CN103850800B - Intake duct deicer and civilian turbofan engine - Google Patents
Intake duct deicer and civilian turbofan engine Download PDFInfo
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- CN103850800B CN103850800B CN201210496822.4A CN201210496822A CN103850800B CN 103850800 B CN103850800 B CN 103850800B CN 201210496822 A CN201210496822 A CN 201210496822A CN 103850800 B CN103850800 B CN 103850800B
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Abstract
The present invention relates to a kind of intake duct deicer and civilian turbofan engine, device comprises: bleed structure, internal heat structure, air-flow heating arrangement and exhaust structure, bleed structure comprises the air entraining jet and bleed conduit that are arranged on fan rectifying cover outer wall, internal heat vibrational power flow is in fan cabin, and communicate with bleed conduit, air-flow heating arrangement comprises anti-icing conduit and is positioned at the D shape ring cavity of inlet lip of motor, anti-icing conduit communicates with internal heat structure and D shape ring cavity respectively, exhaust structure comprises the outlet being arranged on D shape ring cavity and the relief opening being arranged on fan rectifying cover outer wall, the outlet of D shape ring cavity communicates with relief opening.The present invention utilizes bleed structure to obtain outside ambient air, and will treat that heat exchanger components carries out exchange heat in the ambient air of low temperature and fan cabin by internal heat structure, air after heating is introduced into air-flow heating arrangement again and heats inlet lip, thus meets the anti-icing demand of engine inlets.
Description
Technical field
The present invention relates to aeroengine field, particularly relate to a kind of intake duct deicer and civilian turbofan engine.
Background technique
Along with the development of society, the living standard of the mankind improves constantly, civil aviation as one conveniently trip mode obtain vigorous growth.Meanwhile, people have higher requirement to the Security of civil aircraft, Economy, travelling comfort.Civilian turbofan engine is as the power plant of current large-scale airline carriers of passengers, and its intake duct ice formation issues is one of key factor of the whole power plant performance of impact and Security.Because intake duct air is in aspiration phases, airspeed increases, and static temperature reduces, and makes these parts very easily icing.And intake duct freezes and can change the aerodynamic characteristics of gas handling system, increase flow resistance, make inlet flow field skewness, flow distortion even occurs, affect the working stability of motor, flame-out parking time serious, may be caused.Intake duct freezes also may cause and melts the ice cube that comes off and sucked by motor, produces the serious problems of engine foreign object damage.Therefore, the intake duct of civilian turbofan engine must adopt anti-icing design.
The intake duct of existing civilian turbofan engine mainly adopts the anti-icing two kind modes anti-icing with gas of electricity.The anti-icing mode of electricity is convenient to the heat controlling heating, and according to the operation conditions of motor, can regulate the power of electric heater, thus electric heater runs relatively little for the impact of engine power, and can not produce the shock effect of air-flow.Adopt electric heating system, can regulate heating electricity and heating frequency according to the icing form of different parts, freezing environment difference, directionality is better.US20060237582A1 proposes a kind of double walled intake duct electricity ice prevention structure, and the internal layer of this intake duct devises a service ports, makes the maintenance of associated heater and installs very convenient.Because electric heating device needs to introduce power supply from engine accessory power rating, add motor for electrical load, and be not as anti-icing as gas in system reliability, thus current adopt in the civilian turbofan engine of main flow few.
Hot gas anti-icing system generally adopts the high temperature air drawing high-pressure compressor, is delivered to intake duct leading edge by pressure regulating valve or direct bleed, to needing anti-icing parts heating to play anti-icing effect.The controllability that the anti-icing mode of gas has heat is good, and structure is simple, and good reliability, be content with very little anti-icing requirement, and apply the advantages such as more extensive, relevant research and patent are also more.As US4738416 to have the metallic walls of similar profile by laying one deck and intake duct wall, forming a comparatively narrow heat tunnel, improve airspeed when bleed flow is certain and namely enhance heat transfer effect, improve anti-icing efficiency.US20080179448A1 proposes the design of a kind of intake duct hot air anti-icing with cellular structure, this design can realize gas anti-icing while suppress intake duct noise.
