CN112343664A - Efficient cooling system for turbine blades - Google Patents
Efficient cooling system for turbine blades Download PDFInfo
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- CN112343664A CN112343664A CN202011264794.4A CN202011264794A CN112343664A CN 112343664 A CN112343664 A CN 112343664A CN 202011264794 A CN202011264794 A CN 202011264794A CN 112343664 A CN112343664 A CN 112343664A
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- cooling
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- 238000001816 cooling Methods 0.000 title claims abstract description 50
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 125
- 239000007921 spray Substances 0.000 claims abstract description 10
- 239000000446 fuel Substances 0.000 claims description 8
- 238000009413 insulation Methods 0.000 claims 1
- 239000003595 mist Substances 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 25
- 238000002485 combustion reaction Methods 0.000 description 11
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 6
- 239000001257 hydrogen Substances 0.000 description 6
- 229910052739 hydrogen Inorganic materials 0.000 description 6
- 239000000498 cooling water Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 239000003897 fog Substances 0.000 description 4
- 239000000295 fuel oil Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000003245 coal Substances 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
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- 230000000149 penetrating effect Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 229910052702 rhenium Inorganic materials 0.000 description 2
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000005514 two-phase flow Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
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- 238000006243 chemical reaction Methods 0.000 description 1
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- 238000005553 drilling Methods 0.000 description 1
- 238000005868 electrolysis reaction Methods 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000003665 fog water Substances 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 125000004435 hydrogen atom Chemical group [H]* 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
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- 125000004430 oxygen atom Chemical group O* 0.000 description 1
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- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an efficient cooling system for turbine blades, and belongs to the field of turbine engine manufacturing. The system takes cold water as a cooling working medium and comprises a water sprayer, a flow valve, a high-pressure water pump and a water tank; the water sprayer has two, fixes on the turbine chamber inner wall, comprises ring, nozzle: the middle of the circular ring is provided with a cavity which penetrates through the wall of the turbine chamber through a high-pressure water pipe to be connected with a flow valve and a high-pressure water pump outlet, and the high-pressure water pump inlet is connected with a water tank; a plurality of nozzles are uniformly arranged on the circular ring, and spray cold water onto the turbine blades to cool the blades; the cold water absorbs a large amount of heat at high temperature and then decomposes and detonates to generate larger energy and increase the thrust of the engine.
Description
Technical Field
The invention relates to the field of free energy and environmental protection, in particular to a turbofan engine, a turbojet engine and a turboprop engine, and also relates to the technical field of manufacturing of gas turbines.
Background
Hydrogen bombs require millions of high temperature ignitions from the detonation of the bomb, which in turn releases more energy than the bomb.
The water molecule is composed of two hydrogen atoms and one oxygen atom, has a property similar to that of a hydrogen bomb, contains an energy by itself, and has many strange and peculiar properties which are not known.
In life, such things are often encountered: when a coal stove or a gas stove is used, if water is sprayed on the coal stove carelessly, the flame is not reduced, but is fiercely changed into a fire mass which is leaped upwards.
When the fire engine extinguishes fire, the first water column is sprayed to a big fire, the fire is one of retardation, but the fire rebounds quickly, and the fire is more violent.
The fuel and the oxidant of a certain type of liquid rocket both contain moisture, and flight tests show that the moisture of the oxidant can reach 4 percent, and the flight power is not influenced at all.
Scientific experiments prove that: spraying water into liquid fuel oil to atomize the oil for combustion and to make the flame more vigorous, and the amount of water to be mixed can reach one third.
When the automobile runs in rainy days, a driver feels stronger power than usual.
Brown gas has a cold flame of only 130 degrees fahrenheit (water boils 212 degrees fahrenheit), but the same flame can vaporize tungsten, which requires over 10000 degrees fahrenheit, and burning hydrogen can never reach this temperature.
Brown gas can greatly reduce the radiation of radioactive substances, which cannot be done by burning hydrogen.
When brown gas is analyzed in a high-tech laboratory, hydrogen is hardly found, but a water gas mass with excess electrons (charged water gas mass) exists.
The ultrasonic wave can generate cavitation bubbles in water, a large amount of bubbles burst to generate remarkable cavitation, the marine propeller is damaged by the cavitation bubbles, and a large amount of microscopic craters are distributed on the surface of the blade.
