CN105599906A - Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device - Google Patents
Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device Download PDFInfo
- Publication number
- CN105599906A CN105599906A CN201610056438.0A CN201610056438A CN105599906A CN 105599906 A CN105599906 A CN 105599906A CN 201610056438 A CN201610056438 A CN 201610056438A CN 105599906 A CN105599906 A CN 105599906A
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- Prior art keywords
- aero
- heat pipe
- condensation segment
- section
- engine
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/06—Liquid application
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
Abstract
The invention discloses an aero-engine rectification cover hood anti-icing device adopting a loop type heat pipe and belongs to the field of protection of aero-engines. The aero-engine rectification cover hood anti-icing device comprises a loop type axial rotary heat pipe, wherein the axial rotary heat pipe sequentially comprises a condensation section, a heat insulation section and an evaporation section from front to back; the front end of the condensation section is fitted to an aero-engine rectification cover hood; the inner diameter of the front part of the condensation section is greater than that of the back part of the condensation section; the inner diameter from the evaporation section to the heat insulation section is gradually reduced; the inner diameter of the heat insulation section is greater than the maximum inner diameter of the condensation section; a liquid reflowing channel is communicated between the condensation section and the heat insulation section; an inlet of the liquid reflowing channel is located at the condensation section and an outlet of the liquid reflowing channel is located at the heat insulation section; a heating device is mounted on the evaporation section. The loop type axial rotary heat pipe is integrated on the inner surface of the aero-engine rectification cover hood so that generated heat is efficiently and stably transmitted to the surface of the aero-engine rectification cover hood, and anti-icing of the aero-engine rectification cover hood is realized.
Description
Technical field
The present invention relates to a kind of aero-engine rectification calotte anti-icing equipment, is specifically a kind of aero-engine rectification calotte anti-icing equipment and method that adopts loop type heat pipe, belongs to aero-engine protection field.
Background technology
The icing phenomenon of aero-engine rectification calotte has a strong impact on the normal performance of aero-engine performance, even jeopardizes the safety of aero-engine, causes aviation accident. In order to prevent that aero-engine rectification calotte from freezing and conventionally need to carry out heat treated to it in flight course, traditional hot air anti-icing Technology Need is used for anti-icing from compressor bleed, the steam of this part consumption can affect engine work efficiency, and its complex structure, poor stability, and increased regular maintenance difficulty. The electrical heating anti-icing system that part adopts at present, though it is simple in structure, it is convenient to control, but inevitably wants the high-grade electric energy that quantity consumed is considerable.
Summary of the invention
Technical problem to be solved by this invention is to overcome prior art defect, provides a kind of and reduces motor power loss without from compressor bleed, avoids aero-engine rectification calotte anti-icing equipment and the method for the employing loop type heat pipe of power consumption.
In order to solve the problems of the technologies described above, a kind of aero-engine rectification calotte anti-icing equipment that adopts loop type heat pipe provided by the invention, comprise axial-rotation heat pipe, described axial-rotation heat pipe is followed successively by condensation segment, adiabatic section and evaporator section after by forward direction, the front end of described condensation segment and the laminating of aero-engine rectification calotte, the anterior internal diameter of condensation segment is greater than rear portion internal diameter; Described evaporator section diminishes gradually to the internal diameter of adiabatic section, and adiabatic section internal diameter is greater than the maximum inner diameter of condensation segment; Between described condensation segment and adiabatic section, be communicated with liquid reflux channel, the import of liquid reflux channel is positioned at condensation segment, and outlet is positioned at adiabatic section; On described evaporator section, heater is installed, described heater and evaporator section carry out exchange heat.
In the present invention, described condensation segment comprises the first condensation segment and the second condensation segment, and described the first condensation segment is positioned at axial-rotation heat pipe fits with aero-engine rectification calotte foremost, and the front inner diameter of the second condensation segment is greater than back end inside diameter; The import of described liquid reflux channel is positioned on the first condensation segment, and liquid reflux channel forms along the first condensation segment to external expansion and the laminating of aero-engine rectification calotte, between described liquid reflux channel and the first condensation segment, fills Heat Conduction Material.
In the present invention, the outlet of described liquid reflux channel is positioned at front portion or the rear portion of adiabatic section.
In the present invention, described heater is hot fluid cover, and described hot fluid cover is arranged on evaporator section, in hot fluid cover, is provided with hot fluid circulation passage. Hot fluid has multiple choices, as lubricating oil, and fuel oil, high temperature air.
In the present invention, the shell material of described axial-rotation heat pipe is determined by the working media in axial-rotation heat pipe.
