CN115492684A - Composite anti-icing structure for jet flow precooling device - Google Patents
Composite anti-icing structure for jet flow precooling device Download PDFInfo
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- CN115492684A CN115492684A CN202211112071.1A CN202211112071A CN115492684A CN 115492684 A CN115492684 A CN 115492684A CN 202211112071 A CN202211112071 A CN 202211112071A CN 115492684 A CN115492684 A CN 115492684A
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- heat transfer
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- side wall
- air supply
- icing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/10—Aircraft characterised by the type or position of power plant of gas-turbine type
Abstract
The application belongs to an air suction type combined cycle engine in the field of aviation super power, and particularly relates to a composite anti-icing structure for a jet flow precooling device; comprises a gas supply structure and a heat transfer structure; air feed structure has the air feed passageway, and heat transfer structure has lateral wall and inside wall, and the inside wall forms the inboard heat transfer channel who extends to the root by the heat transfer structure top, forms the outside heat transfer channel who extends to the root by the heat transfer structure top between lateral wall and the inside wall, and the inside wall has the inboard through-hole of the inboard heat transfer channel of intercommunication and outside heat transfer channel, and the lateral wall has intercommunication outside heat transfer channel and external outside through-hole, and inboard heat transfer channel all communicates with outside heat transfer channel air feed channel, this application can make full use of steam energy, and reasonable adjustment energy distribution guarantees that the regional homoenergetic of water striking is covered by the anti-icing protection, simultaneously because the effect of gas film seam blowdown overflow water droplet can reduce in no steam protection area and freeze.
Description
Technical Field
The application belongs to an air suction type combined cycle engine in the field of aviation super power, and particularly relates to a composite anti-icing structure for a jet flow precooling device.
Background
As different types of engines have respective performance advantages in different flight ranges, a combined cycle engine is formed by combining the advantages of different types of engines in each task segment in many countries in the world, and the precooling TBCC engine based on the turbine engine shows wide development prospect in the development of the air-breathing combined cycle engine. One of the pre-cooling schemes is that a jet flow pre-cooling device is additionally arranged at the front part of an air inlet of a conventional turbine engine, a nozzle is arranged in the jet flow pre-cooling device, fluid is sprayed to the air inlet, and air flow in the air inlet is cooled through evaporation, so that the temperature of the air flow is reduced, and the working range of the turbine engine is expanded. In addition, under high mach number conditions, the intake stagnation temperature increases, resulting in a decrease in air density, a decrease in flow rate, and a decrease in engine thrust. In order to ensure that the turbine engine can operate efficiently and stably in a wide range, a jet flow precooling device is necessary.
Because the jet flow precooling device is arranged in the air inlet channel, when the aircraft encounters icing meteorological conditions, air containing supercooled water drops can enter the air inlet channel, and the supercooled water impacts the jet flow precooling device to freeze. Icing can affect the pneumatic appearance of the jet flow precooling device, reduce the flow area of air flow and further affect the performance of the engine; meanwhile, the accumulated ice falls off, which may damage engine components and seriously affect the operation safety of the engine. In order to ensure the performance and safety of the engine, anti-icing measures need to be taken for the jet flow precooling device to ensure that the jet flow precooling device has an acceptable aerodynamic shape and prevent the generation of icing which endangers the safety of the engine. Therefore, the patent provides an anti-icing method and an anti-icing system for the jet flow precooling device, so that anti-icing protection is provided for the jet flow precooling device, and the anti-icing requirement of an engine is effectively met while the energy consumption is reduced.