But, hot air anti-icing all must from engine core power traction gas (being generally high-pressure compressor bleed), this must bring the reduction of engine performance, therefore how while meeting the anti-icing demand of engine inlets, improve the utilization ratio of anti-icing hot gas to greatest extent, reduce the key that engine bleed amount is civilian turbofan engine gas anti-icing design as far as possible.
Summary of the invention
The object of the invention is to propose a kind of intake duct ice prevention structure and civilian turbofan engine, can, while meeting the anti-icing demand of engine inlets, avoid reducing engine performance as far as possible.
For achieving the above object, the invention provides a kind of intake duct deicer, comprise: bleed structure, internal heat structure, air-flow heating arrangement and exhaust structure, described bleed structure comprises the air entraining jet being arranged on fan rectifying cover outer wall and the bleed conduit communicated with described air entraining jet, described internal heat vibrational power flow is in fan cabin, and communicate with described bleed conduit, described air-flow heating arrangement comprises anti-icing conduit and is positioned at the D shape ring cavity of inlet lip of motor, described anti-icing conduit communicates with described internal heat structure and described D shape ring cavity respectively, described exhaust structure comprises the outlet being arranged on described D shape ring cavity and the relief opening being arranged on described fan rectifying cover outer wall, the outlet of described D shape ring cavity communicates with described relief opening.
Further, described D shape ring cavity is formed by the inner and outer wall of the inlet lip of described motor and the intake duct bulkhead be arranged in described fan cabin.
Further, described internal heat structure is be set in the heat exchange box treating heat exchanger components outside and/or the internal heat passage treating heat exchanger components.
Further, described in treat that heat exchanger components is engine accessory power rating, described internal heat structure is the heat exchange box being set in described engine accessory power rating outside, carries out exchange heat by the metal wall on described engine accessory power rating surface and the Cryogenic air flowing through heat exchange box.
Further, the volume of described heat exchange box is between the volume of described engine accessory power rating and 1.5 times of the volume of described engine accessory power rating.
Further, describedly treat that heat exchanger components is engine electronic control (EngineElectronicController, be called for short EEC), described internal heat structure is the internal heat passage of described engine electronic control, carries out exchange heat by the internal heat passage of described engine electronic control with the Cryogenic air flow through.
Further, described air entraining jet is flush type spade air entraining jet.
Further, the outlet side of described anti-icing conduit is positioned at the front portion of described D shape ring cavity.
Further, the inner circle sectional area of described bleed conduit and anti-icing conduit is not less than 0.3 times of the inner circle area of described air entraining jet, and the inner circle area of described relief opening is not less than the inner circle area of described air entraining jet.
Further, described air entraining jet is arranged on the top of described fan fairing, and described relief opening is arranged on the bottom of described fan fairing.
Further, described air entraining jet comprises the first air entraining jet and the second air entraining jet, described relief opening comprises first row gas port and second exhaust port, described bleed conduit comprises the first bleed conduit and the second bleed conduit, described anti-icing conduit comprises the first anti-icing conduit and the second anti-icing conduit, in described fan cabin, treat that heat exchanger components comprises engine accessory power rating and engine electronic control, described first air entraining jet is by the heat exchange box of described first bleed tubes connection to described engine accessory power rating outside, and described heat exchange box is by the inside of described first anti-icing tubes connection to described D shape ring cavity, described second air entraining jet is by the internal heat passage of described second bleed tubes connection to described engine electronic control, and described internal heat passage is by the inside of described second anti-icing tubes connection to described D shape ring cavity.
Further, the circumferential angle that described first anti-icing conduit enters the entrance of described D shape ring cavity and the outlet of described D shape ring cavity is not less than 90 degree, and the circumferential angle that described second anti-icing conduit enters the entrance of described D shape ring cavity and the outlet of described D shape ring cavity is not less than 90 degree.