The present invention also provides the anti-icing method of the aero-engine rectification calotte anti-icing equipment of above-mentioned employing loop type heat pipe, comprises the following steps:
1), axial-rotation heat pipe rotates around central shaft, the heat of vaporization that the liquid absorption external heat source of evaporator section imports into is steam, steam arrives condensation segment through adiabatic section under the effect of pressure reduction;
2), steam is condensed into liquid at condensation segment, after its condensation, liberated heat is delivered to the aero-engine rectification calotte surface of fitting with the first condensation segment, liquid reflux channel through condensation segment, it is heated, maintain the temperature of aero-engine rectification calotte outer surface more than apparent freezing point;
3), under the action of the centrifugal, the suffered pressure of the liquid of liquid reflux channel import department is greater than the suffered pressure of exit liquid, makes condensed liquid get back to evaporator section from liquid reflux channel, goes round and begins again.
In the present invention, described liquid working media is determined according to the operating temperature range of condensation segment and evaporator section.
Beneficial effect of the present invention is: (1), loop type axial-rotation heat pipe is integrated in to the inner surface of aero-engine rectification calotte, make the heat producing efficiently, stably be passed to aero-engine rectification calotte surface, realize airplane engine cowling anti-icing, it need to be from compressor bleed, reduce motor power loss, do not need the labyrinths such as air cavity, avoid the consumption for anti-icing high-grade electric energy; (2), condensation segment and aero-engine rectification calotte inner surface directly fit, and reduces the heat transfer resistance of rectification calotte and condensation segment, ensured the anti-icing effect of heating; (3), adopt liquid reflux channel, thereby steam channel is separated or all separation with fluid passage part, reduce the steam that causes due to the gas-liquid reverse flow resistance to liquid, be conducive to improve heat-transfer capability, simultaneously can be by the heat convection heating rectification calotte of liquid in branch road; (4), utilize the used heat of lubricating oil anti-icing, it does not only consume other utilisable energy, and has taken into account the cooling of lubricating oil, energy-conserving and environment-protective; (5), the outlet of liquid reflux channel is located at the rear portion of adiabatic section, can further reduce the impact of vapor flow on liquid; (6), the present invention is simple in structure, volume is little, quality is light, heat transfer efficiency is high.
Brief description of the drawings
Fig. 1 is the aero-engine rectification calotte anti-icing equipment structural representation that the present invention adopts loop type heat pipe;
Fig. 2 is Fig. 1 course of work schematic diagram;
Fig. 3 is the aero-engine rectification calotte anti-icing equipment structural representation that embodiment 2 adopts loop type heat pipe;
Fig. 4 is Fig. 3 course of work schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing and example, technical scheme of the present invention is described further.
As shown in Figure 1, 2, the aero-engine rectification calotte anti-icing equipment of the employing loop type heat pipe in the embodiment of the present invention 1, comprises axial-rotation heat pipe 7, lubricating oil cover 8 and liquid reflux channel 2. Axial-rotation heat pipe 7 is established the first condensation segment 1, the second condensation segment 3, adiabatic section 5 and evaporator section 6 from front to back successively, and axial-rotation heat pipe 7 rotates around central shaft under external force drives, and the tube wall of axial-rotation heat pipe 7 is fine copper and makes.
Lubricating oil cover 8 is arranged on the evaporator section 6 of axial-rotation heat pipe 7, in lubricating oil cover 8, be provided with lubricating oil circulation canal, the import of circulation canal and outlet connecting engine oil system, high temperature lubricating oil in engine in lubricating oil cover 8 with axial-rotation heat pipe 7 on evaporator section 6 carry out exchange heat, evaporator section 6 is in the heat absorbing from motor oil, and lubricating oil has also been realized and having been cooled.
The first condensation segment 1 is positioned at axial-rotation heat pipe 7 foremost, is taper seat structure, fits, to reduce the heat transfer resistance of aero-engine rectification calotte 4 and the first condensation segment 1 with aero-engine rectification calotte 4. The second condensation segment 3 communicates with the first condensation segment 1, is anti-tapered configuration, and the inner diameter D 1 of the second condensation segment 3 front ends is greater than the inner diameter D 2 of rear end.
Evaporator section 6 diminishes gradually to the internal diameter of adiabatic section 5, and the inner diameter D 3 of adiabatic section 5 is greater than the inner diameter D 1 of the second condensation segment 3 front ends, and evaporator section 6 is constant to the external diameter of adiabatic section 5.
