CN104948286A - Cooling method and device for engine core module - Google Patents
Cooling method and device for engine core module Download PDFInfo
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- CN104948286A CN104948286A CN201410118225.7A CN201410118225A CN104948286A CN 104948286 A CN104948286 A CN 104948286A CN 201410118225 A CN201410118225 A CN 201410118225A CN 104948286 A CN104948286 A CN 104948286A
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Abstract
The invention provides a cooling method and device for an engine core module. According to the method, cooling airflow in a fan cabin is reutilized and introduced into the core module so as to cool the core module. In the ground test state, ambient airflow enters the fan cabin for ventilation cooling through an exhaust port of the fan cabin in a free convection mode and is discharged through an air inlet of the fan cabin finally. In other flying states, ambient airflow enters through the air inlet of the fan cabin under the ram action, is divided into a left stream and a right stream for ventilation cooling of the fan cabin, and then is introduced into the core module through an air guiding pipe under the differential pressure of the fan cabin and the core module to conduct ventilation cooling on the core module, and meanwhile, the ambient airflow can conduct directional concentrated cooling on the local high-temperature region in the cabin under the guiding of the air guiding pipe. In this way, ventilation cooling of the core module is achieved, the air entraining content of an external duct is reduced, entraining loss of the external duct is reduced, and reutilization of ventilation cooling airflow of the fan cabin is achieved.
Description
Technical field
The present invention relates to aircraft engines, be specifically related to cooling means and the cooling unit in airplane engine core cabin.
Background technique
Engine core machine, casing and various engine accessory power rating have been contained in engine core cabin.Amount of heat is transmitted by casing to core cabin during engine operation, if heat can not leave in time or assemble rapidly, then can cause the pipeline in cabin and annex cisco unity malfunction, even initiation fire, core cabin ventilation cooling system can cool on the one hand and be loaded in all kinds of annex on engine crankcase and casing itself, the circulation of cabin inner air can be ensured on the other hand, thus prevent the gathering of inflammable gas in cabin, eliminate disaster hidden-trouble.Therefore, core cabin ventilating and cooling technology normally works to guarantee external engine piping and annex, reduces fire possibility occurrence significant.
Current civilian turbofan engine core cabin ventilating and cooling bleed form mainly contains the bleed of bleed hole and wind scoop bleed two kinds.Wherein bleed hole bleed flow is little, external culvert effect of aerodynamic performance is also less, wind scoop bleed efficiency is high, in identical bleed area situation, wind scoop amount of air entrainment is about about 2.4 times of bleed hole, but it is comparatively large externally to contain effect of aerodynamic performance, comprehensive assessment is therefore needed to contain aeroperformance and cooling effect outward to determine bleed form.
But, for civilian turbofan engine, the cooling blast of current core cabin ventilating and cooling technology is all from outer culvert, it is less that effect of aerodynamic performance is externally contained in simple employing bleed hole bleed, but the temperature requirement of each pipeline fittings under being difficult to meet high temperature plateau takeoff condition, only adopt wind scoop bleed can meet the temperature requirement of high temperature plateau takeoff condition, but it is larger externally to contain aeroperformance, and because ambient temperature is very low under cruising condition, do not need very large amount of air entrainment can meet the temperature requirement of annex in cabin yet, this aerodynamic loss just causing the lower outside culvert of cruising condition unnecessary.
Therefore, under different flight status, motor reduces outer aerodynamic loss of containing and becomes one of emphasis of current core cabin ventilating and cooling concern under the prerequisite of requirement that can meet ventilating and cooling.
Summary of the invention
Technical problem to be solved
When carrying out ventilating and cooling to civilian turbofan engine core cabin, in order to reduce the bleed load of outer culvert, the present invention devises a kind of cooling blast in fan cabin that utilizes and carries out the method for ventilating and cooling to core cabin.By this design, cooling blast (having completed the air-flow to fan cabin ventilating and cooling) in engine blower cabin is introduced core cabin by air entraining pipe and ventilating and cooling is carried out to core cabin, the introduction volume of outer culvert air-flow can be reduced on the one hand, reduce bleed loss, can realize on the other hand carrying out orientation cooling to district of core Cang Nei localized hyperthermia, reach the temperature requirement in cabin.