The above shows that water can absorb energy under the conditions of high temperature, electrolysis, ultrasonic wave, microwave and the like, and release more energy, and can be used for solving the cooling problem of the current turbine engine and gas turbine.
The operating principle of the turbofan engine is that gas generated by burning fuel oil in a combustion chamber impacts turbine blades to rotate a turbine and drive a coaxial compressor and a fan to rotate. The rotating fan sucks a large amount of air, the air is compressed by the multistage compressor and sent to the combustion chamber, the compressed air and fuel oil are combusted together to generate high-pressure high-speed airflow, the high-pressure high-speed airflow impacts the turbine blades again, and the rotation of the turbine is accelerated. The gas passing through the turbine chamber enters the afterburner chamber and then is discharged from the spray pipe, and a forward reaction force, namely thrust, is generated on the engine.
The main performance indexes of the gas turbine and the turbofan engine which are used as large-scale power systems are system cycle thermal efficiency and output power, and the system cycle thermal efficiency and the output power are increased along with the increase of the temperature of a gas inlet of a turbine rotor.
According to calculation, the thrust of the engine can be improved by about 10% under the condition that the size of the engine is unchanged when the RIT of the gas at the inlet of the turbine is improved by 55 ℃. This is why the turbine front temperature is an important measure of the engine's performance.
However, RIT is much higher than the melting point of the turbine blade metal material, so cooling is essential.
In the field of aero-engines, modes such as convection cooling, impingement cooling, film cooling, diffusion cooling and the like are developed successively, and the purpose of cooling is to improve the temperature in front of a turbine so as to improve the performance of the engine, enable the temperature field in a blade to be distributed uniformly and reduce thermal stress.
In recent years, with the continuous improvement of the performance of large gas turbines, in order to further reduce the consumption of effective gas, a steam-fog two-phase flow cooling scheme is proposed, i.e. the turbine blade is gradually shifted from air cooling to air and steam dual-medium cooling, and the scheme is increasingly becoming a hot point of research. A large number of researches show that the steam fog cooling has the advantages of fast cooling, high cooling efficiency, small flow resistance, simple structure and the like, and can play an important role in cooling the turbine blade of the next generation of high-performance gas turbine.
The blades and disks of the above turbine engines and gas turbines are in a discrete state, and have the following disadvantages:
1. because the turbine works at a high temperature state for a long time, the requirement on the material of the turbine blade is extremely high, and the requirement can be met only by adding rare metal rhenium, so that the material cost is high.
2. The various cooling methods improve the working environment of the turbine blade, but simultaneously, the turbine blade has a complex structure, a hollow interior and a plurality of air holes on the surface, and the processing technology becomes very complex.
3. The blade and the wheel disc are respectively and independently processed and manufactured and are connected by mortise and tenon joints or welded, so that the strength is low and the blade and the wheel disc are easy to fall off.
4. The cooling working medium is air, and too little of the cooling working medium can cause the temperature of the blade to be higher, thereby reducing the working reliability of the heat component and shortening the service life of the heat component, but too much of the cooling working medium can reduce the performance of the engine.
5. The gas turbine adopts a steam-fog two-phase flow cooling scheme, and the turbine blades are cooled by high-temperature steam, so that the effect is good, the energy of the steam is consumed, the efficiency is still low, and the turbine blades cannot be utilized in a turbine engine.
Disclosure of Invention
In view of the above-mentioned problems with existing turbine manufacturing techniques, the present invention provides an efficient cooling system for turbine blades.
The technical scheme adopted by the invention for realizing the purpose is as follows:
a turbine blade efficient cooling system takes cold water as a cooling working medium and comprises a water sprayer, a flow valve, a high-pressure water pump and a water tank; the two water sprayers are fixed on the inner wall of the turbine chamber and consist of a circular ring and a nozzle; the middle of the circular ring is provided with a cavity which is connected with the flow valve and the outlet of the high-pressure water pump through a high-pressure water pipe, and the inlet of the high-pressure water pump is connected with the water tank; a plurality of nozzles are uniformly arranged on the circular ring, and spray cold water onto the turbine blades to cool the blades; the cold water absorbs a large amount of heat at high temperature and then decomposes and detonates to generate larger energy and increase the thrust of the engine.