Liquid reflux channel 2 be arranged on condensation segment and adiabatic section 5 between, import is positioned on the first condensation segment 1, outlet be positioned at adiabatic section 5 foremost. Liquid reflux channel 2 is expanded laterally along the medial surface of the first condensation segment 1, and combines closely with aero-engine rectification calotte 4, to reduce and the heat transfer resistance of aero-engine rectification calotte. Liquid reflux channel 2 does insulation with rectification calotte 4 and the discontiguous part of Heat Conduction Material and processes. Liquid reflux channel 2 is full of liquid working media down in working order, as absolute ethyl alcohol. Liquid working media in axial-rotation heat pipe 7 determined by the operating temperature range of condensation segment and evaporator section 6, and axial-rotation heat pipe 7 shell materials are determined by the working media being filled with in axial-rotation heat pipe 7, and it can be selected according to concrete application. In the present embodiment, axially rotating heat pipe is chosen absolute ethyl alcohol as working media, and according to material compatibility principle, selecting shell material is fine copper.
The first condensation segment 1 on axial-rotation heat pipe 7, liquid reflux channel 2 and the 4 inner surface laminatings of aero-engine rectification calotte.
The Heat Conduction Material that gap location packed density is less, thermal conductivity factor is higher between liquid reflux channel 2 and the second condensation segment 3, as foam copper.
As shown in Figure 2, the concrete anti-icing process of aero-engine rectification calotte anti-icing equipment of above-mentioned employing loop type heat pipe is:
1), axial-rotation heat pipe rotates around central shaft under external force drives;
2) it is steam that the absolute ethyl alcohol, in evaporator section absorbs the heat of vaporization that lubricating oil imports into, and steam arrives the second condensation segment and the first condensation segment under the effect of pressure reduction behind adiabatic section;
3), a steam part is condensed into liquid at the first condensation segment, another part arrives the second condensation segment and is condensed into liquid;
4), steam liberated heat after condensation is delivered to aero-engine rectification calotte surface through the first condensation segment, the second condensation segment and liquid reflux channel, and it is heated, and maintains the temperature of rectification calotte outer surface on apparent freezing point;
5), because the second condensation segment is anti-tapered configuration, direction along the first condensation segment to evaporator section, bore reduces gradually, and the bore D3 in liquid reflux channel exit is greater than the bore D1 of liquid reflux channel import department, cause the liquid level of import and export apart from the distance difference of the rotating shaft of axial-rotation heat pipe, and P point is identical with the distance h of rotating shaft with Q point place liquid level, and P point is positioned at top, inlet liquid level place, Q point is positioned at outlet liquid level place, the suffered pressure of P point liquid is greater than the suffered pressure of Q point liquid under the action of the centrifugal, make liquid get back to evaporator section from liquid reflux channel, go round and begin again, realize circulating-heating anti-icing.
As shown in Figures 3 and 4, the structure of the structure of embodiment 2 and embodiment 1 is basically identical, difference is that liquid reflux channel 2 outlets are positioned at the rearward end of adiabatic section 5, approach evaporator section 6, can further reduce so in the course of the work the impact of vapor flow on liquid reflux channel institute trickle in adiabatic section 5. Embodiment 2 will possess mounting condition in concrete assembling process, can change the position of liquid reflux channel 2 at adiabatic section place completely if discontented.
Compared with the anti-icing method of tradition, axial-rotation heat pipe of the present invention has the design feature of liquid reflux channel, thereby steam channel is separated or all separation with fluid passage part, reduce the steam that causes due to the gas-liquid reverse flow resistance to liquid,, and by the heat convection heating rectification calotte of liquid in liquid reflux channel, improve anti-icing effect, reduce for pressure-air anti-icing and that draw from compressor, reduce the loss of motor power.
Above-mentioned detailed description of the invention is the preferred embodiments of the present invention, can not limit the present invention, and other any change or other equivalent substitute mode that does not deviate from technical scheme of the present invention and make, within being included in protection scope of the present invention.
Claims (8)
1. one kind adopts the aero-engine rectification calotte anti-icing equipment of loop type heat pipe, it is characterized in that: comprise axial-rotation heat pipe, described axial-rotation heat pipe is followed successively by condensation segment, adiabatic section and evaporator section after by forward direction, the front end of described condensation segment and the laminating of aero-engine rectification calotte, the anterior internal diameter of condensation segment is greater than rear portion internal diameter; Described evaporator section diminishes gradually to the internal diameter of adiabatic section, and adiabatic section internal diameter is greater than the maximum inner diameter of condensation segment; Between described condensation segment and adiabatic section, be communicated with liquid reflux channel, the import of liquid reflux channel is positioned at condensation segment, and outlet is positioned at adiabatic section; On described evaporator section, heater is installed, described heater and evaporator section carry out exchange heat.
2. the aero-engine rectification calotte anti-icing equipment of employing loop type heat pipe according to claim 1, it is characterized in that: described condensation segment comprises the first condensation segment and the second condensation segment, described the first condensation segment is positioned at axial-rotation heat pipe fits with aero-engine rectification calotte foremost, and the front inner diameter of the second condensation segment is greater than back end inside diameter; The import of described liquid reflux channel is positioned on the first condensation segment, and liquid reflux channel forms along the first condensation segment to external expansion and the laminating of aero-engine rectification calotte, between described liquid reflux channel and the first condensation segment, fills Heat Conduction Material.
