CN103850800A - Air inlet anticer and civil turbofan engine - Google Patents
Air inlet anticer and civil turbofan engine Download PDFInfo
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- CN103850800A CN103850800A CN201210496822.4A CN201210496822A CN103850800A CN 103850800 A CN103850800 A CN 103850800A CN 201210496822 A CN201210496822 A CN 201210496822A CN 103850800 A CN103850800 A CN 103850800A
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Abstract
The invention relates to an air inlet anticer and a civil turbofan engine, which comprises a gas introduction structure, an internal heat exchange structure, an air-flow heating structure and an exhaust structure, the gas introduction structure comprises a gas introduction port arranged on the outer wall of a fan fairing and a gas introduction conduit, the internal heat exchange structure is arranged in a fan cabin and is communicated to the gas introduction conduit, the air-flow heating structure comprises an anti-icing conduit and a D-shaped ring chamber positioned at an air inlet lip of the engine, the anti-icing conduit is respectively communicated to the internal heat exchange structure and the D-shaped ring chamber, the exhaust structure comprises an outlet arranged on the D-shaped ring chamber and an air exhaust opening arranged on the outer wall of the fan fairing, and the outlet of the D-shaped ring chamber is communicated to the air exhaust opening. According to the invention, the gas introduction structure is used for acquiring the external environment air, environment air at low temperature and a part to be performed heat exchange are subjected to heat exchange by the internal heat exchange structure, the heated air is introduced in the air-flow heating structure for heating to the air inlet lip, so that the anti-icing requirement of the air inlet of the engine can be satisfied.
Description
Technical field
The present invention relates to aeroengine field, relate in particular to a kind of intake duct deicer and civilian turbofan engine.
Background technique
Along with social development, the mankind's living standard improves constantly, civil aviation as one conveniently trip mode obtained vigorous growth.Meanwhile, Security, Economy, the travelling comfort of people to civil aircraft had higher requirement.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 the icing aerodynamic characteristics that can change gas handling system of intake duct increases flow resistance, make inlet flow field skewness, even there is flow distortion, affect the working stability of motor, when serious, may cause stopping working and stop.Intake duct freezes also may cause and melts the launched machine suction of the ice cube coming off, and 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 electric anti-icing and the anti-icing two kinds of modes of gas.The anti-icing mode of electricity is convenient to control the heat of heating, can, according to the operation conditions of motor, regulate the power of electric heater, thereby electric heater operation is relatively little for the impact of engine power, and can not produces the shock effect of air-flow.Adopt electric heating system, can be according to the icing form of different parts, different heating electric weight and the heating frequencies of regulating of the environment that freezes, directionality is better.US20060237582A1 has proposed a kind of double walled intake duct electricity ice prevention structure, and the internal layer of this intake duct has designed a service ports, makes the maintenance of relevant heater and installs very convenient.Because electric heating device need to be introduced power supply from engine accessory power rating, increased motor for electrical load, and it is anti-icing aspect system reliability, to be not so good as gas, thereby in the civilian turbofan engine of main flow, adopts at present few.
The general high temperature air that draws high-pressure compressor that adopts of hot air anti-icing system, is delivered to intake duct leading edge by pressure regulating valve or direct bleed, and the anti-icing parts of needs are heated to play anti-icing effect.The controllability that the anti-icing mode of gas has heat is good, simple in structure, good reliability, and the anti-icing requirement that is content with very little, applies the advantages such as more extensive, and relevant research and patent are also more.As US4738416 has the metallic walls of similar profile by laying one deck and intake duct wall, form a comparatively narrow heat tunnel, in the situation that bleed flow is certain, improve airspeed and strengthened heat transfer effect, improve anti-icing efficiency.US20080179448A1 has proposed the design of a kind of intake duct hot air anti-icing with cellular structure, and this design can realize gas and suppress intake duct noise anti-icing time.