Based on technique scheme, the present invention utilizes bleed structure to obtain outside ambient air, and will treat that heat exchanger components carries out exchange heat in the ambient air of low temperature and fan cabin by internal heat structure, air after heating is introduced into air-flow heating arrangement again and heats inlet lip, thus reach the anti-icing object of intake duct, meet the anti-icing demand of engine inlets, and do not need from engine bleed due to bleed structure of the present invention, therefore also can not impact the performance of motor, add without the need to arranging anti-icing bleed air line on the engine, also the weight of motor is relatively alleviated, utilize the ambient air of low temperature to treat that heat exchanger components carries out exchange heat simultaneously in internal heat structure and fan cabin, achieve the cooling treating heat exchanger components and fan cabin, ensure that the normal work treating heat exchanger components and fan cabin.
In another embodiment, described D shape ring cavity is formed by the inner and outer wall of the inlet lip of described motor and the intake duct bulkhead be arranged in described fan cabin.D shape ring cavity can realize the concentrated heating being directed to inlet lip position, reaches the anti-icing effect of better intake duct.
In another embodiment, described internal heat structure is be set in the heat exchange box treating heat exchanger components outside and/or the internal heat passage treating heat exchanger components.Internal heat structure selects the heat exchange mode of outside or inside according to the difference treating heat exchanger components, such as when when heat exchanger components is engine accessory power rating, described internal heat structure is the heat exchange box being set in described engine accessory power rating outside, carries out exchange heat by the metal wall on described engine accessory power rating surface with the Cryogenic air flowing through heat exchange box; When heat exchanger components is EEC, described internal heat structure is the internal heat passage of described EEC, carries out exchange heat by the internal heat passage of described EEC with the Cryogenic air flow through.
For treating that heat exchanger components is engine accessory power rating, internal heat structure is heat exchange box, then the volume of preferred heat exchange box is between the volume of described engine accessory power rating and 1.5 times of the volume of described engine accessory power rating, to ensure the heating effect of engine accessory power rating to the Cryogenic air passed through.
In another embodiment, described air entraining jet is flush type spade air entraining jet, and this structural type has lower frontal resistance, can reduce the impact on nacelle starting performance to the full extent.
In another embodiment, the outlet side of described anti-icing conduit is positioned at the front portion of described D shape ring cavity, namely near the entrance location of engine inlets, to ensure that high temperature gas flow from internal heat structure is fully to the heating effect of D shape ring cavity.
In another embodiment, the inner circle sectional area of described bleed conduit and anti-icing conduit is not less than 0.3 times of the inner circle area of described air entraining jet, the inner circle area of described relief opening is not less than the inner circle area of described air entraining jet, to reduce the flow losses of air-flow in fan cabin, D shape ring cavity and conduit.
In another embodiment, described air entraining jet is arranged on the top of described fan fairing, and described relief opening is arranged on the bottom of described fan fairing.The layout of such porting, can allow ambient windstream carry out sufficient heat exchange in fan cabin, makes air-flow can implement available ventilation and cooling to the space of the fan cabin overwhelming majority.
In another embodiment, described air entraining jet comprises the first air entraining jet and the second air entraining jet, described relief opening comprises first row gas port and second exhaust port, described bleed conduit comprises the first bleed conduit and the second bleed conduit, described anti-icing conduit comprises the first anti-icing conduit and the second anti-icing conduit, in described fan cabin, treat that heat exchanger components comprises engine accessory power rating and EEC, described first air entraining jet is by the heat exchange box of described first bleed tubes connection to described engine accessory power rating outside, and described heat exchange box is by the inside of described first anti-icing tubes connection to described D shape ring cavity, described second air entraining jet is by the internal heat passage of described second bleed tubes connection to described EEC, and described internal heat passage is by the inside of described second anti-icing tubes connection to described D shape ring cavity.Utilize engine accessory power rating and EEC to carry out air heating simultaneously, and the high temperature air after heating is guided to D shape ring cavity and carried out hot air anti-icing, better anti-icing effect can be realized, also all cooling action is achieved to engine accessory power rating and EEC simultaneously, ensure that the normal work of engine accessory power rating and EEC.
In another embodiment, the circumferential angle that described first anti-icing conduit enters the entrance of described D shape ring cavity and the outlet of described D shape ring cavity is not less than 90 degree, the circumferential angle that described second anti-icing conduit enters the entrance of described D shape ring cavity and the outlet of described D shape ring cavity is not less than 90 degree, to ensure that high temperature gas flow from internal heat structure is fully to the heating effect of D shape ring cavity.