The working medium of the cooling system is 1-40 ℃ cold water so as to be different from high-temperature steam adopted by a gas turbine, the specific heat capacity of the water is about three times of that of the air, and the cooling effect of the cooling system is necessarily superior to that of cold water and the steam; the characteristics of heat absorption, energy storage and energy release of water are utilized, and the contradiction between the cooling effect and the engine performance is solved.
Suppose that the engine starts on the ground from rest, with a mass M, and a fuel plus air flow phi1The mass of the gas discharged as a velocity upsilon at a time Δ t is Δ m, the velocity obtained by the engine is V, and the flow rate of the cooling water is Φ2(ii) a According to the law of conservation of momentum, if the total momentum before and after the gas is discharged is equal, MV-delta m upsilon is 0; assuming that the thrust of the engine is F, F Δ t-MV- Δ m upsilon, F- Δ m upsilon/Δ t, and Δ m/Δ t- Φ according to the impulse formula1+Φ2，F＝υ(Φ1+Φ2). If there is no flow rate of cooling water phi2And the thrust of the engine is F ═ v Φ1It is apparent that the thrust of the engine increases after the cooling water is added.
The two water sprayers are fixed on the inner wall of the turbine chamber and consist of a circular ring and a nozzle.
Two circular rings are fixed on the inner wall of the turbine chamber, one is positioned in front of the turbine and is called a first ring, and the other is opposite to the turbine blades and is called a second ring; the cavity of the circular ring stores cold water in a high-pressure state and is communicated with a nozzle arranged on the water sprayer.
The nozzles are arranged on the inner side of the circular ring, the direction of the nozzles of the first ring is inclined backwards and points to the turbine blade part, so that the high-pressure kinetic energy of the cold water is utilized to impact the turbine, the turbine blade can be cooled powerfully, and the power of the turbine can be increased; the direction of the nozzles of the second ring points to the circle center, and the nozzles spray atomized water flow centripetally to cover the turbine blades completely.
The flow valve is positioned outside the combustion chamber, and the high-pressure water pipes penetrate through the inner wall of the turbine chamber to be hermetically connected with a cavity of the water sprayer so as to measure, adjust and control the flow of cold water entering the water sprayer, so that the turbine blades and the wheel disc can be fully cooled, and the detonation can be delayed after the cold water absorbs heat.
The high-pressure water pump is positioned outside the turbine chamber, the outlet of the water pump is hermetically connected with the flow control valve through a high-pressure water pipe, and the inlet of the water pump is connected with the water tank, so that the cold water is pressurized, the jet speed of the nozzle is increased, the cold water can fully cover the surface of the whole turbine blade, and the cooling is effectively carried out.
The water tank is positioned outside the turbine chamber and is connected with a water inlet of the high-pressure water pump through a water pipe; the water tank stores enough pure cold water to supply cooling needs.
The invention uses the steam fog cooling scheme of a gas turbine for reference, combines the special properties of water, and provides a technical scheme taking cold water as a working medium, and directly adopts a cold water external cooling mode to form a low-temperature region in the space of a turbine blade so as to cool the blade. When high-temperature fuel gas passes through the blades, cold water absorbs a large amount of heat and turns into high-temperature water vapor, and delayed explosion combustion occurs, so that greater energy is generated, and the combustion efficiency is enhanced. The result is that the blades are cooled and the gas flow is increased, thereby achieving two purposes.
Its advantages are as follows:
1. because the effect of cold water on turbine cooling is obvious, the material requirement on the turbine blade can be reduced, and rare metal rhenium is not needed or added in a small amount, so that the cost of the originally high material is reduced.
2. With the efficient cooling system, the turbine blade and the wheel disc can realize the integration of manufacturing processes such as casting, milling, heat treatment and the like, and the blade does not need hollow machining and surface punching, thereby simplifying the machining process of the turbine. As a result, the strength of the turbine blade to disk connection is significantly increased, while the manufacturing costs are substantially reduced.
3. The method solves the contradiction between the cooling efficiency and the engine performance, not only can greatly improve the cooling efficiency, but also can improve the performance of the engine, and realizes win-win.
4. Because the cooling water can be converted into fuel gas, a large amount of fuel oil can be saved, and the range of the airplane is increased.
Drawings
Fig. 1 is a schematic diagram of the overall working relationship of the preferred embodiment of the present invention.
Fig. 2 is a left side view of the sprinkler.