But, hot air anti-icing all must be from engine core power traction gas (being generally high-pressure compressor bleed), this must bring the reduction of engine performance, therefore how in meeting the anti-icing demand of engine inlets, improve to greatest extent the utilization ratio of anti-icing hot gas, reduce engine bleed amount is the key of 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, in 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, inner heat exchange structure, air-flow heating arrangement and exhaust structure, described bleed structure comprises the bleed conduit that is arranged on the air entraining jet of fan rectifying cover outer wall and communicates with described air entraining jet, described inner heat exchange structure is arranged 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 the inlet lip of motor, described anti-icing conduit communicates with described inner heat exchange structure and described D shape ring cavity respectively, described exhaust structure comprises the outlet that is arranged on described D shape ring cavity and the relief opening that is 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 being arranged in described fan cabin.
Further, described inner heat exchange structure is to be set in the heat exchange box for the treatment of heat exchanger components outside and/or the inside heat exchanger channels for the treatment of heat exchanger components.
Further, described in treat that heat exchanger components is engine accessory power rating, described inner heat exchange structure is the heat exchange box that is set in described engine accessory power rating outside, the metal wall by described engine accessory power rating surface carries out exchange heat with the Cryogenic air that flows 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 system device (Engine Electronic Controller, be called for short EEC), the inside heat exchanger channels that described inner heat exchange structure is described engine electronic control system device, carries out exchange heat by inside heat exchanger channels and the Cryogenic air flowing through of described engine electronic control system device.
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 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 row gas 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, the heat exchanger components for the treatment of in described fan cabin comprises engine accessory power rating and engine electronic control system device, described the first air entraining jet is connected to the heat exchange box of described engine accessory power rating outside by described the first bleed conduit, and described heat exchange box is connected to the inside of described D shape ring cavity by described the first anti-icing conduit, described the second air entraining jet is connected to the inside heat exchanger channels of described engine electronic control system device by described the second bleed conduit, and described inner heat exchanger channels is connected to the inside of described D shape ring cavity by described the second anti-icing conduit.
Further, the circumferential angle that described the 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 the 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 by inner heat exchange structure, the heat exchanger components for the treatment of in the ambient air of low temperature and fan cabin is carried out to exchange heat, air after heating is introduced into air-flow heating arrangement again inlet lip is heated, thereby reach the anti-icing object of intake duct, meet the anti-icing demand of engine inlets, and because bleed structure of the present invention need to be from engine bleed, therefore also can not impact the performance of motor, add without anti-icing bleed air line is set on motor, also relatively alleviated the weight of motor, the treat heat exchanger components of the ambient air that simultaneously utilizes low temperature in inner heat exchange structure and fan cabin carries out exchange heat, realized and treated the cooling of heat exchanger components and fan cabin, guaranteed to treat the normal work in 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 being arranged in described fan cabin.D shape ring cavity can be realized the concentrated heating that is directed to inlet lip position, reaches the anti-icing effect of better intake duct.
In another embodiment, described inner heat exchange structure is to be set in the heat exchange box for the treatment of heat exchanger components outside and/or the inside heat exchanger channels for the treatment of heat exchanger components.Inner heat exchange structure is selected outside or inner heat exchange mode according to the difference for the treatment of heat exchanger components, for example, when in the time that heat exchanger components is engine accessory power rating, described inner heat exchange structure is the heat exchange box that is set in described engine accessory power rating outside, carries out exchange heat by metal wall and the Cryogenic air that flows through heat exchange box on described engine accessory power rating surface; When in the time that heat exchanger components is EEC, the inside heat exchanger channels that described inner heat exchange structure is described EEC, carries out exchange heat by inside heat exchanger channels and the Cryogenic air flowing through of described EEC.
For treating that heat exchanger components is engine accessory power rating, inner heat exchange structure is heat exchange box, preferably the volume of heat exchange box 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 of passing 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 to the full extent the impact on nacelle starting performance.