For achieving the above object, the invention provides a kind of civilian turbofan engine, comprise fan and fan cabin, wherein also comprise aforesaid intake duct deicer.
Based on technique scheme, the civilian turbofan engine of the present invention is owing to have employed aforesaid intake duct deicer, not only can reach the anti-icing object of intake duct, and due to without the need to from engine bleed, therefore also can not impact the performance of motor, adding without the need to arranging anti-icing bleed air line on the engine, also relatively alleviating the weight of motor; Utilize the ambient air of low temperature to treat that heat exchanger components carries out exchange heat simultaneously in internal heat structure and fan cabin, achieve the cooling treating heat exchanger components and fan cabin, ensure that the normal work treating heat exchanger components and fan cabin.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, and form a application's part, schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of an embodiment of intake duct deicer of the present invention.
Fig. 2 is the structural representation of another embodiment of intake duct deicer of the present invention.
Fig. 3 is the air circumferential flow schematic diagram in the D shape ring cavity of intake duct deicer embodiment of the present invention.
Embodiment
Below by drawings and Examples, technological scheme of the present invention is described in further detail.
Intake duct deicer of the present invention is at least by bleed structure, internal heat structure, air-flow heating arrangement and exhaust structure four part-structure composition, bleed structure is responsible for introducing outside ambient air, the Cryogenic air that internal heat structure is responsible for heat and the introducing produced by the heating component in fan cabin exchanges, ambient air is made to be heated into high temperature air, and high temperature air is introduced in air-flow heating arrangement to improve the temperature of inlet location, suppress the formation of ice sheet, and the air turned cold after circulation in air-flow heating arrangement is discharged by exhaust structure again.
Fig. 1 and Fig. 2 is respectively the embodiment of two kinds of intake duct deicers, in these two embodiments, bleed structure comprises the air entraining jet being arranged on fan rectifying cover outer wall and the bleed conduit communicated with air entraining jet, and internal heat vibrational power flow in fan cabin 12, and communicates with bleed conduit.Air-flow heating arrangement comprises anti-icing conduit and is positioned at the D shape ring cavity 17 of inlet lip of motor, anti-icing conduit communicates with internal heat structure and D shape ring cavity 17 respectively, the outlet 15 that exhaust structure comprises the outlet 15 being arranged on D shape ring cavity 17 and relief opening 13, the D shape ring cavity being arranged on fan rectifying cover outer wall 2 communicates with relief opening.
Internal heat structure has two kinds of structural types at least, and a kind of is be set in the heat exchange box treating heat exchanger components outside, and another kind is the internal heat passage treating heat exchanger components.In Fig. 1 embodiment, treat that heat exchanger components is engine accessory power rating 6, be provided with heat exchange box 7 in engine accessory power rating 6 outer cover, carry out exchange heat by the metal wall on engine accessory power rating 6 surface with the Cryogenic air flowing through heat exchange box 7.In Fig. 2 embodiment, treat that heat exchanger components is EEC22, internal heat structure is exactly the internal heat passage (not shown) of EEC, carries out exchange heat by the internal heat passage of EEC22 with the Cryogenic air flow through.
Air entraining jet can adopt the structural type of flush type spade air entraining jet, and this structural type has lower frontal resistance, can reduce the impact on nacelle starting performance to the full extent.
D shape ring cavity 17 can be formed by the inwall 1 of the inlet lip of motor and outer wall 2 and the intake duct bulkhead 16 be arranged in fan cabin 12.From Fig. 1 and Fig. 2, the cross section of D shape ring cavity 17 is similar to the letter " D " of retrography, in fact this space is the annular housing of a base closed, only has the insert port of anti-icing conduit can be communicated with fan cabin 12 with internal heat structure respectively with the outlet on intake duct bulkhead 16.The D shape ring cavity of this base closed can realize the concentrated heating being directed to inlet lip position, reaches the anti-icing effect of better intake duct.
As depicted in figs. 1 and 2, the outlet side of anti-icing conduit is positioned at the front portion of D shape ring cavity 17 namely near the entrance location of engine inlets, the curve of direction in the drawings with arrow of air flowing schematically marks, to ensure that high temperature gas flow from internal heat structure is fully to the heating effect of D shape ring cavity.
