CN112682174B - Anti-icing structure suitable for aeroengine extension board and wing - Google Patents
Anti-icing structure suitable for aeroengine extension board and wing Download PDFInfo
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- CN112682174B CN112682174B CN202011470796.9A CN202011470796A CN112682174B CN 112682174 B CN112682174 B CN 112682174B CN 202011470796 A CN202011470796 A CN 202011470796A CN 112682174 B CN112682174 B CN 112682174B
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- 239000000945 filler Substances 0.000 claims abstract description 23
- 238000005192 partition Methods 0.000 claims abstract description 14
- 229910052751 metal Inorganic materials 0.000 claims description 15
- 239000002184 metal Substances 0.000 claims description 15
- 239000011148 porous material Substances 0.000 claims description 15
- 239000006260 foam Substances 0.000 claims description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000002994 raw material Substances 0.000 claims description 3
- 229910052755 nonmetal Inorganic materials 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 14
- 238000000034 method Methods 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 3
- 230000001681 protective effect Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010440 gypsum Substances 0.000 description 1
- 229910052602 gypsum Inorganic materials 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Abstract
The invention discloses an anti-icing structure suitable for a rectification support plate and a wing of an aircraft engine, which comprises an anti-icing part, wherein a partition plate is arranged in the anti-icing part, the partition plate divides the internal space of the anti-icing part into an air inlet cavity and an impact cavity, a jet hole is formed in the partition plate, the air inlet cavity is communicated with the impact cavity through the jet hole, and the convection-impact heat exchange of heat flow between the air inlet cavity and the impact cavity is formed; a flow distribution plate is vertically arranged in the air inlet cavity, an air inlet is formed in the top of the air inlet cavity on the right side of the flow distribution plate, and intervals are reserved between the two ends of the flow distribution plate and the top surface and the bottom surface of the anti-icing component to form a channel for forward conveying of heat flow; and a plurality of layers of porous medium fillers are laid in the impact cavity along the expansion direction, and the surface of the impact cavity is provided with an air outlet slit. The invention can regulate and control the heat flow distribution far away from the near end of the heat source, reduce the uneven far-near end protection of the traditional heat exchange structure, enhance the heat exchange effect of hot air flow and the front edge of the part, and reduce the hot air condition requirement required by the conventional hot air anti-icing method.
Description
Technical Field
The invention relates to an anti-icing heat transfer technology of aircraft parts, in particular to an anti-icing structure suitable for an aircraft engine support plate and an aircraft wing.
Background
When an airplane flies over high altitude, low temperature and humid environment, ice accretion can be generated on the surfaces of some windward components, such as wings, the front edge of a rectification support plate and the like. The generation of ice accretion not only affects the working performance of the aircraft, but also seriously threatens the flight safety. At present, the anti-icing of most parts on the airplane is realized in a hot air anti-icing mode, and the anti-icing mode is developed and widely applied, but has some defects. Firstly, hot gas anti-icing requires air to be led from a high-pressure stage of an engine, the air is valuable for the engine, and the air leading causes the work capacity of the engine to be reduced and the thrust to be reduced; secondly, in order to improve the heat exchange efficiency of the thermal anti-icing system, a complex hot gas channel design is required, so that holes, slots and the like are inevitably formed in the inner part and the surface of the part, and the strength of the part is insufficient; thirdly, the problems of uneven protection effect of parts with larger span, such as wings, supporting plates and the like, exist during hot gas anti-icing, and the protection effect of the region far away from a hot gas source is poor; finally, the thermal anti-icing system only depends on designing a hot gas flowing structure to complete heat exchange, the means is single, and the lifting space is small.
At present, along with the development of a high-thrust engine, more severe requirements are provided for the air entraining amount of a hot gas anti-icing system, the anti-icing thermal structure of related components needs to be deeply and optimally designed, measures except the flow structure design are sought, the heating efficiency and the protection uniformity of the thermal protection air are fully improved, and therefore the satisfactory anti-icing effect is achieved with the air entraining amount as small as possible.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to provide an anti-icing structure which can distribute hot air flow, effectively relieve the protection difference of the far end and the near end of the anti-icing structure and enhance the heat exchange effect of the hot air flow and the leading edge of a part and is suitable for supporting plates and wings of an aircraft engine.
