CN114771846A - Cooling device for air film and internal turbulent flow and application - Google Patents
Cooling device for air film and internal turbulent flow and application Download PDFInfo
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- CN114771846A CN114771846A CN202210371612.6A CN202210371612A CN114771846A CN 114771846 A CN114771846 A CN 114771846A CN 202210371612 A CN202210371612 A CN 202210371612A CN 114771846 A CN114771846 A CN 114771846A
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- 238000001816 cooling Methods 0.000 title claims abstract description 64
- 239000007789 gas Substances 0.000 claims abstract description 40
- 239000002737 fuel gas Substances 0.000 claims abstract description 12
- 239000007921 spray Substances 0.000 claims description 22
- 239000010410 layer Substances 0.000 claims description 9
- 239000002356 single layer Substances 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 18
- 230000008901 benefit Effects 0.000 abstract description 5
- 238000012795 verification Methods 0.000 abstract description 3
- 239000000112 cooling gas Substances 0.000 description 7
- 238000004364 calculation method Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Combustion & Propulsion (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a cooling device for air film and internal turbulent flow and application thereof, belonging to the field of aeroengines; the cold side flat plate is positioned on one side of the cold air channel, and the hot side flat plate is positioned on one side of the high-temperature fuel gas channel; a plurality of hollow flow disturbing columns are arranged between the cold side flat plate and the hot side flat plate, the cold air channel is communicated with the high-temperature fuel gas channel through hollow holes of the hollow flow disturbing columns, and an intermediate channel containing the hollow flow disturbing columns is formed between the two layers of flat plates. The invention utilizes the characteristics of small flow resistance and easy outflow of the hollow hole, can avoid gas from flowing backwards, and simultaneously utilizes the advantages of small flow resistance of the inner turbulent flow of the inclined hollow turbulent flow column and good attachment of an external air film. The structure is suitable for areas which need high cooling efficiency but are easy to generate gas backflow, such as high-temperature nozzle wall surfaces. Through numerical verification, compared with the existing impact and gas film double-wall structure, the structure has better cooling effect and smaller flow resistance.
Description
Technical Field
The invention belongs to the field of aero-engines, and particularly relates to a cooling device for air film and internal turbulent flow and application thereof.
Background
Military warplanes often gain additional thrust by afterburning beyond the maximum throttle opening of the engine during short take-off and fast maneuvers. Because the afterburner space is limited, the burnt gas acts on the spray pipe wall of the engine convergence section in an oblique impact mode, so that the gas is easy to flow backwards, and serious consequences are caused. Research shows that the temperature of the fuel gas of the tail nozzle reaches more than 2000K. In addition, the pressure gradient from the inlet to the outlet of the engine nozzle is large, so that the gas in the expansion section is easily and strongly sucked, and the backward flowing phenomenon of the convergence section is aggravated.
The impact double-wall air film cooling technology is one of advanced cooling modes of high-temperature components of modern engines, and can fully utilize the advantage of high impact heat exchange coefficient before air conditioner forms an air film to achieve the effect of locally strengthening heat exchange. The cooling performance of the novel impact/divergence cooling laminate heat screen is compared by the existing literature, the feasibility of applying the novel impact/divergence cooling laminate heat screen to an afterburner is demonstrated, the same working condition is contrastively analyzed with a corrugated plate heat screen and a single-layer flat plate heat screen, and the result shows that the impact/divergence cooling laminate heat screen has a better cooling effect. The double-wall structure has a structure strengthening effect, and meanwhile, the film hole outflow has a certain vibration-proof effect, so that the service life and the reliability of the afterburner can be prolonged. However, in the prior art, the double-wall cooling structure can achieve a good heat exchange effect, but the internal flow resistance of the double-wall cooling structure is large, the influence of the change of the main secondary flow total pressure ratio is large, the outflow is not easy to occur under the condition of a small pressure ratio, and the double-wall cooling structure is not suitable for being applied to a convergent section of an engine spray pipe.
At present, researches on methods for reducing the internal flow resistance of the double-wall structure are carried out at home and abroad, for example, methods for adding pits on a target surface and changing the shape of a turbulent flow column are adopted, but the methods are limited by large turns and vortices of airflow under the condition of fluid impact-air film, so that the flow loss is large, and the improvement effect is not obvious.