3. the aero-engine rectification calotte anti-icing equipment of employing loop type heat pipe according to claim 1 and 2, is characterized in that: the outlet of described liquid reflux channel is positioned at front portion or the rear portion of adiabatic section.
4. the aero-engine rectification calotte anti-icing equipment of employing loop type heat pipe according to claim 3, is characterized in that: described heater is hot fluid cover, and described hot fluid cover is arranged on evaporator section, in hot fluid cover, is provided with hot fluid circulation passage.
5. the aero-engine rectification calotte anti-icing equipment of employing loop type heat pipe according to claim 4, is characterized in that: the material of described axial-rotation heat pipe is determined according to the liquid working media in axial-rotation heat pipe.
6. the aero-engine rectification calotte anti-icing equipment of employing loop type heat pipe according to claim 1 and 2, is characterized in that: described heater is hot fluid cover, and described hot fluid cover is arranged on evaporator section, in hot fluid cover, is provided with hot fluid circulation passage.
7. an anti-icing method that adopts the aero-engine rectification calotte anti-icing equipment of loop type heat pipe described in claim 1, is characterized in that comprising the following steps:
1), axial-rotation heat pipe rotates around central shaft, it is steam that the liquid working media of evaporator section absorbs the heat of vaporization that external heat source imports into, steam arrives condensation segment through adiabatic section under the effect of pressure reduction;
2), steam is condensed into liquid at condensation segment, after its condensation, liberated heat is delivered to and the aero-engine rectification calotte surface of the first condensation segment, liquid reflux channel laminating through condensation segment, and it is heated;
3), under the action of the centrifugal, the suffered pressure of the liquid of liquid reflux channel import department is greater than the suffered pressure of exit liquid, makes condensed liquid get back to evaporator section from liquid reflux channel, goes round and begins again.
8. the anti-icing method that adopts according to claim 7 the aero-engine rectification calotte anti-icing equipment of loop type heat pipe, is characterized in that: the working media of described rotating heat pipe is determined according to the operating temperature range of condensation segment and evaporator section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610056438.0A CN105599906A (en) | 2016-01-28 | 2016-01-28 | Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610056438.0A CN105599906A (en) | 2016-01-28 | 2016-01-28 | Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device |
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| CN105599906A true CN105599906A (en) | 2016-05-25 |
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| CN201610056438.0A Pending CN105599906A (en) | 2016-01-28 | 2016-01-28 | Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005430A (en) * | 2016-06-30 | 2016-10-12 | 天津曙光天成科技有限公司 | Wing anti-freezing structure and aircraft adopting same |
| CN106475361A (en) * | 2016-10-14 | 2017-03-08 | 上海工程技术大学 | A kind of utilization temperature difference induction icing the method for Concentration De-ice |
| CN108981433A (en) * | 2018-08-16 | 2018-12-11 | 中国矿业大学 | A kind of heating of rotating heat pipe, cooling and safety device |
| CN110318883A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of aero-engine calotte single hole impingement heat transfer structure in helical curve channel |
| CN110720020A (en) * | 2017-07-06 | 2020-01-21 | 麦克赛尔株式会社 | Heat transport device and projection type image display apparatus |
| CN114109536A (en) * | 2021-11-15 | 2022-03-01 | 江苏迈信林航空科技股份有限公司 | Engine impeller cover and machining process thereof |
| CN114483314A (en) * | 2022-02-24 | 2022-05-13 | 南京航空航天大学 | Cap heat exchange structure with porous jet impact |
| US20220212806A1 (en) * | 2019-11-12 | 2022-07-07 | Subaru Corporation | Propulsion system, anti-icing method of rotor and aircraft |
| CN114750963A (en) * | 2022-06-16 | 2022-07-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-temperature thermal diode anti-icing device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005430A (en) * | 2016-06-30 | 2016-10-12 | 天津曙光天成科技有限公司 | Wing anti-freezing structure and aircraft adopting same |
| CN106475361A (en) * | 2016-10-14 | 2017-03-08 | 上海工程技术大学 | A kind of utilization temperature difference induction icing the method for Concentration De-ice |
| CN110720020A (en) * | 2017-07-06 | 2020-01-21 | 麦克赛尔株式会社 | Heat transport device and projection type image display apparatus |
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| CN114750963A (en) * | 2022-06-16 | 2022-07-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-temperature thermal diode anti-icing device |
| CN114750963B (en) * | 2022-06-16 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-temperature thermal diode anti-icing device |
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Application publication date: 20160525 |