The technical scheme is as follows: the anti-icing component comprises an anti-icing component, wherein a partition plate is arranged in the anti-icing component, the partition plate divides the internal space of the anti-icing component into an air inlet cavity and an impact cavity, a jet hole is formed in the partition plate, the air inlet cavity is communicated with the impact cavity through the jet hole, and the convection-impact heat exchange of heat flow between the air inlet cavity and the impact cavity is formed; a flow distribution plate is vertically arranged in the air inlet cavity, an air inlet is formed in the top of the air inlet cavity on the right side of the flow distribution plate, and intervals are reserved between the two ends of the flow distribution plate and the top surface and the bottom surface of the anti-icing component to form a channel for forward conveying of heat flow; and a plurality of layers of porous medium fillers are laid in the impact cavity along the expansion direction, and the surface of the impact cavity is provided with an air outlet slit.
The pore diameter of the porous medium filler is reduced layer by layer from top to bottom, and the thickness and the layer number of the porous medium filler are adjusted according to the internal flow resistance and the anti-icing requirement so as to adapt to different working conditions.
The porosity of the porous medium filler in the same layer is consistent, the pore diameter is uniform, and the flow properties along all directions are the same.
The porous medium filler is made of a non-metal porous material or foam metal prepared by taking metal and alloy thereof as raw materials, and has light weight and high porosity.
The jet holes are arranged in a plurality of numbers according to the rule of single-row equal distance, and the heat flow exchange of the air inlet cavity and the impact cavity is realized.
Two rows of air outlet slits are respectively formed in the front surface and the rear surface of the impact cavity, the air outlet slits on the same surface are distributed in a fork row mode, the air outlet slits on the front surface of the impact cavity and the air outlet slits on the rear surface of the impact cavity are symmetrically arranged, heat flow can be timely discharged, a hot air film is formed on the surface of the anti-icing component, and a certain protection effect is achieved on a downstream area.
The anti-icing part is made of metal aluminum.
Has the advantages that: compared with the prior art, the invention has the beneficial effects that: (1) the hot air flow can be distributed in areas with different distances from a heat source, so that the problem of large difference of far-end and near-end protection of components caused by hot air flow reduction and temperature loss in the traditional anti-icing structure is solved; (2) the porous medium has excellent characteristics of low density, high porosity, high specific surface area, high effective heat conductivity coefficient and the like, so that the heat exchange effect between hot air flow and parts can be enhanced after the porous medium is used as a filler, and the anti-icing effect with high efficiency and low consumption is achieved; the structural strength of the anti-icing component is improved to a certain extent; (3) the anti-icing structure still has good protection effect under the harsh hot gas condition, the air entraining condition required by the anti-icing structure is lower than the air entraining requirement of the conventional anti-icing mode, and the surface of the part still has a certain icing temperature margin (a value higher than the icing temperature), so that the temperature or flow of the hot gas is allowed to be further reduced, and the air entraining amount is further reduced; (4) the processing process of the protective structure is not more complicated than that of the traditional protective structure, and the laying of the porous medium filler is simple.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the flow of hot gas in the internal passages of the anti-icing component of FIG. 1;
FIG. 3 is a top view of FIG. 1;
FIG. 4 is a schematic view of the jet flow rate of each jet hole when the inlet hot gas flow rate is 6g/s according to the present invention;
FIG. 5 is a schematic diagram of the temperature distribution of the leading edge line of the rectifying support plate when different porous media fillers are used in the present invention.
Detailed Description
The invention is described in further detail below with reference to specific embodiments and the attached drawings.
As shown in fig. 1 and 2, the present invention includes an anti-icing part 1 having a three-dimensional full-size structure, and the material of the anti-icing part 1 is aluminum metal. A partition plate 3 is arranged in the anti-icing component 1, the partition plate 3 divides the inner space of the anti-icing component 1 into a left part and a right part, the left side of the partition plate 3 is an air inlet cavity 11, and the right side of the partition plate 3 is an impact cavity 12. The partition plate 3 is provided with a plurality of jet holes 31, and parameters such as an impact distance, a hole shape, a hole size, a hole interval and a hole opening angle of the jet holes 31 are adjusted according to heat flow conditions and component sizes. In this embodiment, the jet holes 31 are circular and arranged in a single row at equal intervals. The air inlet cavity 11 and the impact cavity 12 are communicated through the jet hole 31, and the convection-impact heat exchange of heat flow between the air inlet cavity 11 and the impact cavity 12 is formed. The flow distribution plate 111 is vertically arranged in the air inlet cavity 11, the air inlet 112 is formed in the top of the air inlet cavity on the right side of the flow distribution plate 111, the two ends of the flow distribution plate 111 are respectively reserved with the top surface and the bottom surface of the anti-icing component 1 at intervals, a heat flow forward conveying channel is formed, and the size of the channel can be adjusted. The heat flow is divided into two parts after entering the air inlet cavity 11 from the air inlet 112, the two parts are respectively concentrated to heat the upper end and the lower end of the anti-icing part 1, and then the two parts of heat flow are converged at the middle part of the front half part of the air inlet cavity 11, so that the defect of insufficient middle protection caused by heat loss along the heat flow is overcome, and the heat flow regulation and control effect is achieved. Whether channels at other positions of the flow distribution plate 111 are arranged or not and the arrangement size are determined according to the thermal protection effect of each part, and the flow distribution plate 111 and the number of the channels with proper sizes are arranged according to the heat requirement of the corresponding area and the like so as to perform reasonable heat flow regulation. Two rows of air outlet slits 121 are respectively arranged on the front surface and the rear surface of the impact cavity 12, the air outlet slits on the same surface are distributed in a fork row manner, and the air outlet slits on the front surface of the impact cavity 12 and the air outlet slits on the rear surface of the impact cavity 12 are symmetrically arranged. The adjustment of the parameters of the air outlet slit 121 can refer to the jet hole 31.