Advanced aircraft engines afterburners are short and combustion flame oblique impact acts on the convergent section of the nozzle. Because of the scouring action of the gas, on one hand, the heat load of the heat shield at the convergent section of the spray pipe is large, and the heat shield is influenced by the suction of the opening of the expansion section, and the gas is easily poured into the cold air channel from the gas film hole at the convergent section, so that the heat shield loses the heat insulation capability. The traditional porous structure flat plate has low cold efficiency and is difficult to form effective protection on the wall surface of a convergence section, and the impact and gas film double-wall structure is difficult to flow out due to large internal flow resistance in a small pressure ratio. In addition, due to the low-pressure suction effect of the gas at the expansion section, most of the cooling gas is sucked to the expansion section with a mild working condition, so that the waste of the cooling gas is caused to a certain extent, and the gas backflow at the convergence section is aggravated.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides the air film and internal turbulent flow cooling device, the middle channel with the turbulent flow columns is formed between the two layers of flat plates, the hollow turbulent flow columns are arranged in a staggered mode, the characteristics of small flow resistance and easy outflow of hollow holes are utilized, the backflow of fuel gas can be avoided, and meanwhile, the advantages of small flow resistance of internal turbulent flow of the inclined hollow turbulent flow columns and good attachment of external air films are utilized. The structure is suitable for areas which need high cooling efficiency but are easy to generate gas backflow, such as high-temperature nozzle wall surfaces. Through numerical verification, compared with the existing impact and gas film double-wall structure, the structure has better cooling effect and smaller flow resistance.
The technical scheme of the invention is as follows: the utility model provides a cooling device of air film with inside vortex which characterized in that: the cold side flat plate is positioned at one side of a cold air channel, and the hot side flat plate is positioned at one side of a high-temperature fuel gas channel;
a plurality of hollow flow disturbing columns are arranged between the cold side flat plate and the hot side flat plate, the cold air channel is communicated with the high-temperature fuel gas channel through hollow holes of the hollow flow disturbing columns, and an intermediate channel containing the hollow flow disturbing columns is formed between the two layers of flat plates.
The invention further adopts the technical scheme that: the hollow turbulence columns are arranged in a staggered mode, and form an inclination angle of 20-90 degrees with the air flow direction of the middle channel.
The further technical scheme of the invention is as follows: hollow hole aperture D of the hollow turbulent flow columniBetween 0.5 and 5 mm.
The invention further adopts the technical scheme that: the span-wise hole distance P and the flow-direction hole distance S of the hollow holes are 3-10 times of the hole diameter D of the hollow holesi。
The invention further adopts the technical scheme that: the hollow holes are distributed in a regular rhombus shape in the flow direction.
The invention further adopts the technical scheme that: the average height H of the channels formed by the hot side flat plate and the cold side flat plate is 1-10 times of the diameter D of the hollow holeiAnd (4) inside.
The invention further adopts the technical scheme that: the radial section of the hollow turbulent flow column is circular, oval, drop-shaped or hyperbolic.
The further technical scheme of the invention is as follows: the cross section of the hollow hole of the hollow flow disturbing column is consistent with the shape of the radial cross section of the hollow flow disturbing column.
An engine nozzle, characterized by: the cooling device for the air film and the internal turbulent flow is arranged on the inner side of the outer wall of the convergent section of the engine spray pipe and is connected to a single-layer corrugated plate of the afterburner through transition corrugations;
the cold side flat plate and the outer wall of the convergent section of the spray pipe form an outer duct, and the hot side flat plate forms the inner wall surface of the spray pipe; the tail ends of the cold side flat plate and the outer wall surface of the spray pipe convergence section are of a closed structure, so that all cold air of the outer duct flows out through the hollow holes of the hollow turbulence columns, and a cooling air film is formed on the hot side flat plate; and the total pressure outflow is utilized, so that the occurrence rate of gas backflow is reduced.
