state is input to the liquid inlet of the regenerator 31 to be cooled again, and then flows to the shaft cooling unit 13, the first evaporation unit 32 and the second evaporation unit 33 to be cooled, so that normal navigation of the aircraft is ensured. The outlet of the first temperature control medium of the heat storage and exchange unit 34 may be in communication with a fourth ejector 45. After the first temperature control medium absorbs heat in the heat storage and exchange unit 34, the heat can be conveyed to the fourth injection pipe 45 to be fully mixed with the first temperature control mediums from the first injection pipe 42, the second injection pipe 43 and the third injection pipe 44 to form a low-temperature low-pressure high-dryness two-phase flow, and then the low-temperature low-pressure high-dryness two-phase flow enters the gas-liquid separation unit 14 to separate liquid from gas, so that the liquid carrying work of the compression unit 11 is avoided, and the cooling effect is kept.
In other embodiments, the seventh shell portion 417 may include an equal diameter section 4171, a variable diameter section 4172, which are sequentially communicated in the first direction. The constant diameter section 4171 may be a tubular body of constant cross-sectional area that may be the same as the larger cross-sectional area end of the sixth shell portion 416 to provide more room for mixing of the first temperature-controlled media to allow for more thorough mixing of the first temperature-controlled media to optimize cooling. The large cross-sectional area end of the reducing section 4172 may be in communication with the constant diameter section 4171 and the small cross-sectional area end may be in communication with the separation inlet 142. When the mixing of the first temperature control mediums is completed, a low-temperature low-pressure high-dryness two-phase flow is formed, and the reducing section 4172 can accelerate the low-temperature low-pressure high-dryness two-phase flow to be conveyed to the separation inlet 142, so that the cooling efficiency is improved.
The heat storage and exchange unit 34 may include a third regulating valve 341, a third expansion valve 342, a third cold plate 343, a second pump 344, a liquid accumulation chamber 345, and a heat exchanger 346. The third regulating valve 341, the third expansion valve 342, and the third cold plate 343 may be sequentially communicated. The third cold plate 343, the second pump 344, the effusion cell 345, and the heat exchanger 346 may be sequentially communicated, and the third cold plate 343 may be communicated with the heat exchanger 346. The outlet of the third cold plate 343 may be in communication with the fourth ejector 45. The liquid outlet of regenerator 31 may also be in communication with a third regulator valve 341. When the ultra-high power electronic device works for a short time, the low-temperature liquid working medium at the inlet of the heat exchanger 346 can be converted into high-temperature liquid working medium to flow from the outlet of the heat exchanger 346 to the liquid accumulation cavity 345 after receiving the instant high-power waste heat from the heat source of the ultra-high power electronic device in the heat exchanger 346, and then is input to the third cold plate 343 by the second pump 344. The third temperature control medium (which may be fuel) in the third cold plate 343 may absorb heat, so that the high temperature liquid working medium becomes the low temperature liquid working medium, and returns to the heat exchanger 346 again to absorb waste heat. After the super-power electronic device finishes short-time operation, the third regulating valve 341 is opened according to a predetermined program, and the first temperature control medium cooled by the regenerator 31 may be changed into a low-pressure low-temperature low-dryness two-phase flow through the third expansion valve 342 and flow to the third cold plate 343 to absorb heat of the third temperature control medium. Then, the first temperature control medium flows to the fourth injection pipe 45, and is mixed with other first temperature control mediums to form a low-temperature low-pressure high-dryness two-phase flow, and flows from the small cross-sectional area end of the seventh shell portion 417 to the separation inlet 142 along the first direction, so that the gas and the liquid are further separated, and the gas enters the compression unit 11 from the first separation outlet 143, so that the liquid carrying work of the compression unit 11 is avoided, and the cooling efficiency is ensured.
It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples of implementing the disclosure, and that various changes in form and details may be made therein without departing from the spirit and scope of the disclosure.