Along with the continuous improvement of the performance of the aero-engine, the demands of the anti-icing system and the anti-icing method for the low-temperature gas cooling and the gas consumption are stronger and stronger under the condition of ensuring the all-weather safe and stable operation of the engine. Because the appearance of the jet flow precooling device is similar to that of an inlet part of a turbofan engine, the prior art related to the invention is a hot gas anti-icing system of a rectifying support plate, and the prior hot gas anti-icing system has the following defects in anti-icing application:
1. from the technical aspect: the existing hot gas anti-icing system has a further strengthened space for the anti-icing effect of key protection areas aiming at the situation that the utilization rate of precious anti-icing hot gas resources needs to be improved;
2. from the aspect of efficiency: the existing hot gas anti-icing system is generally low in heat transfer efficiency, and the hot gas is large in temperature drop along the way, so that the anti-icing effect of the root section of the heat transfer structure is not ideal;
3. from the aspect of energy consumption: the anti-icing hot air flow of the existing hot air anti-icing system is large, so that the energy consumption of an engine is large, and the performance of the engine is influenced.
Disclosure of Invention
In order to solve the above problems, the present application provides a composite anti-icing structure for a jet precooling apparatus, comprising:
the composite anti-icing structure is arranged on the incident flow side of the jet flow precooling device and comprises an air supply structure and a heat transfer structure;
the air supply structure is provided with an air supply channel, the air supply channel is connected with the air compressor through an air supply pipe, and the air supply pipe introduces high-temperature and high-pressure air of the air compressor into the air supply structure;
the heat transfer structure is provided with an outer side wall and an inner side wall, the inner side wall forms an inner side heat transfer channel extending from the top of the heat transfer structure to the root, an outer side heat transfer channel extending from the top of the heat transfer structure to the root is formed between the outer side wall and the inner side wall, the inner side wall is provided with an inner side through hole communicating the inner side heat transfer channel with the outer side heat transfer channel, the outer side wall is provided with an outer side through hole communicating the outer side heat transfer channel with the outside, the inner side heat transfer channel and the outer side heat transfer channel are both communicated with the air supply channel, and the outer side wall is a flow-facing surface.
The technical effect of the technical characteristics is as follows: by passing
Preferably, the air supply channel comprises an outer air supply channel and an inner air supply channel, the outer air supply channel is connected with the outer heat transfer channel, and the inner air supply channel is connected with the inner heat transfer channel.
Preferably, the outer air supply channel and the inner air supply channel are respectively connected with an air supply pipe, and each air supply pipe is provided with a flow valve.
Preferably, the inner through hole is located at the inner sidewall near the root.
Preferably, the heat transfer structure is a symmetrical structure with a uniform cross section, and the outer side wall and the inner side wall are bulged towards the inflow direction at the symmetrical plane to form a streamline curved surface.
Preferably, the inner side through holes are located at the foremost end of the inner side wall facing the incoming flow direction, the outer side through holes are located at the rearmost end of the outer side wall facing the incoming flow direction, the outer side through holes are symmetrically distributed along the symmetry plane, and the outer side through holes are uniformly distributed from the top to the root.
Preferably, the volume of the inner heat exchange channel is larger than that of the outer heat exchange channel, and the surface area of the inner heat exchange channel is smaller than that of the outer heat exchange channel.
Preferably, the outer through hole adopts a runway type air film seam, the width of the air film seam is between 1mm and 1.5mm, and the length of the air film seam is between 18mm and 22 mm.
Preferably, the distance between the inner and outer side walls is greatest towards the forwardmost end in the direction of flow.
Preferably, the total flow area of the inner through holes is 100mm 2 ～120mm 2 。
The advantages of the present application include: 1. according to the characteristics of the anti-icing system, the invention provides a double-channel air supply structure, which can achieve the purpose of independently adjusting the air supply flow according to a set target; 2. the invention adopts a composite anti-icing method of coupling 'convection + impact + air film' of a 'hot air insulating layer', can fully utilize hot air energy, reasonably adjust energy distribution, ensure that a water impact area can be covered by anti-icing protection, and simultaneously reduce icing in a non-hot air protection area due to the action of blowing off overflowing water drops by air film seams; 3. the anti-icing system has the characteristic of double hot air channels, can greatly reduce the temperature drop of hot air along the way, and ensures that the anti-icing effect of any position of an anti-icing component meets the anti-icing requirement; 4. the anti-icing system has high heat transfer efficiency, uses smaller anti-icing hot airflow, ensures the safe and stable operation of the turbine in all weather, simultaneously reduces the influence of anti-icing air entraining on the working efficiency of the engine to the minimum extent, reduces the energy consumption of the engine and improves the performance of the engine.