Detailed Description
The invention will be further described with reference to the accompanying drawings and preferred embodiments:
fig. 1 is a schematic diagram showing the overall operation of the preferred embodiment of the present invention, and as shown, the system is composed of a water sprayer 1001, a flow valve 1002, a high pressure water pump 1003 and a water tank 1004, the thick arrows indicate the flowing direction of the gas, and the thin arrows indicate the spraying direction of the cold water.
Fig. 2 is a left side view of the sprinkler, as shown, the outermost circle being the turbine chamber inner wall, the sprinkler 1001 consisting of a ring 2001 and a nozzle 2002.
The number of the water sprayers 1001 is two, and the two sprayers are fixed on the inner wall of the turbine chamber and are composed of a ring 2001 and a nozzle 2002.
The two circular rings 2001 are fixed on the inner wall of the turbine chamber, one is positioned in front of the turbine and is called a first ring, and the other is opposite to the turbine blades and is called a second ring; the cavity of the ring stores cold water in a high pressure state, the upper part of the cavity penetrates through the inner wall of the turbine chamber to be connected with a high pressure water pipe, and a plurality of nozzles 2002 are arranged at the lower part of the cavity.
The nozzles 2002 are uniformly arranged on the inner side of the ring 2001 and communicated with the cavity of the ring 2001; the jet orifice adopts laser drilling, and the extremely fine high-speed water flow is jetted centripetally, the direction of the first ring of nozzles is inclined and aligned with the turbine blade part, and the second ring of nozzles is opposite to the turbine blade to jet the fog water flow.
The flow valve 1002 is installed outside the combustion chamber and is connected with the water sprayer 1001 through a plurality of high-pressure water pipes penetrating through the inner wall of the turbine chamber; the flow control can be synchronously adjusted in proportion according to the flow consumption of the fuel at different flight speeds, so that the cooling efficiency and the working performance of the engine are ensured.
The high-pressure water pump 1003 is arranged outside the turbine chamber, the outlet of the high-pressure water pump is connected with the flow valve 1002 through a high-pressure water pipe, and the inlet water pipe of the high-pressure water pump is inserted into the water tank 1004; its function is to generate cold water under high pressure, which is supplied to the nozzle 2002 to spray a high velocity stream of cooling water.
The water tank 1004 is positioned outside the turbine chamber, is connected with the water inlet of the high-pressure water pump through a water pipe and has the function of storing enough pure cold water; the water tank is manufactured and installed as required by the oil tank, and heat preservation and anti-freezing measures are required.
The second embodiment of the invention is similar to the preferred embodiment, except that: the ring 2001 of the water sprayer 1001 is smaller in diameter and is equivalent to the diameter of a wheel disc of a turbine and is positioned in front of the turbine, and a main shaft vertically penetrates through the center of the ring; the nozzle 2002 is arranged on the outer side of the circular ring 2001 and sprays water flow to the turbine blades in a radiation mode; the circular ring 2001 is connected with the flow valve 1002 by a plurality of high-pressure water pipes penetrating through the wall of the turbine chamber, and the circular ring is fixed; the strength of the connection is subject to the impact of high velocity gas and is not as good as the preferred embodiment.
The test working process of the preferred embodiment of the invention is as follows:
1. after the engine is started and the combustion chamber is ignited, the high pressure water pump 1003 and the flow valve 1002 successively turn on the switch circuit. The flow value initially set by the flow valve 1002 is lower because the turbine blade temperature is initially lower and less water needs to be cooled.
2. As the fuel flow increases and the turbine front temperature rises, the flow valve 1002 needs to constantly increase the flow of cold water to ensure that the temperature of the turbine blades does not exceed a maximum value, and therefore the flow of cold water is related to the fuel flow.
3. The first ring of water jets 1001 is horizontally distanced from the turbine in order to create a pre-cooled space, at a suitable distance, which needs to be repeatedly modified during the test.
4. The nozzles 2002 of the first ring are not arranged perpendicularly and centripetally, but are arranged obliquely backwards, and the angle is more or less suitable and needs to be adjusted continuously in the test, so that the direction-adjustable nozzles are used for the test.
5. The diameters of the nozzles of the first ring nozzle 2002 and the second ring nozzle 2002 are respectively proper so as to spray different water flows, and the cooling effect is optimal and needs to be determined in experiments.