In another embodiment, the outlet side of described anti-icing conduit is positioned at the front portion of described D shape ring cavity, i.e. the entrance location of close engine inlets, to ensure the high temperature gas flow heating effect to D shape ring cavity fully from inner heat exchange structure.
In another embodiment, the inner circle sectional area of described bleed conduit and anti-icing conduit is not less than 0.3 times of 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 porting like this, can allow ambient windstream in fan cabin, carry out sufficient heat exchange, makes air-flow to 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 row gas 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, the heat exchanger components for the treatment of in described fan cabin comprises engine accessory power rating and EEC, described the first air entraining jet is connected to the heat exchange box of described engine accessory power rating outside by described the first bleed conduit, and described heat exchange box is connected to the inside of described D shape ring cavity by described the first anti-icing conduit, described the second air entraining jet is connected to the inside heat exchanger channels of described EEC by described the second bleed conduit, and described inner heat exchanger channels is connected to the inside of described D shape ring cavity by described the second anti-icing conduit.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 carry out hot air anti-icing, can realize better anti-icing effect, also engine accessory power rating and EEC all realized to cooling action simultaneously, guarantee the normal work of engine accessory power rating and EEC.
In another embodiment, the circumferential angle that described the 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 the 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 the high temperature gas flow heating effect to D shape ring cavity fully from inner heat exchange structure.
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 having adopted aforesaid intake duct deicer, not only can reach the anti-icing object of intake duct, and due to without from engine bleed, therefore also can not impact the performance of motor, add without anti-icing bleed air line is set on motor, also relatively alleviated the weight of motor; The treat heat exchanger components of the ambient air that simultaneously utilizes low temperature in inner heat exchange structure and fan cabin carries out exchange heat, realized and treated the cooling of heat exchanger components and fan cabin, guaranteed to treat the normal work in heat exchanger components and fan cabin.
Brief description of the drawings
Accompanying drawing described herein is used to provide a further understanding of the present invention, forms the application's a part, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is an embodiment's of intake duct deicer of the present invention structural representation.
Fig. 2 is another embodiment's of intake duct deicer of the present invention structural representation.
Fig. 3 is the air circumferential flow schematic diagram in intake duct deicer embodiment's of the present invention D shape ring cavity.
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, inner heat exchange structure, air-flow heating arrangement and exhaust structure four part-structure compositions, bleed structure is responsible for introducing outside ambient air, inner heat exchange structure is responsible for heat that the heating component in fan cabin is produced and the Cryogenic air of introducing exchanges, make ambient air be heated into high temperature air, and being introduced in air-flow heating arrangement, high temperature air improves the temperature of inlet location, suppress the formation of ice sheet, and the air turning cold after circulation in air-flow heating arrangement is discharged by exhaust structure again.
Fig. 1 and Fig. 2 are respectively the embodiment of two kinds of intake duct deicers, in these two embodiments, bleed structure comprises the bleed conduit that is arranged on the air entraining jet of fan rectifying cover outer wall and communicates with air entraining jet, and inner heat exchange structure is arranged 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 the inlet lip of motor, anti-icing conduit communicates with inner heat exchange structure and D shape ring cavity 17 respectively, exhaust structure comprises the outlet 15 that is arranged on D shape ring cavity 17 and the relief opening 13 that is arranged on fan rectifying cover outer wall 2, and the outlet 15 of D shape ring cavity communicates with relief opening.
Inner heat exchange structure has two kinds of structural types at least, and a kind of is to be set in the heat exchange box for the treatment of heat exchanger components outside, and another kind is the inside heat exchanger channels for the treatment of 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 metal wall and the Cryogenic air that flows through heat exchange box 7 on engine accessory power rating 6 surfaces.In Fig. 2 embodiment, treat that heat exchanger components is EEC22, inner heat exchange structure is exactly the inside heat exchanger channels (not shown) of EEC, carries out exchange heat by inside heat exchanger channels and the Cryogenic air flowing through of EEC22.
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 to the full extent the impact on nacelle starting performance.