Drawings
FIG. 1 is a schematic view illustrating an installation of a jet precooling apparatus on an air inlet according to a preferred embodiment of the present application;
FIG. 2 is a schematic view of an axial view of a jet precooling apparatus installed on an air inlet according to a preferred embodiment of the present application;
FIG. 3 is a cross-sectional view of a preferred embodiment composite anti-icing structure of the present application;
FIG. 4 is a schematic view of an air intake configuration in accordance with a preferred embodiment of the present application;
FIG. 5 is a cross-sectional view of the air intake structure E-E of FIG. 4;
FIG. 6 is a cross-sectional view of the air intake structure F-F of FIG. 4;
FIG. 7 is a longitudinal cross-sectional view of the air intake structure of FIG. 4;
FIG. 8 is a cross-sectional view of a jet pre-cooling device and heat transfer structure;
fig. 9 is a longitudinal sectional view of a jet pre-cooling device and a heat transfer structure.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a compound anti-icing structure for efflux precooling apparatus includes:
the composite anti-icing structure is arranged on the upstream side of the jet flow precooling device and comprises an air supply structure and a heat transfer structure; the air supply structure is provided with an air supply channel, the air supply channel is connected with the air compressor through an air supply pipe, and the air supply pipe introduces high-temperature and high-pressure air of the air compressor into the air supply structure;
the heat transfer structure is provided with an outer side wall and an inner side wall, the inner side wall forms an inner side heat transfer channel extending from the top of the heat transfer structure to the root, an outer side heat transfer channel extending from the top of the heat transfer structure to the root is formed between the outer side wall and the inner side wall, the inner side wall is provided with an inner side through hole communicating the inner side heat transfer channel with the outer side heat transfer channel, the outer side wall is provided with an outer side through hole communicating the outer side heat transfer channel with the outside, the inner side heat transfer channel and the outer side heat transfer channel are both communicated with the air supply channel, and the outer side wall is a head-on surface.
The air supply channel comprises an outer air supply channel and an inner air supply channel, the outer air supply channel is connected with the outer heat transfer channel, and the inner air supply channel is connected with the inner heat transfer channel.
The outer side gas supply channel and the inner side gas supply channel are respectively connected with a gas supply pipe, and each gas supply pipe is provided with a flow valve.
The outer through hole is located at the position, close to the root, of the outer side wall.
The heat transfer structure is a symmetrical structure with equal section, and the outer side wall and the inner side wall are bulged towards the incoming flow direction at the symmetrical surface to form a streamline curved surface.
The inboard through-hole is located the inside wall and flows the direction foremost end department towards coming, and the outside through-hole is located the outside wall and flows the direction rearmost end department towards coming, and the outside through-hole is followed the symmetry plane symmetric distribution, outside through-hole is by top to root evenly distributed.
The volume of the inner heat exchange channel is larger than that of the outer heat exchange channel, and the surface area of the inner heat exchange channel is smaller than that of the outer heat exchange channel.
The outer side through hole adopts a runway type air film seam, the width of the air film seam is between 1mm and 1.5mm, and the length of the air film seam is between 18mm and 22 mm.
The distance between the inner and outer side walls is greatest towards the forwardmost end of the direction of flow.
The total flow area of the inner side through holes is 100mm 2 ～120mm 2 ；
In order to increase the heat exchange coefficient, enhance the heat exchange effect of hot gas and the outer wall and simultaneously consider the practical convenience of engineering, the width of the outer heat exchange channel is about 1 mm-3 mm;
the following detailed description is made in conjunction with the accompanying drawings: fig. 1 and 2 show a jet precooling device a arranged inside an inlet of a turbine b, and fig. 2 shows a distribution diagram of the jet precooling device a in the inlet. When turbine b operates at a higher mach number, the inlet flow stagnation temperature exceeds the allowable temperature of the turbine inlet section c material, and reducing the inlet flow temperature allows the turbine b section to operate safely at the higher mach number while also extending the operable range of turbine b. Based on the above, a plurality of jet flow precooling devices a can be arranged at the inlet of the air inlet of the turbine b; when the turbine b works under a high Mach number, the jet flow precooling device a jets micro water drops, and the water drops evaporate to take away the heat of the airflow, so that the temperature of the airflow is reduced.