Advantageous effects
The invention has the beneficial effects that: the invention provides a cooling device with an air film and internal turbulence of a hollow column, which fully utilizes the advantages that the flow resistance of an inclined turbulence column is small, convection cooling can be enhanced, and the air film is attached to an inclined hollow hole, so that the aim of efficient cooling is fulfilled. The specific implementation principle is as follows: as shown in fig. 2, a part of the cooling gas B flows out D from the gas side of the hot-side flat plate through the hollow hole 3 to form a gas film layer, so that the heat transfer of the main flow gas a to the hot-side flat plate is reduced; the other part of the cooling gas C passes through the turbulent flow column row 4 at high speed under the suction action of the fuel gas at the expansion section of the spray pipe, and takes away the heat of the flat plate 2 at the hot side and the hollow column; the staggered arrangement of the turbulence columns ensures that the turbulence is more sufficient, and the outflow of the hollow holes is ensured to form uniform coverage on the surface of the flat plate at the hot side; the turbulent flow column 4 and the middle channel airflow C form an inclination angle of 20-90 degrees, so that the flow section is elliptical on one hand, the internal flow resistance is reduced, and the cooling airflow D and the main flow A have smaller included angles on the other hand, so that the cold air is ensured to be applied to the wall surface, the higher cooling effect is achieved, and the mixing loss of the spray pipe is reduced. As shown in fig. 5, the cold-side flat plate is connected with the outer wall surface of the nozzle convergent section at the tail end to form a closed cavity, and the risk of gas backflow can be reduced as much as possible by using the total pressure outflow; the combination of internal turbulent flow cooling and external air film cooling improves the cold effect and avoids the defect that the flow resistance of the traditional double-wall impact and air film structure is too large. As shown in fig. 6, the cylindrical shapes of the oval 12, the hyperbolic 13 and the drop 14 not only can make the gas film better applied on the surface of the gas, enhance the heat exchange effect, but also can reduce the flow resistance of the internal cylindrical row.
After numerical verification, as shown in fig. 7 and fig. 8, which are respectively a cloud chart and a comparison chart of the comparison of the comprehensive cooling efficiency of an embodiment of the present invention and a conventional impact + gas film double-wall model with holes opened at the same position, under the condition of using the same gas film cooling gas quantity, the comprehensive cooling efficiency of the present invention is increased from 0.636 to 0.818, the comprehensive cooling efficiency is improved to 1.29 times of that of the conventional structure, and the total pressure loss coefficient of the cold gas is reduced from 1.03 to 0.62 and reduced to 60.2 percent of that of the conventional impact + gas film double-wall model.
In summary, the invention has the advantages that: (1) the cooling air consumption is less, and the cooling efficiency is high; (2) the included angle between the cold air and the main flow is small, and the blending loss is low; (3) the structure has small internal flow resistance, and the cold air flows out in total pressure, so that the gas can be prevented from flowing backwards.
Drawings
FIG. 1 is a schematic view of a cooling apparatus with air film and internal turbulence according to the present invention;
FIG. 2 is a schematic flow diagram of a cooling device with air film and internal turbulence according to the present invention;
FIG. 3 is a schematic diagram showing the characteristic dimensions of a cooling device for air film plus internal turbulence according to the present invention;
FIG. 4 is a schematic view of an arrangement of holes of a cooling device for air film plus internal turbulence according to the present invention;
FIG. 5 is a schematic view of an application scenario of the present invention in a converging section of an engine nozzle;
FIG. 6 is a schematic view of the structure of the hollow turbulent flow column of the present invention;
FIG. 7 is a cloud chart comparing the integrated cooling efficiency of an embodiment of the present invention with a single-layer multi-inclined-orifice model;
FIG. 8 is a comparison plot of the spanwise average integrated cooling efficiency of an embodiment of the present invention versus a single-layer multi-inclined-hole plate model;
description of reference numerals: 1. a cold side plate; 2. a hot side plate; 3. a hollow bore; 4. a hollow turbulence column; 5. an afterburner outer wall; 6. a single-layer corrugated plate of the afterburner; 7. a main gas duct; 8. the outer wall of the convergent section of the spray pipe; 9. the outer wall of the expansion section of the spray pipe; 10. the expansion section of the spray pipe impacts a gas film double-wall cooling structure; 11. a circular hollow turbulence column; 12. an elliptical hollow turbulence column; 13. a water drop-shaped hollow turbulence column; 14. a hyperbolic hollow turbulence column; A. mainstream gas; B. cooling airflow in a bypass; C. cooling air flow between the double-layer plates; D. hollow hole outflow; diThe inner diameter of the hollow turbulence column; doThe turbulent flow outer diameter of the hollow column; H. average height of channels between plates; p, arranging the spread-out intervals of the hollow turbulent flow columns; s, arranging flow direction intervals of the hollow turbulence columns; theta, the angle of the air flow between the hollow turbulent flow column and the middle channel.