D shape ring cavity 17 can be formed by the inwall of the inlet lip of motor 1 and outer wall 2 and the intake duct bulkhead 16 being 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 base closed, only has the outlet on insert port and the intake duct bulkhead 16 of anti-icing conduit to be communicated with inner heat exchange structure and fan cabin 12 respectively.The D shape ring cavity of this base closed can be realized the concentrated heating that is 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 entrance location of the close engine inlets in front portion of D shape ring cavity 17, the direction of Air Flow schematically marks with the curve of arrow in the drawings, to ensure the high temperature gas flow heating effect to D shape ring cavity fully from inner heat exchange structure.
For Fig. 1 embodiment, colder ambient air outside can enter the first bleed conduit 5 by the first air entraining jet 3, enter into heat exchange box 7 through the first bleed conduit 5 again, be converted to high temperature air by the exchange heat in heat exchange box from Cryogenic air, 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 turning cold enters fan cabin 12 from exporting 15 again, then discharges from first row gas port 13 through passing through fan cabin 12.
Fig. 2 embodiment and Fig. 1 embodiment's principle is similar, be that inner heat exchange structure is distinct, colder ambient air outside can enter the second bleed conduit 21 by the second air entraining jet 19, enter into EEC22 through the second bleed conduit 21 again, be converted to high temperature air by the inside heat exchanger channels at EEC22 from Cryogenic air, 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 turning cold enters fan cabin 12 from exporting 15 again, discharge from second row gas port 23 through passing through fan cabin 12 again.
In Fig. 1 embodiment, the volume V of heat exchange box 7
7can be arranged in the volume V of engine accessory power rating 6
6volume V with engine accessory power rating 6
61.5 times between, to ensure the heating effect of engine accessory power rating to the Cryogenic air of passing 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 order to allow ambient windstream carry out sufficient heat exchange in fan cabin, make air-flow to implement available ventilation and cooling to the space of the fan cabin overwhelming majority, the top that air entraining jet can be arranged on to fan fairing, relief opening is arranged on the bottom of described fan fairing.
In another embodiment, can there is plural inner heat exchange structure, 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 row gas port 23.Outside ambient air can enter into D shape ring cavity by two passages respectively, then discharges from D shape ring cavity.
What these two inner heat exchange structures adopted treats that heat exchanger components is respectively engine accessory power rating 6 and the EEC22 in fan cabin 12, the first air entraining jet 3 is connected to the heat exchange box 7 of engine accessory power rating 6 outsides 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, the second air entraining jet 19 is connected to the inside heat exchanger channels of EEC22 by the second bleed conduit 21, and inner heat exchanger channels is connected to the inside of D shape ring cavity 17 by the second anti-icing conduit 20.
Fig. 3 has provided the air circumferential flow schematic diagram in intake duct deicer embodiment's of the present invention D shape ring cavity.The short-term with arrow and curve in Fig. 3 represent the direction that air-flow is moving, can see thus from the first anti-icing conduit 4 and the second anti-icing conduit 20 situation that the high temperature air of discharging circulates in D shape ring cavity, cooled air is discharged in fan cabin through the outlet 15 of D shape ring cavity again.The circumferential angle that the 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 row gas port 23
231.2 times.
The embodiment of several intake duct deicers of foregoing description can be applied in all kinds of motors that have 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.
Embodiment by previously described intake duct deicer of the present invention and civilian turbofan engine can find out, the present invention has the following advantages:
1, the ambient air of low temperature enters behind fan cabin, by with the exchange heat of engine accessory power rating and/or EEC, D shape ring cavity by the heat of engine accessory power rating and/or EEC for heating air inlet road lip, can realize intake duct anti-icing, meets the anti-icing demand of intake duct;
2, the ambient air of low temperature enters fan cabin and engine accessory power rating and/or EEC and carries out exchange heat, thereby form cooling to engine accessory power rating and/or EEC, reduce the temperature in engine accessory power rating and/or EEC and fan cabin, ensured the normal work in engine accessory power rating and/or EEC and fan cabin;
3, anti-icing than traditional engine bleed, because the present invention need to be from engine bleed, thereby effectively avoid reducing because anti-icing bleed causes engine performance;
4, the high temperature combustion lubricating oil steam leaking out from annex is after the exchange heat in inlet lip D shape chamber, and combustion lubricating oil gas temperature reduces, thereby effectively reduces the possibility that combustion lubricating oil steam catches 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 the present invention is had been described in detail with reference to preferred embodiment, those of ordinary skill in the field are to be understood that: still can modify or part technical characteristics is equal to replacement the specific embodiment of the present invention; 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 protection of the present invention.