As shown in fig. 1 and 3, multiple layers of porous medium fillers 2 are spread in the impact cavity 12 along the expansion direction to form an enhanced heat exchange area in an ice accumulation focal area. The porosity and pore size of each layer of porous medium filler can be adjusted. The pore diameter of the porous medium filler 2 is reduced from top to bottom layer by layer. The porous medium filler 2 has uniform porosity and uniform pore diameter in the same layer, and has the same flow property along all directions. The thickness and the layer number of the porous medium filler 2 are adjusted according to the internal flow resistance and the anti-icing uniformity requirement of the surface of the component, the pore size of each layer of the porous medium filler can be adjusted according to the flow resistance characteristic, but the integral change rule of the pore size among the layers is not changed. In this embodiment, the porous media filler 2 has six layers. The porous medium filler 2 has the characteristics of light weight and high porosity, and the porous medium conforming to the characteristics can be non-metallic porous materials such as graphite foam, gypsum, ceramic and the like, or foam metal prepared by taking metals such as Cu, Al, Ni and the like and alloys thereof as raw materials. In this embodiment, foamed aluminum is used as the porous medium filler 2, the porosity of the foamed metal is 0.9, and the pore diameters of the six foamed metal layers from top to bottom along the leaf height direction are 1.6mm, 1.4mm, 1.2mm, 1.0mm, 0.8mm and 0.6mm in sequence. The thicknesses of the components are 62.9mm, 60.0mm, 60.0mm, 60.0mm, 60.0mm and 72.9mm in sequence. When the temperature of the bleed air is 420K, the amount of the bleed air is 5g/s, and the temperature of the working environment is 263.15K, the average temperature of the surface of the obtained rectifying support plate is 328.5K, the lowest temperature is 292.8K, the temperature values which are respectively higher than the freezing point are 55.5K and 19.8K, and the sufficient anti-icing effect can be achieved.
In this embodiment, a rectifying support plate made of aluminum metal is selected as the anti-icing component 1. As shown in fig. 4, comparing the flow distribution of the impact chamber 12 inside the flow straightening plate under three conditions of filling six layers of foam metal with different pore diameters, not filling foam metal and filling only one pore diameter foam metal, after filling foam metal, the flow of the jet holes at the bottom and the top of the flow straightening plate is slightly reduced, while the flow of the jet holes at the middle section is increased, and the flow distribution characteristic is improved. As shown in FIG. 5, the leading edge of the rectifying support plate which is most prone to icing is selected as an object, and compared with the surface temperature distribution under the same three conditions, compared with the condition that foam metal is not filled, the temperature of the hot gas protection area after filling is obviously increased, and the average temperature is increased by more than 10K. Therefore, the anti-icing structure effectively improves the heat exchange between heat flow and the protective component, and enhances the anti-icing effect. In practical application, the hot gas condition can be further reduced, and the anti-icing heat exchange structure with low consumption and high efficiency is obtained. The invention takes an aircraft engine rectifying support plate as an example, on one hand, the splitter plate is additionally arranged to distribute heat flow so as to improve the protection uniformity of parts, and on the other hand, the anti-icing effect of hot gas is obviously improved by combining an internal filling means of an excellent heat exchange material on the basis of the design of a hot gas flowing structure.