The technological scheme adopted
According to an aspect of the present invention, provide a kind of cooling means of airplane engine core cabin, described airplane engine comprises core cabin and fan cabin, and described fan cabin is provided with air entraining jet and relief opening, it is characterized in that, described method comprises:
Relief opening controlling mechanism is set in the exhaust ports in described fan cabin, and described relief opening controlling mechanism can be switched between primary importance and the second place;
Arrange air entraining device, the air-flow from described fan cabin can be guided to described core cabin to cool described core cabin by described air entraining device; And
In described primary importance, make described relief opening controlling mechanism close the relief opening in described fan cabin, thus make the air-flow flowed out from described fan cabin enter described core cabin via described air entraining device; In the described second place, described relief opening controlling mechanism is made not block the relief opening in described fan cabin.
In said method, preferably, described relief opening controlling mechanism is spoiler, during aircraft flight, described spoiler is placed on described primary importance, concentrates cooling to carry out orientation by described air entraining device to the district of localized hyperthermia in described core cabin; And at aircraft floor vehicle stop state, described spoiler is placed on the described second place, ensure that the relief opening of ambient windstream through described fan cabin enters described fan cabin and carry out ventilating and cooling to described fan cabin.
In said method, preferably, described relief opening controlling mechanism is louvre type valve, during aircraft flight, described louvre type valve is placed on described primary importance, concentrates cooling to carry out orientation by described air entraining device to the district of localized hyperthermia in described core cabin; And at aircraft floor vehicle stop state, described louvre type valve is placed on the described second place, ensure that the relief opening of ambient windstream through described fan cabin enters described fan cabin and carry out ventilating and cooling to described fan cabin.
In said method, preferably, the entrance of described air entraining device is communicated with described fan cabin fluid, and the outlet of described air entraining device is communicated with described core cabin fluid.
In said method, preferably, described air entraining device be provided with multiple outlet, multiple high-temperature zones in described core cabin are led in described multiple outlet respectively, with respectively to described multiple high-temperature zone carry out orientation cooling.
According to a further aspect in the invention, additionally provide a kind of cooling unit of airplane engine core cabin, described airplane engine comprises core cabin and fan cabin, and described fan cabin is provided with air entraining jet and relief opening, it is characterized in that, described cooling unit comprises:
Be arranged on the relief opening controlling mechanism of the exhaust ports in described fan cabin, described relief opening controlling mechanism can switch between primary importance and the second place;
Air entraining device, the air-flow from described fan cabin can be guided to described core cabin to cool described core cabin by described air entraining device; And
In described primary importance, described relief opening controlling mechanism cuts out the relief opening in described fan cabin, the air-flow flowed out is entered enter described core cabin via described air entraining device from described fan cabin; In the described second place, described relief opening controlling mechanism does not block the relief opening in described fan cabin.
In above-mentioned cooling unit, preferably, described relief opening controlling mechanism is spoiler, and described spoiler is rotatably installed on the exhaust ports in described fan cabin via roll pin, thus can switch at closedown described relief opening and not blocking between described relief opening.
In above-mentioned cooling unit, preferably, described relief opening controlling mechanism is louvre type valve, and described louvre type valve is installed on the exhaust ports in described fan cabin, thus can switch at closedown described relief opening and not blocking between described relief opening.
In above-mentioned cooling unit, preferably, described air entraining device is made up of air entraining pipe, bleed ring and diversion division, and between described air entraining pipe, bleed ring and diversion division, mutual fluid is communicated with, and described air entraining pipe is communicated with described fan cabin fluid, described diversion division leads to the high-temperature zone in described core cabin.
Preferably, described diversion division leads to one-tenth annex in described core cabin to cool it.
Preferably, arrange multiple pod apertures or many honeycomb ducts along described bleed ring circumference, described multiple pod apertures or many honeycomb ducts carry out orientation to high-temperature zone, many places respectively and concentrate cooling.