Since the jet flow precooling device a is arranged in the air inlet channel. When an airplane encounters icing meteorological conditions, airflow containing liquid supercooled water enters an air inlet channel, the supercooled water impacts a jet flow precooling device a to freeze, and then a flow field at an inlet of an engine is changed, and meanwhile, the falling of accumulated ice can damage engine parts. Thus, anti-icing protection of the jet pre-cooling device a is required. The invention adopts a hot gas anti-icing mode, and the principle is that high-temperature and high-pressure air led out by a gas compressor d enters an anti-icing system of a jet flow precooling device so as to ensure that the jet flow precooling device can stably work in an icing envelope, a composite anti-icing structure of the invention is arranged on the upstream side of the jet flow precooling device, and the whole composite anti-icing structure is shown in figure 3 and comprises a gas supply structure 1 and a heat transfer structure 2; the air supply structure 1 is provided with an air supply channel, the air supply channel is connected with the air compressor through an air supply pipe, and the air supply pipe introduces high-temperature and high-pressure air of the air compressor into the air supply structure 1;
the transverse cross-sectional view of the heat transfer structure 2 and the jet flow precooling device a is shown in fig. 8, the longitudinal cross-sectional view of the heat transfer structure 2 and the jet flow precooling device a is shown in fig. 9, the heat transfer structure 2 is provided with an outer side wall and an inner side wall, the inner side wall forms an inner side heat transfer channel 22 extending from the top of the heat transfer structure 2 to the root, an outer side heat transfer channel 21 extending from the top of the heat transfer structure 2 to the root is formed between the outer side wall and the inner side wall, the inner side wall is provided with an inner side through hole communicating the inner side heat transfer channel 22 and the outer side heat transfer channel 21, the inner side through hole is an exhaust hole 23 in the drawing, the air film gap is an air film gap 24 in the drawing, the outer side wall is provided with an outer side through hole communicating the outer side heat transfer channel 21 with the outside, the outer side heat transfer channel 22 and the outer side heat transfer channel 21 are both communicated with the air supply channel, and the outer side wall is an upstream surface.
The air supply channels include an outside air supply channel 12 and an inside air supply channel 11, as shown in fig. 4-7, the outside air supply channel 12 is connected with an outside heat transfer channel 21, and the inside air supply channel 11 is connected with an inside heat transfer channel 22; the outer air supply channel 12 and the inner air supply channel 11 are respectively connected with an air supply pipe, each air supply pipe is provided with a flow valve, wherein the flow valves can independently supply air for an inner heat transfer channel 22 and an outer heat transfer channel 21 of a heat transfer structure of a jet flow precooling device, and carry out flow regulation according to requirements; hot air enters the heat transfer structure 2 in the jet flow precooling device a from the inner side air supply channel 11 and the outer side air supply channel 12 respectively, so that the two-channel air supply structure 1 is independent and does not interfere with each other; the air supply structure is made of flexible materials, and the flow areas of the two air supply pipes can be flexibly adjusted according to different states of the engine, so that the flow distribution is adjusted. The air film slit 24 is located at the outer sidewall near the root. The heat transfer structure 2 is a symmetrical structure with equal section, and the outer side wall and the inner side wall are bulged towards the incoming flow direction at the symmetrical surface to form a streamline curved surface. The air vent 23 is positioned at the foremost end of the inner side wall facing the incoming flow direction, and the air film slit 24 is positioned at the rearmost end of the outer side wall facing the incoming flow directionThe air film seams 24 are symmetrically distributed along the symmetrical plane, the air film seams 24 are uniformly distributed from the top to the root, the air film seams 24 adopt runway type air film seams, the width of the air film seams is between 1 and 1.5mm, and the length of the air film seams is between 18 and 22 mm; the distance between the inner and outer side walls is greatest towards the forwardmost end of the direction of flow; the total flow area of the exhaust holes 23 is 100-120 mm 2 。