6. The outlet pressure of the high pressure water pump 1003 is more or less suitable and can be determined by trial and error, so the outlet pressure of the water pump is adjustable.
7. Because the cold water can be exploded and burnt only after being heated by the high-temperature fuel gas for a certain time, whether the temperature in the afterburner chamber is higher than that in the prior art or not is measured, so that whether the cold water is secondarily detonated after being heated in the turbine chamber or not is determined.
8. The exhaust speed of the nozzle of the engine is measured, and whether the thrust of the engine is increased compared with the prior art is measured.
9. When the turbine engine is at high altitude, the air density is low due to lean air, the intake air flow is reduced, and at this time, the aircraft needs to consume more fuel than the ground to maintain a higher speed, and the condition of insufficient combustion and black smoke can occur. Therefore, the flow of the cold water is properly increased, the components of hydrogen and oxygen in the combustion reaction can be increased, and the combustion efficiency is improved. Thus, the control of the flow valve 1002 is also related to the air flow.
10. When the aircraft lands, as the flying speed is gradually reduced, the consumed fuel flow rate is reduced and the air density is increased, so that the flow rate of cold water must be reduced to avoid sudden flameout of the engine due to excessive cooling.
Claims (9)
1. The system takes cold water as a cooling working medium and consists of a water sprayer, a flow valve, a high-pressure water pump and a water tank; the water sprayer consists of a circular ring and a nozzle, wherein a cavity is arranged in the middle of the circular ring and is connected with the flow valve and the outlet of the high-pressure water pump through a high-pressure water pipe, and the inlet of the high-pressure water pump is connected with the water tank; a plurality of nozzles are uniformly arranged on the circular ring, and spray cold water onto the turbine blades to cool the blades; the cold water absorbs a large amount of heat at high temperature and then decomposes and detonates to generate larger energy and increase the thrust of the engine.
2. The turbine blade efficient cooling system as claimed in claim 1, wherein the cooling working medium is cold water of 1-40 ℃, and the turbine blade is efficiently cooled by external cooling without reducing the thrust of the engine.
3. The system of claim 1, wherein the number of the water jets is two, and the two water jets are fixed on the inner wall of the turbine chamber and are composed of a ring and a nozzle.
4. A turbine blade efficient cooling system as claimed in claim 1 or claim 3, wherein there are two said circular rings, one is located in front of the turbine and is called the first ring, and the other is located opposite to the turbine blade and is called the second ring, and there is a cavity in the middle to store the cold water in high pressure state.
5. A high efficiency cooling system for turbine blades as claimed in claim 1 or claim 3 wherein said plurality of nozzles are uniformly mounted on a circular ring.
6. A turbine blade efficient cooling system as claimed in claim 1 or claim 5, wherein the nozzle part of the nozzle is laser drilled to spray extremely fine high-speed water flow centripetally, the direction of the first ring of nozzles is inclined to be directed at the turbine blade part, and the second ring of nozzles is directed to spray mist water flow toward the turbine blade.
7. The turbine blade efficient cooling system as claimed in claim 1, wherein the flow valve is installed outside the turbine chamber, and connected to a water sprayer through a high pressure water pipe passing through an inner wall of the turbine chamber, so that the flow rate of the cold water can be automatically adjusted according to the flow rate of the fuel and air.
8. The system for cooling turbine blades at high efficiency as claimed in claim 1, wherein said high pressure water pump is installed outside the turbine chamber and can be automatically started, pressure-regulated and shut down according to the command.
9. The system of claim 1, wherein the water box is installed outside the turbine chamber, and is constructed and installed to provide thermal insulation and freeze protection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011264794.4A CN112343664A (en) | 2020-11-13 | 2020-11-13 | Efficient cooling system for turbine blades |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011264794.4A CN112343664A (en) | 2020-11-13 | 2020-11-13 | Efficient cooling system for turbine blades |
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| CN112343664A true CN112343664A (en) | 2021-02-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217193A (en) * | 2021-05-14 | 2021-08-06 | 西北工业大学 | Turbine wheel disc water spray cooling structure |
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2020
- 2020-11-13 CN CN202011264794.4A patent/CN112343664A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217193A (en) * | 2021-05-14 | 2021-08-06 | 西北工业大学 | Turbine wheel disc water spray cooling structure |
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Application publication date: 20210209 |