Preferably, the exhaust in the effective bleed area≤described core cabin of the effective bleed area≤described air entraining pipe of the described air entraining jet in described fan cabin is sewed with effect leaving area, and the useful area sum of described honeycomb duct is not less than effective bleed area of described air entraining pipe, and the caliber of described honeycomb duct is not more than the caliber of described bleed ring.
Preferably, described honeycomb duct number is N, and 4≤N≤8.
In above-mentioned cooling unit, preferably, described air entraining device is provided with air entraining pipe, and described air entraining pipe is communicated with described fan cabin fluid, and the relief opening cross section in the import cross section of described air entraining pipe and described fan cabin forms angle α, and 30 °≤α≤120 °.
In above-mentioned cooling unit, preferably, described air entraining device is provided with air entraining pipe, and described air entraining pipe is communicated with described fan cabin fluid, and the relief opening cross section in the import cross section of described air entraining pipe and described fan cabin forms angle α, 90 °≤α≤120 °.
The present invention, by carrying out secondary utilization to the cooling blast in fan cabin, is introduced into core cabin, can realize the cooling in core cabin.Under ground run state, ambient windstream enters fan cabin by natural convection from fan cabin relief opening and carries out ventilating and cooling, finally discharges from fan cabin suction port.In other regime of flight, ambient windstream is entered from fan cabin suction port by punching press effect, two strands, left and right is divided into carry out ventilating and cooling to fan cabin, then under fan cabin and core cabin differential pressure action, core cabin is introduced by air entraining pipe, ventilating and cooling is carried out to core cabin, orientation can be carried out to district of Cang Nei localized hyperthermia simultaneously under honeycomb duct guides and concentrate cooling.Thus realize the ventilating and cooling in core cabin, reduce the outer amount of air entrainment containing runner, reduce the outer bleed loss contained, the secondary simultaneously realizing fan cabin ventilating and cooling air-flow utilizes.
Accompanying drawing explanation
Fig. 1 is the structural representation of the civilian turbofan engine be provided with according to cooling unit of the present invention, and it utilizes fan cabin cooling blast to core cabin ventilating and cooling, and in figure, arrow represents the flow direction of air-flow;
The structural representation of the air entraining device in Fig. 2 Fig. 1;
Fig. 3 is the circumferential structural representation of the air entraining device in core cabin in Fig. 1;
Fig. 4 is the structural representation of another embodiment of air entraining device; And
Fig. 5 is the relief opening controlling mechanism structural representation in air entraining device and fan cabin.
Description of reference numerals:
0. fan cone; 1. inlet lip outer wall; 2. inlet lip inwall; 3. fan cabin air entraining jet; 4. fan cabin; 5. fan fairing; 6. fan cabin fire-wall; 7. outside, contain outer wall; 8. by-pass air duct; 9. outside, contain inwall; 10. core hood; Outlet is contained outside 11.; 12. one-tenth annexes; 13. core cabins; 14. honeycomb ducts; 15. bleed rings; 16. fan support plates; 17. air entraining pipes; 18. roll pins; 19. fan cabin relief openings; 20. spoilers; 21. fans.
Embodiment
Below with reference to accompanying drawing, preferred embodiment of the present invention is described in detail, so that clearer understanding objects, features and advantages of the present invention.It should be understood that embodiment shown in the drawings is not limitation of the scope of the invention, and the connotation just in order to technical solution of the present invention is described.In accompanying drawing, the same or analogous reference character of identical element indicates.
Fig. 1 illustrates in airplane engine, utilizes fan cabin cooling blast core cabin to be carried out to the structural representation of ventilating and cooling.As shown in Figure 1, aircraft machine motor generally comprises core cabin and fan cabin, is provided with various one-tenth annex 12 in core cabin.At aircraft run duration, especially during flying, need to cool fan cabin and core cabin, thus ensure fan cabin and core cabin and various components and parts wherein, such as become annex to cool, to ensure that it normally works.