In operation, a portion of the hot gas flowing from the gas supply structure 1 enters the inner heat transfer channel 22 from the top of the inner gas supply channel 11. The hot gas flows from the top to the root and then flows into the outer heat transfer passages 21 through the exhaust holes 23 in the root. Hot gas exhausted from the exhaust holes 23 impacts the wall surface of the front edge of the outer side wall, so that heat exchange between the hot gas and the front edge of the outer side wall is enhanced, and the temperature of the outer side wall is increased; and then in two directions: a part of the hot air moves towards the root of the outer heat transfer passage 21, converges in the same direction with the hot air of the outer heat transfer passage 21, and is discharged from an air film seam 24 at the root; the other part flows to the middle part of the outer heat transfer channel 21 and impacts with the hot gas in the channel in opposite direction, so as to strengthen the turbulent flow in the middle part, increase the internal heat exchange coefficient, and is discharged from the air film seam 24 at the middle and lower part after being mixed. Because the volume of the inner heat transfer channel is larger than that of the outer heat transfer channel, and the surface area of the inner heat transfer channel is smaller than that of the outer heat transfer channel, the inner heat transfer channel 22 provides a heat preservation effect for the hot gas of the outer heat transfer channel 21, the temperature drop of the hot gas along the way is greatly reduced, and due to the existence of the root exhaust holes 23, the hot gas flow from the middle lower part to the root is enhanced, the turbulent flow is enhanced, the heat exchange coefficient is increased, and the root heat exchange is enhanced; another part steam that flows by air feed structure 1 gets into outside heat transfer passage 21 by the top air vent, steam flows by top to root, heat device lateral wall leading edge and lateral wall side with the form of convection current, steam after the heating is discharged from the air film seam 24 at lateral heat transfer passage 21 afterbody edge, hot gas flow rate this moment is great, the temperature is higher, can form the gas film protection on the outer wall surface, prevent that the overflow water of front portion striking from flowing backward, make difficult to freeze because of the overflow water produces in the non-heating region in rear portion, further increase the protection zone.
To sum up, this application realizes that this device anti-icing concrete point includes:
1. due to the existence of the inner side heat transfer passage 22 and the outer side heat transfer passage 21, the heat can form the mutual heat preservation effect when flowing along the inner parts of the passages at the two sides, and the heat preservation of the heat mentioned in the composite anti-icing method can be realized;
2. the hot gas in the outer heat transfer channel 21 heats the outer side wall in a heat exchange mode of convection in the process of moving from the top to the root;
3. the two exhaust holes 23 at the root part between the inner side heat transfer channel and the outer side heat transfer channel enable hot gas of the inner side heat transfer channel 22 to impact the front edge of the outer side wall at the root part of the anti-icing relatively weak jet flow precooling device 1, and the impact mentioned in the composite anti-icing method can be realized;
4. the hot air heated on the outer side wall is discharged from the air film seam 24 at the edge of the tail part of the outer side heat transfer channel 21, the hot air flow speed is high, the temperature is high, air film protection can be formed on the surface of the outer wall, and the air film mentioned in the composite anti-icing method can be realized.