Claims (13)
1. an intake duct deicer, it is characterized in that, comprise: bleed structure, inner heat exchange structure, air-flow heating arrangement and exhaust structure, described bleed structure comprises the bleed conduit that is arranged on the air entraining jet of fan rectifying cover outer wall and communicates with described air entraining jet, described inner heat exchange structure is arranged 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 the inlet lip of motor, described anti-icing conduit communicates with described inner heat exchange structure and described D shape ring cavity respectively, described exhaust structure comprises the outlet that is arranged on described D shape ring cavity and the relief opening that is 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 being arranged in described fan cabin.
3. intake duct deicer according to claim 1, is characterized in that, described inner heat exchange structure is to be set in the heat exchange box for the treatment of heat exchanger components outside and/or the inside heat exchanger channels for the treatment of 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 inner heat exchange structure is the heat exchange box that is set in described engine accessory power rating outside, carries out exchange heat by metal wall and the Cryogenic air that flows through heat exchange box on described engine accessory power rating surface.
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 system device, the inside heat exchanger channels that described inner heat exchange structure is described engine electronic control system device, carries out exchange heat by inside heat exchanger channels and the Cryogenic air flowing through of described engine electronic control system device.
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 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 row gas 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, the heat exchanger components for the treatment of in described fan cabin comprises engine accessory power rating and engine electronic control system device, described the first air entraining jet is connected to the heat exchange box of described engine accessory power rating outside by described the first bleed conduit, and described heat exchange box is connected to the inside of described D shape ring cavity by described the first anti-icing conduit, described the second air entraining jet is connected to the inside heat exchanger channels of described engine electronic control system device by described the second bleed conduit, and described inner heat exchanger channels is connected to the inside of described D shape ring cavity by described the second anti-icing conduit.
12. intake duct deicers according to claim 11, it is characterized in that, the circumferential angle that described the 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 the 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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| CN105508054A (en) * | 2014-09-23 | 2016-04-20 | 中航商用航空发动机有限责任公司 | Engine gas inlet pipe anti-icing system and aircraft engine |
| CN106555676A (en) * | 2015-09-28 | 2017-04-05 | 中航商用航空发动机有限责任公司 | Nacelle is cooled down and the anti-icing set composite of air intake duct 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 |
| CN112253261A (en) * | 2020-09-11 | 2021-01-22 | 北京动力机械研究所 | Split type heat sink cylindrical rectifier for stable combustion of heater |
| CN113357045A (en) * | 2021-05-23 | 2021-09-07 | 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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|---|---|---|---|---|
| CN105508054A (en) * | 2014-09-23 | 2016-04-20 | 中航商用航空发动机有限责任公司 | Engine gas inlet pipe anti-icing system and aircraft engine |
| 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 |
| CN106555676A (en) * | 2015-09-28 | 2017-04-05 | 中航商用航空发动机有限责任公司 | Nacelle is cooled down and the anti-icing set composite of air intake duct and fanjet |
| 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 |
| CN112253261A (en) * | 2020-09-11 | 2021-01-22 | 北京动力机械研究所 | Split type heat sink cylindrical rectifier for stable combustion of heater |
| 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 |
| CN113357045A (en) * | 2021-05-23 | 2021-09-07 | 中国航发沈阳发动机研究所 | High stealthy turbofan engine |
| 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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