In general, in existing aircraft, fan cabin is provided with air entraining jet 3 and relief opening 19, for cooling fan cabin.Particularly, during aircraft, ambient air flows into due to the air entraining jet 3 of punching press effect from fan cabin, carry out ventilating and cooling, and in ground parking state, ambient windstream enters fan cabin through fan cabin relief opening 19 and carries out ventilating and cooling to it to fan cabin.
For the cooling in core cabin, mainly introduce environmental gas by wind scoop (not shown) and bleed hole (not shown) at present, core cabin is cooled.But this type of cooling also exists the problems such as the aerodynamic loss such as causing outer culvert unnecessary.
Claimant passes through the discovery that studies for a long period of time, during the flight of aircraft, after environmental gas completes the cooling to fan cabin, though gas flow temperature raises to some extent, but still lower than temperature in core cabin, therefore, the present invention imagines a kind of method again utilizing this part gas to come coolant core cabin.
The method comprises: arrange relief opening controlling mechanism in the exhaust ports in fan cabin, and described relief opening controlling mechanism can be switched between primary importance and the second place; Arrange air entraining device, the air-flow from described fan cabin can be guided to described core cabin to cool described core cabin by described air entraining device; And in described primary importance, make described relief opening controlling mechanism close the relief opening in described fan cabin, thus the air-flow flowed out from described fan cabin is made to enter described core cabin via described air entraining device; In the described second place, described relief opening controlling mechanism is made not block the relief opening in described fan cabin.
Preferably, during aircraft flight, described relief opening controlling mechanism is placed on described primary importance, concentrates cooling to carry out orientation by described air entraining device to the district of localized hyperthermia in described core cabin.At aircraft floor vehicle stop state, described relief opening controlling mechanism is placed on the described second place, ensures that the relief opening of ambient windstream through described fan cabin enters described fan cabin and carry out ventilating and cooling to described fan cabin.
Preferably, relief opening controlling mechanism is spoiler, and this spoiler can rotate within the scope of several angle, thus can close or open the relief opening in (not blocking) fan cabin.
Preferably, the entrance of described air entraining device is communicated with described fan cabin fluid, and the outlet of described air entraining device is communicated with described core cabin fluid.
Air entraining device can be provided with multiple outlet, and multiple high-temperature zones in described core cabin are led in described multiple outlet respectively, to carry out orientation cooling to described multiple high-temperature zone respectively, thus to coolings such as the one-tenth annexes at these region places.Air entraining device can be arranged to different structures as required, hereafter will describe in further detail.
Fig. 1 illustrates according to above-mentioned principle, utilizes the cooled gas in fan cabin core cabin to be carried out to the structural representation of an embody rule embodiment of the method for ventilating and cooling.As shown in Figure 1, the cooling unit of the cooled gas in fan cabin to airplane engine core cabin is utilized mainly to comprise spoiler 20 and the air entraining device 100 at relief opening 19 place being arranged on fan cabin 4.See Fig. 5, spoiler 20 is rotatably installed on relief opening 19 place in fan cabin 4 via roll pin 18, thus can switch at closedown described relief opening 19 and not blocking between described relief opening 19.
Spoiler 20 is plate-like piece, and its size is arranged to the relief opening 19 can closing fan cabin.But should be understood that spoiler 20 also can be made up of other relief opening controlling mechanism can changed between the primary importance of closing relief opening 19 and the second place of not blocking relief opening 19.In described primary importance, the relief opening in described fan cabin closed by described spoiler, the air-flow flowed out entered enter described core cabin via described air entraining device from described fan cabin.In the described second place, described spoiler does not block the relief opening in described fan cabin, thus ambient air can enter fan cabin by relief opening, to cool fan cabin.
An optional alternative structure of spoiler is the valve (not shown) of louvre type.This louvre type valve is arranged on relief opening 19 place in fan cabin.During aircraft, this louvre type valve is in closed condition, thus closes the relief opening 19 in fan cabin, the air-flow flowed out is entered enter core cabin via air entraining device 100 from described fan cabin.And in ground parking state, this louvre type valve is in open mode, ambient windstream enters fan cabin by natural convection through fan cabin relief opening 19 and carries out ventilating and cooling.