The application has the following technical effects:
1. the purpose of independently adjusting the air supply flow according to the set target can be achieved;
2. the composite anti-icing structure of coupling convection, impact and air film of the hot air insulation layer is adopted, so that the energy of hot air can be fully utilized, the energy distribution is reasonably adjusted, the water impact area can be protected and covered by anti-icing, and meanwhile, due to the action of blowing off overflowing water drops by the air film seam, the icing can be reduced in the non-hot air protection area;
3. the gas supply structure has the characteristic of double hot gas channels, so that the temperature drop of hot gas along the way can be greatly reduced, and the anti-icing effect of any position of an anti-icing component can be ensured to meet the anti-icing requirement;
4. the heat transfer structure of the application has high heat transfer efficiency, the used anti-icing hot airflow is small, the turbine is ensured to run safely and stably under all weather, meanwhile, the influence of anti-icing air entraining on the working efficiency of the engine is reduced to the minimum degree, the energy consumption of the engine is reduced, and the performance of the engine is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A composite anti-icing structure for a fluidic precooling apparatus, comprising:
the composite anti-icing structure is arranged on the incident flow side of the jet flow precooling device and comprises an air supply structure and a heat transfer structure;
the air supply structure is provided with an air supply channel, the air supply channel is connected with the air compressor through an air supply pipe, and the air supply pipe introduces high-temperature and high-pressure air of the air compressor into the air supply structure;
the heat transfer structure is provided with an outer side wall and an inner side wall, the inner side wall forms an inner side heat transfer channel extending from the top of the heat transfer structure to the root, an outer side heat transfer channel extending from the top of the heat transfer structure to the root is formed between the outer side wall and the inner side wall, the inner side wall is provided with an inner side through hole communicating the inner side heat transfer channel with the outer side heat transfer channel, the outer side wall is provided with an outer side through hole communicating the outer side heat transfer channel with the outside, the inner side heat transfer channel and the outer side heat transfer channel are both communicated with the air supply channel, and the outer side wall is a flow-facing surface.
2. The composite anti-icing structure for a fluidic pre-cooling device as recited in claim 1, wherein the air supply channel comprises an outer air supply channel and an inner air supply channel, the outer air supply channel is connected to the outer heat transfer channel, and the inner air supply channel is connected to the inner heat transfer channel.
3. The composite anti-icing structure for a jet precooling apparatus according to claim 2, wherein the outer gas supply channel and the inner gas supply channel are respectively connected with a gas supply pipe, and each gas supply pipe is provided with a flow valve.
4. The composite anti-icing structure for a fluidic pre-cooling device according to claim 1, wherein the inner through-hole is located at the inner sidewall near the root.
5. The composite anti-icing structure for a jet flow precooling apparatus according to claim 1, wherein the heat transfer structure is a symmetrical structure with a uniform cross section, and the outer side wall and the inner side wall are convex in the incoming flow direction at the symmetrical plane to form a streamline curved surface.
6. The composite anti-icing structure for a jet flow precooling apparatus according to claim 5, wherein the inner through holes are located at the foremost end of the inner side wall facing the incoming flow direction, the outer through holes are located at the rearmost end of the outer side wall facing the incoming flow direction, the outer through holes are symmetrically distributed along the symmetry plane, and the outer through holes are uniformly distributed from the top to the root.
7. The composite anti-icing structure for a fluidic pre-cooling device of claim 1, wherein a volume of the inner heat exchange channel is larger than a volume of the outer heat exchange channel, and a surface area of the inner heat exchange channel is smaller than a surface area of the outer heat exchange channel.
8. The composite anti-icing structure for a jet flow precooling apparatus according to claim 6, wherein the outer through holes are air film slits of a runway type, the width of the air film slits is between 1mm and 1.5mm, and the length of the air film slits is between 18mm and 22 mm.
9. The composite anti-icing structure for a jet precooling apparatus according to claim 5, wherein a distance between the inner side wall and the outer side wall is greatest at a forwardmost end in the direction of flow.
10. The composite anti-icing structure for a fluidic pre-cooling device of claim 5, wherein the total flow area of the inner through holes is 100mm 2 ～120mm 2 。
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| CN202211112071.1A CN115492684A (en) | 2022-09-13 | 2022-09-13 | Composite anti-icing structure for jet flow precooling device |
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| CN202211112071.1A CN115492684A (en) | 2022-09-13 | 2022-09-13 | Composite anti-icing structure for jet flow precooling device |
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