Detailed Description
The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present invention and should not be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
The embodiment is a specific embodiment of a cooling device with a hollow column and air film and internal turbulent flow in an engine spray pipe.
High-temperature low-pressure gas discharged from the turbine enters the main gas duct 7 after diffusion, is mixed with fuel oil sprayed by the fuel oil nozzle and then is combusted to form high-temperature gas, an oblique impact effect is formed on a convergent section of the spray pipe, the temperature of the main flow high-temperature gas A can reach 2200K, the main flow high-temperature gas A far exceeds the melting point of a material, and therefore the wall surface of the spray pipe needs to be cooled.
Referring to fig. 1, 2, 3 and 4, the air film and internal turbulence cooling device with a hollow column of the present embodiment includes a cold-side plate 1, a hot-side plate 2 and a hollow turbulence column 4 connecting the two plates. The cold side plate is provided with hollow holes 3 which are arranged in a staggered mode, the cold side flat plate 1 and the outer wall surface 8 of the spray pipe convergence section form a cold air channel, a middle channel is formed between the two layers of flat plates, and the hot side flat plate 2 forms the inner wall surface of fuel gas of the high-temperature component.
Fig. 2 and 5 show the working mode of the cooling device with hollow column air film and internal turbulence of the nozzle convergent section, the cooling device with hollow column air film and internal turbulence is connected to the afterburner single-layer corrugated plate through transition corrugations, a part of the cooling air from the afterburner culvert enters the outer culvert formed by the cold side flat plate and the outer wall of the nozzle convergent section to form cooling air flow B, the tail end of the outer culvert of the convergent section is in a closed form, so that all the cooling air passes through the hollow column to form outflow D, and a cooling air film is formed on the hot side flat plate 2; the other part of cold air from an afterburner culvert passes through the middle channel and cools a flat plate at the hot side under the turbulent flow effect of the hollow column row forming a certain angle with the flow direction and the suction effect of the expansion section.
In the embodiment, the average height H of the channel between the two plates is 2.5mm, and the inner diameter D of the hollow turbulence columniIs 1mm, and the outer diameter D of the hollow turbulent flow columnoThe diameter of the hollow turbulence column array is 1.5mm, the spanwise distance P of the hollow turbulence column array is 3mm, the flow direction distance S of the hollow turbulence column array is 1.5mm, and the air flow angle theta between the hollow turbulence column and the middle channel is 30 degrees.
Because the cold side flat plate and the outer wall form a straight cold air channel, the tail end of the cold side flat plate is closed, and meanwhile, the hollow hole has smaller flow resistance compared with a double-layer wall impacting an air film structure, the risk of backward flowing of fuel gas can be reduced. Part of cooling gas from the afterburner passes through the hollow hole under the limitation of the closed cavity, and forms a gas film layer on the flat plate at the hot side, thereby greatly reducing the heat transfer quantity of the fuel gas to the flat plate at the hot side; in addition, a part of cooling gas passes through the hollow cylindrical row of the middle channel, and under the strong suction effect of the expansion section of the spray pipe, the convection heat exchange is enhanced, the heat of the flat plate at the hot side is taken away, and the temperature of the flat plate at the hot side is further reduced, so that the wall surface of the expansion section of the whole spray pipe is well protected. The present embodiment was compared with the conventional impact + gas film double wall at the same aperture ratio and aperture position by numerical calculation. The specific calculation settings are shown in table 1, and the cooling effect comparison between the embodiment and the conventional impact + gas film double-wall model is shown in fig. 7 and fig. 8. Under the condition of the same cold air consumption, the comprehensive cooling efficiency is improved to 1.29 times of that of the traditional impact and gas film double-layer wall structure, and the total pressure loss coefficient of the cold air is reduced by 60.2 percent.