Preferably, spoiler 20 can according to the instruction from engine control system, rotated by driven by motor choked flow door pivot, thus can to switch between primary importance and the second place at spoiler, namely switch at the described relief opening 19 of closedown and not blocking between described relief opening 19.In its alternate embodiment, louvre type valve also can switch opening according to the instruction from engine control system between closed condition, namely switches at the described relief opening 19 of closedown and opening between described relief opening 19.
Air entraining device 100 is made up of bleed ring 15, air entraining pipe 17 and honeycomb duct 14, wherein between air entraining pipe 17, bleed ring 15 and honeycomb duct 14, mutual fluid is communicated with, and described air entraining pipe 17 is communicated with described fan cabin 4 fluid, described honeycomb duct 14 leads to the high-temperature zone in described core cabin 13, with to the one-tenth annex in described core cabin 13 to cool it.
Bleed ring 15 is fixedly mounted on the inwall mounting edge of core cabin by pipeline clamp and support, and its pipeline clamp and support can carry out different designs according to actual needs.Bleed ring can be made into difformity as required.Bleed ring shown in Fig. 2 is annulus, but those of ordinary skill in the art will understand, and bleed ring 15 also can be Q-RING, polygonal ring, vesica piscis etc.Bleed ring 15 is connected to form by pipe joint so that install in core cabin by multiple pipeline section.
Bleed ring 15 is provided with multiple air outlets (not shown), and each air outlet is communicated with honeycomb duct 14 fluid.The quantity of air outlet correspondingly can be arranged according to the quantity of honeycomb duct 14.
Many honeycomb ducts 14 are arranged along described bleed ring 14 circumference, and described many honeycomb ducts carry out orientation to high-temperature zone, many places respectively and concentrate cooling.The quantity of honeycomb duct can be arranged as required, but, for ensureing ventilating and cooling effect in core cabin, consider that honeycomb duct contains the choked flow effect of cooling blast out of my cabin to core simultaneously, honeycomb duct number N is preferably 4≤N≤8, and circumferential distribution mode can be determined according to temperature requirements in cabin.
The length of honeycomb duct 14 is determined according to becoming the temperature requirement in the structural configuration of annex, cabin in core cabin length, cabin, needs the directed region of cooling of concentrating directly honeycomb duct can be reached this region in the scope that space allows.
The import of air entraining pipe 17 is communicated with fan cabin fluid, and outlet is communicated with bleed ring 15 fluid.The concrete shape of air entraining pipe can carry out respective design according to actual conditions.But, for ensureing not affect the ventilating and cooling effect under the different conditions of fan cabin, more easily realize the switching of air flow path, air entraining pipe import axial position is preferably positioned at fan cabin exhaust ports, air entraining pipe import cross section and relief opening cross section, fan cabin form angle α, 30 °≤α≤120 °, but during 90 °≤α≤120 °, effect is better, ensures that air-flow enters core cabin smoothly.
In addition, for ensureing that air-flow does not occur damming when entering core cabin, core cabin can be discharged smoothly simultaneously, being positioned at air entraining jet effective bleed area S in fan cabin
entrancethe effective bleed area S of≤air entraining pipe≤core cabin exhaust is sewed with effect leaving area S
outlet, honeycomb duct useful area sum S
pipeeffective bleed area S of air entraining pipe should be not less than, honeycomb duct caliber D
pipebe not more than bleed endless tube footpath D
ring.
Below an embodiment according to air entraining device 100 of the present invention is described by reference to the accompanying drawings.But those of ordinary skill in the art should be understood that air entraining device 100 also can for can guide to described core cabin with other air entraining device cooled described core cabin by the air-flow from described fan cabin after reading this description.
As an alternate embodiment, Fig. 4 illustrates another air entraining device.This air entraining device does not arrange honeycomb duct, but directly on bleed ring, offers pod apertures, for the number needing the position of special cooling suitably can strengthen water conservancy diversion aperture and pod apertures.