For Fig. 1 embodiment, colder ambient air outside can enter the first bleed conduit 5 by the first air entraining jet 3, heat exchange box 7 is entered into again through the first bleed conduit 5, high temperature air is converted to from Cryogenic air by the exchange heat in heat exchange box, high temperature air enters into D shape ring cavity 17 by the first anti-icing conduit 4, high temperature air carries out exchange heat at D shape ring cavity 17 and the outer wall of D shape ring cavity, reach anti-icing effect, and the air turned cold enters fan cabin 12 from outlet 15 again, then discharge from first row gas port 13 through passing through fan cabin 12.
The principle of Fig. 2 embodiment and Fig. 1 embodiment is similar, just internal heat structure is distinct, namely colder ambient air outside can enter the second bleed conduit 21 by the second air entraining jet 19, EEC22 is entered into again through the second bleed conduit 21, high temperature air is converted to from Cryogenic air by the internal heat passage at EEC22, high temperature air enters into D shape ring cavity 17 by the second anti-icing conduit 20, high temperature air carries out exchange heat at D shape ring cavity 17 and the outer wall of D shape ring cavity, reach anti-icing effect, and the air turned cold enters fan cabin 12 from outlet 15 again, discharge from second exhaust port 23 through passing through fan cabin 12 again.
In Fig. 1 embodiment, the volume V of heat exchange box 7
7the volume V of engine accessory power rating 6 can be arranged in
6with the volume V of engine accessory power rating 6
61.5 times between, to ensure the heating effect of engine accessory power rating to the Cryogenic air passed through.
In order to reduce the flow losses of air-flow in fan cabin, D shape ring cavity and conduit, the inner circle sectional area S of bleed conduit and anti-icing conduit
tpreferably be not less than the inner circle area S of air entraining jet
i0.3 times, the inner circle area S of relief opening
opreferably be not less than the inner circle area S of air entraining jet
i.
Arrange in the position of air entraining jet and relief opening, in fan cabin, sufficient heat exchange is carried out in order to allow ambient windstream, make air-flow can implement available ventilation and cooling to the space of the fan cabin overwhelming majority, air entraining jet can be arranged on the top of fan fairing, relief opening is arranged on the bottom of described fan fairing.
In another embodiment, plural internal heat structure can be had, accordingly, air entraining jet can comprise the first air entraining jet 3 and the second air entraining jet 19, bleed conduit can comprise the first bleed conduit 5 and the second bleed conduit 21, anti-icing conduit can comprise the first anti-icing conduit 4 and the second anti-icing conduit 20, and relief opening can comprise first row gas port 13 and second exhaust port 23.Outside ambient air can enter into D shape ring cavity respectively by two passages, then discharges from D shape ring cavity.
What these two internal heat structures adopted treat heat exchanger components is respectively in fan cabin 12 engine accessory power rating 6 and EEC22, first air entraining jet 3 is connected to the heat exchange box 7 of engine accessory power rating 6 outside by the first bleed conduit 5, and heat exchange box 7 is connected to the inside of D shape ring cavity 17 by the first anti-icing conduit 4, second air entraining jet 19 is connected to the internal heat passage of EEC22 by the second bleed conduit 21, and internal heat passage is connected to the inside of D shape ring cavity 17 by the second anti-icing conduit 20.
Fig. 3 gives the air circumferential flow schematic diagram in the D shape ring cavity of intake duct deicer embodiment of the present invention.The short-term of the band arrow in Fig. 3 and curve represent the dynamic direction of air-flow, can see the situation of high temperature air at D shape ring cavity Inner eycle of discharge from the first anti-icing conduit 4 and the second anti-icing conduit 20 thus, cooled air is discharged in fan cabin through the outlet 15 of D shape ring cavity again.The circumferential angle that first anti-icing conduit 4 enters the entrance of D shape ring cavity and the outlet 15 of D shape ring cavity is as can see from Figure 3 not less than 90 degree, and the circumferential angle that the second anti-icing conduit 20 enters the entrance of D shape ring cavity and the outlet of D shape ring cavity is not less than 90 degree.