TABLE 1 implementation case and impact + gas film double-wall model numerical calculation method
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are exemplary and not to be construed as limiting the present invention, and that those skilled in the art may make variations, modifications, substitutions and alterations within the scope of the present invention without departing from the spirit and scope of the present invention.
Claims (9)
1. The utility model provides a cooling device of air film with inside vortex which characterized in that: the cold side flat plate is positioned on one side of the cold air channel, and the hot side flat plate is positioned on one side of the high-temperature fuel gas channel;
a plurality of hollow flow disturbing columns are arranged between the cold side flat plate and the hot side flat plate, the cold air channel is communicated with the high-temperature fuel gas channel through hollow holes of the hollow flow disturbing columns, and an intermediate channel containing the hollow flow disturbing columns is formed between the two layers of flat plates.
2. The film-plus-internal-turbulated cooling apparatus of claim 1, wherein: the hollow turbulence columns are arranged in a staggered mode, and form an inclination angle of 20-90 degrees with the airflow direction of the middle channel.
3. The air film and internal turbulated cooling apparatus of claim 2, wherein: the aperture D of the hollow hole of the hollow turbulent flow columniBetween 0.5 and 5 mm.
4. The film-plus-internal-turbulated cooling apparatus of claim 3, wherein: the span-wise hole distance P and the flow-wise hole distance S of the hollow holes are 3-10 times of the hole diameter D of the hollow holesi。
5. A cooling device for air film plus internal turbulence as defined in claim 3, wherein: the hollow holes are distributed in a regular rhombus shape in the flow direction.
6. A cooling device for air film plus internal turbulence as defined in claim 3, wherein: the average height H of the channel formed by the hot side flat plate and the cold side flat plate is 1-10 times of the diameter D of the hollow holeiAnd (4) the following steps.
7. The air film and internal turbulated cooling apparatus of claim 1, wherein: the radial section of the hollow turbulence column is circular, elliptical, drop-shaped or hyperbolic.
8. The air film plus internal turbulated cooling apparatus of claim 7, wherein: the cross section of the hollow hole of the hollow flow disturbing column is consistent with the shape of the radial cross section of the hollow flow disturbing column.
9. An engine nozzle employing the film-plus-internal-turbulated cooling apparatus of any one of claims 1 to 8, wherein: the cooling device for the air film and the internal disturbed flow is arranged on the inner side of the outer wall of the convergent section of the engine spray pipe and is connected to a single-layer corrugated plate of the afterburner through transition corrugations; the cold side flat plate and the outer wall of the convergent section of the spray pipe form an outer duct, and the hot side flat plate forms the inner wall surface of the spray pipe; the tail ends of the cold side flat plate and the outer wall surface of the spray pipe convergence section are of a closed structure, so that all cold air of the outer duct flows out through the hollow holes of the hollow turbulence columns, and a cooling air film is formed on the hot side flat plate; and the total pressure outflow is utilized, so that the occurrence rate of gas backflow is reduced.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210371612.6A CN114771846A (en) | 2022-04-11 | 2022-04-11 | Cooling device for air film and internal turbulent flow and application |
| CN202211227195.4A CN115783274A (en) | 2022-04-11 | 2022-10-09 | Cooling device for air film and internal turbulent flow and application |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210371612.6A CN114771846A (en) | 2022-04-11 | 2022-04-11 | Cooling device for air film and internal turbulent flow and application |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114771846A true CN114771846A (en) | 2022-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210371612.6A Withdrawn CN114771846A (en) | 2022-04-11 | 2022-04-11 | Cooling device for air film and internal turbulent flow and application |
| CN202211227195.4A Pending CN115783274A (en) | 2022-04-11 | 2022-10-09 | Cooling device for air film and internal turbulent flow and application |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211227195.4A Pending CN115783274A (en) | 2022-04-11 | 2022-10-09 | Cooling device for air film and internal turbulent flow and application |
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| Country | Link |
|---|---|
| CN (2) | CN114771846A (en) |
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2022
- 2022-04-11 CN CN202210371612.6A patent/CN114771846A/en not_active Withdrawn
- 2022-10-09 CN CN202211227195.4A patent/CN115783274A/en active Pending
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| CN115783274A (en) | 2023-03-14 |
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Application publication date: 20220722 |
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