Claims (10)
1. An ejector assembly, the ejector assembly comprising:
the injection shell unit comprises a first shell part, a second shell part, a third shell part, a fourth shell part and a fifth shell part; the first shell part, the second shell part, the third shell part, the fourth shell part and the fifth shell part are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the second shell portion gradually decreases in a first direction, the cross-sectional area of the third shell portion gradually increases in the first direction, and the cross-sectional area of the fifth shell portion gradually decreases in the first direction; wherein the first direction is a direction extending from the first shell portion to the fifth shell portion;
the first injection pipe extends into the inner cavity of the first shell part from the outside of the opening end of the first shell part; one end of the first injection pipe is fixedly connected with the opening end of the first shell part; the cross section area of one end of the first injection pipe close to the opening end of the first shell part is larger than that of the other end;
The second injection pipe penetrates through the side wall of the first shell part and is communicated with the inner cavity of the first shell part;
the central line of the first injection pipe is coincident with the central line of the first shell part; the center line of the second injection pipe is arranged at intervals with the center line of the first shell part, so that the center line of the second injection pipe is parallel to the tangential direction of the inner peripheral surface of the first shell part and is deviated towards the center line direction of the first shell part, and the center line of the second injection pipe is obliquely arranged with the center line of the first shell part;
the third injection pipe penetrates through the side wall of the joint of the second shell part and the third shell part and is communicated with the inner cavity of the second shell part and the inner cavity of the third shell part.
2. An ejector assembly according to claim 1, wherein,
the cross-sectional area of the second ejector pipe positioned at one end outside the first shell part is larger than that of the other end.
3. An ejector assembly according to claim 1, wherein,
the second ejector pipe extends to the other end from one end located outside the first shell part towards the direction away from the first ejector pipe.
4. An ejector assembly according to claim 1, wherein,
the center line of the third injection pipe is perpendicularly intersected with the center line of the second shell part.
5. An ejector assembly according to claim 4, wherein,
the cross-sectional area of the third injection pipe positioned at one end outside the second shell part is smaller than the cross-sectional area of the other end.
6. An ejector assembly according to claim 1, wherein,
the injection assembly further comprises a sixth shell part, a seventh shell part and a fourth injection pipe; the first shell part, the second shell part, the third shell part, the fourth shell part, the fifth shell part, the sixth shell part and the seventh shell part are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the sixth shell portion gradually increases in the first direction, and the cross-sectional area of the seventh shell portion decreases in the first direction; the fourth injection pipe passes through the side wall of the joint of the fifth shell part and the sixth shell part and is communicated with the internal cavities of the fifth shell part and the sixth shell part.
7. An ejector assembly according to claim 6, wherein,
The center line of the fourth injection pipe is perpendicularly intersected with the center line of the fifth shell part.
8. An ejector assembly according to claim 6, wherein,
the cross-sectional area of the fourth injection pipe positioned at one end outside the fifth shell part is smaller than the cross-sectional area of the other end.
9. An aircraft thermal management system comprising an ejector assembly according to any one of claims 1-5, characterized in that,
the compression assembly comprises a gas-liquid separation unit, a compression unit, a driving unit and a shaft cooling unit; the driving unit drives the compressing unit to compress a first temperature control medium; an inlet of the compression unit is communicated with the gas-liquid separation unit, and an opening end of the fifth shell part far away from the fourth shell part is communicated with the gas-liquid separation unit; the shaft cooling unit is arranged on the periphery of a transmission shaft of the driving unit, and an outlet of the shaft cooling unit is communicated with the third injection pipe;
a condensing assembly, an inlet of the first temperature control medium of the condensing assembly is communicated with an outlet of the compression unit;
the evaporation assembly comprises a heat regenerator, a first evaporation unit and a second evaporation unit; the outlet of the first temperature control medium of the condensation component is communicated with the liquid inlet of the heat regenerator; the liquid outlet of the heat regenerator is respectively communicated with the inlet of the shaft cooling unit, the inlet of the first evaporation unit and the inlet of the second evaporation unit; the outlet of the first evaporation unit is communicated with the first injection pipe; and the outlet of the second evaporation unit is communicated with the second injection pipe.
10. An aircraft thermal management system according to claim 9, wherein
The injection assembly further comprises a sixth shell part, a seventh shell part and a fourth injection pipe; the first shell part, the second shell part, the third shell part, the fourth shell part, the fifth shell part, the sixth shell part and the seventh shell part are sequentially and fixedly connected to form a hollow tubular body with two open ends; the cross-sectional area of the sixth shell portion gradually increases in the first direction, and the cross-sectional area of the seventh shell portion decreases in the first direction; the fourth injection pipe passes through the side wall of the joint of the fifth shell part and the sixth shell part and is communicated with the internal cavities of the fifth shell part and the sixth shell part;
the evaporation assembly further comprises a heat storage and exchange unit; the liquid outlet of the heat regenerator is respectively communicated with the inlet of the shaft cooling unit, the inlet of the first evaporation unit, the inlet of the second evaporation unit and the inlet of the first temperature control medium of the heat storage and exchange unit; and an outlet of the first temperature control medium of the heat storage and exchange unit is communicated with the fourth injection pipe.
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