For ensureing that ambient air can enter fan cabin and D shape ring cavity, the static pressure P of the first air entraining jet 3
3should not be less than the static pressure P of first row gas port 13
131.2 times, the static pressure P of the second air entraining jet 19
19should not be less than the static pressure P of second exhaust port 23
231.2 times.
The embodiment of several intake duct deicers of foregoing description can be applied to all kinds ofly to be had in the motor of anti-icing demand, especially be applicable to being applied in civilian turbofan engine, civilian turbofan engine comprises fan and fan cabin 12, fan is made up of fan calotte 11 and fan support plate 14, fan cabin 12 is made up of fan fairing 8, fan cabin fire-wall 9, fancase 10 and intake duct bulkhead 16, and fan is arranged in fancase 10.Engine accessory power rating 6 and EEC22 are all arranged in fan cabin 12.
Can be found out by the embodiment of previously described intake duct deicer of the present invention and civilian turbofan engine, the present invention has the following advantages:
1, after the ambient air of low temperature enters fan cabin, by the exchange heat with engine accessory power rating and/or EEC, the heat of engine accessory power rating and/or EEC is used for the D shape ring cavity of heating air inlet road lip, can intake duct be realized anti-icing, meet the demand that intake duct is anti-icing;
2, the ambient air of low temperature enters fan cabin and engine accessory power rating and/or EEC and carries out exchange heat, thus cooling is formed to engine accessory power rating and/or EEC, reduce the temperature in engine accessory power rating and/or EEC and fan cabin, ensure that the normal work in engine accessory power rating and/or EEC and fan cabin;
3, the engine bleed compared to traditional is anti-icing, because the present invention does not need from engine bleed, thus efficiently avoid and causes engine performance to reduce because of anti-icing bleed;
4, the high temperature leaked out from annex fires lubricating oil steam after the exchange heat in inlet lip D shape chamber, and combustion lubricating oil gas temperature reduces, thus effectively reduces the possibility of firing lubricating oil steam and catching fire in fan cabin.
Finally should be noted that: above embodiment is only in order to illustrate that technological scheme of the present invention is not intended to limit; Although with reference to preferred embodiment to invention has been detailed description, those of ordinary skill in the field are to be understood that: still can modify to the specific embodiment of the present invention or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solution of the present invention, it all should be encompassed in the middle of the technological scheme scope of request of the present invention protection.
Claims (13)
1. an intake duct deicer, it is characterized in that, comprise: bleed structure, internal heat structure, air-flow heating arrangement and exhaust structure, described bleed structure comprises the air entraining jet being arranged on fan rectifying cover outer wall and the bleed conduit communicated with described air entraining jet, described internal heat vibrational power flow is in fan cabin, and communicate with described bleed conduit, described air-flow heating arrangement comprises anti-icing conduit and is positioned at the D shape ring cavity of inlet lip of motor, described anti-icing conduit communicates with described internal heat structure and described D shape ring cavity respectively, described exhaust structure comprises the outlet being arranged on described D shape ring cavity and the relief opening being arranged on described fan rectifying cover outer wall, the outlet of described D shape ring cavity communicates with described relief opening.
2. intake duct deicer according to claim 1, is characterized in that, described D shape ring cavity is formed by the inner and outer wall of the inlet lip of described motor and the intake duct bulkhead be arranged in described fan cabin.
3. intake duct deicer according to claim 1, is characterized in that, described internal heat structure is be set in the heat exchange box treating heat exchanger components outside and/or the internal heat passage treating heat exchanger components.
4. intake duct deicer according to claim 3, it is characterized in that, describedly treat that heat exchanger components is engine accessory power rating, described internal heat structure is the heat exchange box being set in described engine accessory power rating outside, carries out exchange heat by the metal wall on described engine accessory power rating surface with the Cryogenic air flowing through heat exchange box.
5. intake duct deicer according to claim 4, is characterized in that, the volume of described heat exchange box is between the volume of described engine accessory power rating and 1.5 times of the volume of described engine accessory power rating.