Claims (6)
1. The utility model provides an anti-icing structure suitable for aeroengine rectification extension board and wing which characterized in that: the anti-icing device comprises an anti-icing component (1), wherein a partition plate (3) is arranged in the anti-icing component (1), the partition plate (3) divides the inner space of the anti-icing component (1) into an air inlet cavity (11) and an impact cavity (12), a jet hole (31) is formed in the partition plate (3), the air inlet cavity (11) is communicated with the impact cavity (12) through the jet hole (31), and convection-impact heat exchange of heat flow between the air inlet cavity (11) and the impact cavity (12) is formed; a flow distribution plate (111) is vertically arranged in the air inlet cavity (11), an air inlet (112) is formed in the top of the air inlet cavity on the right side of the flow distribution plate (111), and intervals are reserved between the two ends of the flow distribution plate (111) and the top surface and the bottom surface of the anti-icing part (1) to form a channel for forward heat flow conveying; a plurality of layers of porous medium fillers (2) are laid in the impact cavity (12) along the expansion direction, and an air outlet slit (121) is formed in the surface of the impact cavity (12);
the pore diameter of the porous medium filler (2) is reduced layer by layer from top to bottom, and the thickness and the layer number of the porous medium filler (2) are adjusted according to the internal flow resistance and the anti-icing requirement.
2. The anti-icing structure for aircraft engine fairing plates and wings as claimed in claim 1, wherein: the porosity of the porous medium filler (2) in the same layer is consistent, the pore diameter is uniform, and the flow properties along all directions are the same.
3. The anti-icing structure for aircraft engine fairing plates and wings as claimed in claim 1, wherein: the material of the porous medium filler (2) is a non-metal porous material or foam metal prepared by taking metal and alloy thereof as raw materials.
4. The anti-icing structure for aircraft engine fairing plates and wings as claimed in claim 1, wherein: the jet holes (31) are multiple in number and are arranged according to a single-row equidistant rule.
5. The anti-icing structure for aircraft engine fairing plates and wings as claimed in claim 1, wherein: two rows of air outlet slits (121) are respectively formed in the front surface and the rear surface of the impact cavity (12), the air outlet slits on the same surface are distributed in a fork row mode, and the air outlet slits on the front surface of the impact cavity (12) and the air outlet slits on the rear surface of the impact cavity (12) are symmetrically arranged.
6. An anti-icing structure for aeroengine fairing plates and wings as claimed in any one of claims 1 to 5, wherein: the anti-icing component (1) is made of metal aluminum.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011470796.9A CN112682174B (en) | 2020-12-15 | 2020-12-15 | Anti-icing structure suitable for aeroengine extension board and wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011470796.9A CN112682174B (en) | 2020-12-15 | 2020-12-15 | Anti-icing structure suitable for aeroengine extension board and wing |
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| Publication Number | Publication Date |
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| CN112682174A CN112682174A (en) | 2021-04-20 |
| CN112682174B true CN112682174B (en) | 2022-04-19 |
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| CN202011470796.9A Active CN112682174B (en) | 2020-12-15 | 2020-12-15 | Anti-icing structure suitable for aeroengine extension board and wing |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113864058B (en) * | 2021-10-29 | 2024-04-09 | 中国航发沈阳发动机研究所 | Aeroengine air inlet casing support plate and frame and assembly method thereof |
| CN114876638B (en) * | 2022-05-16 | 2023-05-09 | 南京航空航天大学 | Hot gas anti-icing structure of aeroengine rectification support plate |
| CN114922734B (en) * | 2022-06-10 | 2023-05-23 | 南京航空航天大学 | Uniform temperature rectification support plate hot gas anti-icing structure based on rib column partition turbulence |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB793949A (en) * | 1954-11-12 | 1958-04-23 | T K S Aircraft De Icing Ltd | Improvements relating to means for distributing fluids |
| US5029440A (en) * | 1990-01-26 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Acoustical anti-icing system |
| CA2731974A1 (en) * | 2008-07-30 | 2010-02-04 | Aircelle | Acoustic attenuation panel for aircraft engine nacelle |
| CN106703997B (en) * | 2016-12-19 | 2018-08-24 | 北京航空航天大学 | Lean forward seam engine support plate hot air anti-icing structure |
| RU177516U1 (en) * | 2017-07-21 | 2018-02-28 | Научно-производственная ассоциация "Технопарк Авиационных Технологий" | Paddle for adjustable inlet guide vane |
| CN111561393A (en) * | 2020-05-22 | 2020-08-21 | 中国航发沈阳发动机研究所 | Support plate structure and air inlet casing frame with same |
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