The present invention relates to a kind of fan cabin cooling blast that utilizes and carry out method and the cooling unit of ventilating and cooling to core cabin, this cooling means is considered to carry out secondary utilization to the cooling blast in fan cabin, is introduced into core cabin and continues cooling.Under ground run state, ambient windstream enters fan cabin by natural convection from fan cabin relief opening and carries out ventilating and cooling, finally discharge from fan cabin suction port, now relief opening controlling mechanism is placed on the ingress of air entraining device, ensure that air-flow enters fan cabin smoothly.In other regime of flight, relief opening controlling mechanism is placed on fan cabin relief opening, ambient windstream is entered from fan cabin suction port by punching press effect, two strands, left and right is divided into carry out ventilating and cooling to fan cabin, then under fan cabin and core cabin differential pressure action, core cabin is introduced by air entraining pipe, ventilating and cooling is carried out to core cabin, orientation can be carried out to district of Cang Nei localized hyperthermia simultaneously under honeycomb duct guides and concentrate cooling.
The beneficial effect of the invention:
(1) air-flow completed the cooling of fan cabin is carried out ventilating and cooling by air entraining pipe introducing core cabin to core cabin, reduce the outer amount of air entrainment containing runner, the bleed contained outside reducing loss, the secondary simultaneously realizing fan cabin ventilating and cooling air-flow utilizes.
(2) the concentrated cooling of orientation can be carried out in the region high to temperature requirement in cabin, ensure that in core cabin, pipeline and annex normally work.
(3) the ventilating and cooling effect in fan cabin under ground parking state can be ensured
Below described preferred embodiment of the present invention in detail, but it will be appreciated that, after having read above-mentioned instruction content of the present invention, those skilled in the art can make various changes or modifications the present invention.These equivalent form of values fall within the application's appended claims limited range equally.
Claims (15)
1. the cooling means in airplane engine core cabin, described airplane engine comprises core cabin and fan cabin, and described fan cabin is provided with air entraining jet and relief opening, it is characterized in that, described method comprises:
Relief opening controlling mechanism is set in the exhaust ports in described fan cabin, and described relief opening controlling mechanism can be switched between primary importance and the second place;
Arrange air entraining device, the air-flow from described fan cabin can be guided to described core cabin to cool described core cabin by described air entraining device; And
In described primary importance, make described relief opening controlling mechanism close the relief opening in described fan cabin, thus make the air-flow flowed out from described fan cabin enter described core cabin via described air entraining device; In the described second place, described relief opening controlling mechanism is made not block the relief opening in described fan cabin.
2. method according to claim 1, it is characterized in that, described relief opening controlling mechanism is spoiler, during aircraft flight, described spoiler is placed on described primary importance, concentrates cooling to carry out orientation by described air entraining device to the district of localized hyperthermia in described core cabin; And
At aircraft floor vehicle stop state, described spoiler is placed on the described second place, ensures that the relief opening of ambient windstream through described fan cabin enters described fan cabin and carry out ventilating and cooling to described fan cabin.
3. method according to claim 1, it is characterized in that, described relief opening controlling mechanism is louvre type valve, during aircraft flight, described louvre type valve is placed described primary importance, concentrates cooling to carry out orientation by described air entraining device to the district of localized hyperthermia in described core cabin; And
At aircraft floor vehicle stop state, described louvre type valve is placed on the described second place, ensures that the relief opening of ambient windstream through described fan cabin enters described fan cabin and carry out ventilating and cooling to described fan cabin.
4. method according to claim 1, is characterized in that, is communicated with by the entrance of described air entraining device with described fan cabin fluid, and the outlet of described air entraining device is communicated with described core cabin fluid.
5. method according to claim 1, is characterized in that, described air entraining device be provided with multiple outlet, multiple high-temperature zones in described core cabin are led in described multiple outlet respectively, with respectively to described multiple high-temperature zone carry out orientation cooling.
6. the cooling unit in airplane engine core cabin, described airplane engine comprises core cabin and fan cabin, and described fan cabin is provided with air entraining jet and relief opening, it is characterized in that, described cooling unit comprises:
Be arranged on the relief opening controlling mechanism of the exhaust ports in described fan cabin, described relief opening controlling mechanism can switch between primary importance and the second place;
Air entraining device, the air-flow from described fan cabin can be guided to described core cabin to cool described core cabin by described air entraining device; And
In described primary importance, described relief opening controlling mechanism cuts out the relief opening in described fan cabin, the air-flow flowed out is entered enter described core cabin via described air entraining device from described fan cabin; In the described second place, described relief opening controlling mechanism does not block the relief opening in described fan cabin.
7. device according to claim 6, it is characterized in that, described relief opening controlling mechanism is spoiler, and described spoiler is rotatably installed on the exhaust ports in described fan cabin via roll pin, thus can switch at closedown described relief opening and not blocking between described relief opening.
8. device according to claim 6, it is characterized in that, described relief opening controlling mechanism is louvre type valve, and described louvre type valve is installed on the exhaust ports in described fan cabin, thus can switch at closedown described relief opening and not blocking between described relief opening.
9. device according to claim 6, it is characterized in that, described air entraining device is made up of air entraining pipe, bleed ring and diversion division, between described air entraining pipe, bleed ring and diversion division, mutual fluid is communicated with, and described air entraining pipe is communicated with described fan cabin fluid, described diversion division leads to the high-temperature zone in described core cabin.
10. device according to claim 9, is characterized in that, described diversion division leads to one-tenth annex in described core cabin to cool it.
11. devices according to claim 9, is characterized in that, arrange multiple pod apertures or many honeycomb ducts along described bleed ring circumference, and described multiple pod apertures or many honeycomb ducts carry out orientation to high-temperature zone, many places respectively and concentrate cooling.
12. devices according to claim 11, it is characterized in that, the exhaust in the effective bleed area≤described core cabin of the effective bleed area≤described air entraining pipe of the described air entraining jet in described fan cabin is sewed with effect leaving area, and the useful area sum of described honeycomb duct is not less than effective bleed area of described air entraining pipe, and the caliber of described honeycomb duct is not more than the caliber of described bleed ring.
13. devices according to claim 11, is characterized in that, described honeycomb duct number is N, and 4≤N≤8.
14. devices according to claim 6, it is characterized in that, described air entraining device is provided with air entraining pipe, and described air entraining pipe is communicated with described fan cabin fluid, and the relief opening cross section in the import cross section of described air entraining pipe and described fan cabin forms angle α, and 30 °≤α≤120 °.
15. devices according to claim 6, it is characterized in that, described air entraining device is provided with air entraining pipe, and described air entraining pipe is communicated with described fan cabin fluid, and the relief opening cross section in the import cross section of described air entraining pipe and described fan cabin forms angle α, 90 °≤α≤120 °.
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| CN106882390A (en) * | 2015-12-15 | 2017-06-23 | 中航商用航空发动机有限责任公司 | Airplane air entraining precooling heat regenerative system |
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| CN115845290A (en) * | 2022-12-27 | 2023-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Fire extinguishing pipe network for engine compartment |
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| CN110500185A (en) * | 2019-07-25 | 2019-11-26 | 中国商用飞机有限责任公司 | Ventilation cooling device for air entraining valve |
| CN112455700A (en) * | 2020-11-25 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Engine compartment cooling device |
| CN113022858A (en) * | 2021-03-04 | 2021-06-25 | 中国电子科技集团公司第二十九研究所 | Nacelle air inlet and exhaust device |
| CN113606045A (en) * | 2021-07-15 | 2021-11-05 | 南京航空航天大学 | Large-bypass-ratio turbofan engine core cabin ventilation structure and ventilation method thereof |
| CN113882954A (en) * | 2021-09-17 | 2022-01-04 | 北京动力机械研究所 | Low flow resistance diverging device |
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| CN114543567A (en) * | 2022-02-25 | 2022-05-27 | 中国商用飞机有限责任公司 | Valve cooling assembly |
| CN114543567B (en) * | 2022-02-25 | 2022-10-11 | 中国商用飞机有限责任公司 | Valve cooling assembly |
| CN115845290A (en) * | 2022-12-27 | 2023-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Fire extinguishing pipe network for engine compartment |
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