6. intake duct deicer according to claim 3, it is characterized in that, describedly treat that heat exchanger components is engine electronic control, described internal heat structure is the internal heat passage of described engine electronic control, carries out exchange heat by the internal heat passage of described engine electronic control with the Cryogenic air flow through.
7. intake duct deicer according to claim 1, is characterized in that, described air entraining jet is flush type spade air entraining jet.
8. intake duct deicer according to claim 1, is characterized in that, the outlet side of described anti-icing conduit is positioned at the front portion of described D shape ring cavity.
9. intake duct deicer according to claim 1, it is characterized in that, the inner circle sectional area of described bleed conduit and anti-icing conduit is not less than 0.3 times of the inner circle area of described air entraining jet, and the inner circle area of described relief opening is not less than the inner circle area of described air entraining jet.
10. intake duct deicer according to claim 1, is characterized in that, described air entraining jet is arranged on the top of described fan fairing, and described relief opening is arranged on the bottom of described fan fairing.
11. intake duct deicers according to claim 10, it is characterized in that, described air entraining jet comprises the first air entraining jet and the second air entraining jet, described relief opening comprises first row gas port and second exhaust port, described bleed conduit comprises the first bleed conduit and the second bleed conduit, described anti-icing conduit comprises the first anti-icing conduit and the second anti-icing conduit, in described fan cabin, treat that heat exchanger components comprises engine accessory power rating and engine electronic control, described first air entraining jet is by the heat exchange box of described first bleed tubes connection to described engine accessory power rating outside, and described heat exchange box is by the inside of described first anti-icing tubes connection to described D shape ring cavity, described second air entraining jet is by the internal heat passage of described second bleed tubes connection to described engine electronic control, and described internal heat passage is by the inside of described second anti-icing tubes connection to described D shape ring cavity.
12. intake duct deicers according to claim 11, it is characterized in that, the circumferential angle that described first anti-icing conduit enters the entrance of described D shape ring cavity and the outlet of described D shape ring cavity is not less than 90 degree, and the circumferential angle that described second anti-icing conduit enters the entrance of described D shape ring cavity and the outlet of described D shape ring cavity is not less than 90 degree.
13. 1 kinds of civilian turbofan engines, comprise fan and fan cabin, it is characterized in that, also comprise the arbitrary described intake duct deicer of claim 1 ~ 12.
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| CN201210496822.4A CN103850800B (en) | 2012-11-29 | 2012-11-29 | Intake duct deicer and civilian turbofan engine |
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| CN105508054B (en) * | 2014-09-23 | 2018-12-07 | 中国航发商用航空发动机有限责任公司 | A kind of engine inlets anti-icing system and aero-engine |
| CN106555676B (en) * | 2015-09-28 | 2018-03-06 | 中国航发商用航空发动机有限责任公司 | Nacelle cools down and air intake duct anti-icing set composite and fanjet |
| CN107100738A (en) * | 2016-12-19 | 2017-08-29 | 浙江科技学院 | A kind of anti-icing equipment of snail fan engine |
| CN112253261B (en) * | 2020-09-11 | 2022-10-28 | 北京动力机械研究所 | Split type heat sink cylindrical rectifier for stable combustion of heater |
| CN113357045B (en) * | 2021-05-23 | 2022-08-30 | 中国航发沈阳发动机研究所 | High stealthy turbofan engine |
| CN114320607A (en) * | 2022-01-06 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Non-rotary double-layer structure anti-icing fairing cap of aircraft engine |
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| GB509622A (en) * | 1938-01-27 | 1939-07-19 | Cecil Louis Cowdrey | Improved means for preventing the formation of ice on the wings of aircraft |
| CN101952171A (en) * | 2007-12-28 | 2011-01-19 | 空中巴士运作简易股份有限公司 | Aircraft propulsion assembly comprising hot air bleed systems |
| CN102190084A (en) * | 2010-03-18 | 2011-09-21 | 空中巴士运作简易股份有限公司 | De-icing system comprising detection means for detecting an air leak in the hot air supply |
| CN102182559A (en) * | 2011-05-04 | 2011-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Anti-icing passage system with functions of precooling and backheating |
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|---|---|
| CN103850800A (en) | 2014-06-11 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |