CN104948286B - The cooling means and cooling device in engine core cabin - Google Patents
The cooling means and cooling device in engine core cabin Download PDFInfo
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- CN104948286B CN104948286B CN201410118225.7A CN201410118225A CN104948286B CN 104948286 B CN104948286 B CN 104948286B CN 201410118225 A CN201410118225 A CN 201410118225A CN 104948286 B CN104948286 B CN 104948286B
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Abstract
The invention provides a kind of cooling means and cooling device in engine core cabin.In this method, by carrying out secondary use to the cooling air-flow of fan nacelle, core nacelle is introduced into, the cooling of core nacelle can be realized.Under ground run state, ambient windstream is aerated cooling by free convection from fan nacelle exhaust outlet into fan nacelle, is finally discharged from fan nacelle air inlet.In other state of flights, ambient windstream is acted on from fan nacelle air inlet by punching press to be entered, it is divided into two strands of left and right and cooling is aerated to fan nacelle, then core nacelle is introduced by air entraining pipe under fan nacelle and core nacelle differential pressure action, cooling is aerated to core nacelle, while concentration cooling can be oriented to area of Cang Nei localized hyperthermias under mozzle guiding.So as to realize the ventilating and cooling of core nacelle, reduce the outer amount of air entrainment for containing runner, reduce the outer bleed loss contained, while realize the secondary use of fan nacelle ventilating and cooling air-flow.
Description
Technical field
The present invention relates to aircraft engines, and in particular to the cooling means and cooling device of aircraft engine core nacelle.
Background technology
Engine core machine, casing and various engine accessory power ratings are contained in engine core cabin.Engine leads to when working
Cross casing and transmit amount of heat to core nacelle, if heat can not in time disperse or assemble rapidly, the pipe in cabin can be caused
Road and annex cisco unity malfunction, or even trigger fire, on the one hand core nacelle ventilation cooling system can cool down to be loaded in starts
On the other hand all kinds of annexes and casing on machine casing can ensure the circulation of cabin inner air, so as to prevent combustibility in itself
Aggregation of the gas in cabin, eliminate disaster hidden-trouble.Therefore, core nacelle ventilating and cooling technology is to ensureing external engine piping and attached
Part normal work, it is significant to reduce fire possibility occurrence.
Current civilian fanjet core nacelle ventilating and cooling bleed form mainly has the bleed of bleed hole and wind scoop bleed two
Kind.Wherein bleed hole bleed flow is small, and externally culvert effect of aerodynamic performance is also smaller, wind scoop bleed efficiency high, in identical bleed
In the case of area, wind scoop amount of air entrainment is about 2.4 times of bleed hole or so, but it is larger externally to contain effect of aerodynamic performance, it is therefore desirable to
Contain aeroperformance and cooling effect outside comprehensive assessment to determine bleed form.
However, for civilian fanjet, the cooling air-flow of core nacelle ventilating and cooling technology both is from outer at present
Contain, it is smaller externally to contain effect of aerodynamic performance using the bleed of bleed hole merely, but it is difficult to meets respectively to manage under the takeoff condition of high temperature plateau
The temperature requirement of road annex, the temperature requirement of high temperature plateau takeoff condition is disclosure satisfy that only with wind scoop bleed, but externally contains gas
Dynamic performance is larger, and because ambient temperature is very low under cruising condition, it is not necessary to very big amount of air entrainment also disclosure satisfy that
The temperature requirement of annex in cabin, this results in the aerodynamic loss that outer culvert is unnecessary under cruising condition.
Therefore, under different flight status, engine reduces outer on the premise of it disclosure satisfy that the requirement of ventilating and cooling
Containing aerodynamic loss turns into one of emphasis of current core nacelle ventilating and cooling concern.
The content of the invention
Technical problem to be solved
When being aerated cooling to civilian fanjet core nacelle, in order to reduce the bleed load contained outside, the present invention
Devise a kind of method that cooling air-flow using fan nacelle is aerated cooling to core nacelle.Designed, will started by this
Cooling air-flow in machine fan nacelle（The air-flow to fan nacelle ventilating and cooling is completed）Core nacelle is introduced and to core by air entraining pipe
Heart cabin is aerated cooling, on the one hand can reduce the introduction volume of outer culvert air-flow, reduce bleed loss, on the other hand can realize
Cooling is oriented to area of localized hyperthermia in core nacelle, reaches the temperature requirement in cabin.
Used technical scheme
According to an aspect of the present invention, there is provided a kind of cooling means of aircraft engine core nacelle, the aircraft engine
Machine includes core nacelle and fan nacelle, and the fan nacelle is provided with bleed ports and exhaust outlet, it is characterised in that methods described includes：
Exhaust outlet governor motion is set in the exhaust ports of the fan nacelle, and enables the exhaust outlet governor motion
Switch between first position and the second place；
Set air entraining device, the air entraining device air-flow from the fan nacelle can be guided to the core nacelle with
The core nacelle is cooled down；And
In the first position so that the exhaust outlet governor motion closes the exhaust outlet of the fan nacelle, so that
Enter the core nacelle via the air entraining device from the air-flow of fan nacelle outflow；In the second place so that described
Exhaust outlet governor motion does not block the exhaust outlet of the fan nacelle.
In the above method, it is preferred that the exhaust outlet governor motion is spoiler, during aircraft flight, by the resistance
Flowing plate is placed on the first position, to be oriented collection to the area of localized hyperthermia in the core nacelle by the air entraining device
Middle cooling；And in aircraft floor dead ship condition, the spoiler is placed on the second place, ensure ambient windstream through institute
The exhaust outlet for stating fan nacelle is aerated cooling into the fan nacelle to the fan nacelle.
In the above method, it is preferred that the exhaust outlet governor motion is venetian blind type valve, will during aircraft flight
The venetian blind type valve is placed on the first position, with by the air entraining device to the localized hyperthermia in the core nacelle
Area is oriented concentration cooling；And in aircraft floor dead ship condition, the venetian blind type valve is placed on the second
Put, ensure that exhaust outlet of the ambient windstream through the fan nacelle is aerated cooling into the fan nacelle to the fan nacelle.
In the above method, it is preferred that the entrance of the air entraining device and the fan nacelle are in fluid communication, and draw described
The outlet of device of air is in fluid communication with the core nacelle.
In the above method, it is preferred that the air entraining device is provided with multiple outlets, the multiple outlet respectively leads to described
Multiple high-temperature regions of core nacelle, to be oriented cooling to the multiple high-temperature region respectively.
According to another aspect of the present invention, a kind of cooling device of aircraft engine core nacelle, the aircraft are additionally provided
Engine includes core nacelle and fan nacelle, and the fan nacelle is provided with bleed ports and exhaust outlet, it is characterised in that the cooling device
Including：
The exhaust outlet governor motion of the exhaust ports of the fan nacelle is arranged on, the exhaust outlet governor motion can be
Switch between one position and the second place；
Air entraining device, the air entraining device can be guided the air-flow from the fan nacelle to the core nacelle with to institute
Core nacelle is stated to be cooled down；And
In the first position, the exhaust outlet governor motion closes the exhaust outlet of the fan nacelle so that from the wind
The air-flow of fan cabin outflow enters enters the core nacelle via the air entraining device；In the second place, the exhaust outlet is adjusted
The exhaust outlet of the fan nacelle is not blocked in section mechanism.
In above-mentioned cooling device, it is preferred that the exhaust outlet governor motion is spoiler, the spoiler is via rotational pin
The exhaust ports of the fan nacelle are rotatably installed on, so as to close the exhaust outlet and do not blocking the exhaust outlet
Between switch.
In above-mentioned cooling device, it is preferred that the exhaust outlet governor motion is venetian blind type valve, the venetian blind type is lived
Door is installed on the exhaust ports of the fan nacelle, so as to be cut between closing the exhaust outlet and not blocking the exhaust outlet
Change.
In above-mentioned cooling device, it is preferred that the air entraining device is made up of air entraining pipe, bleed ring and diversion division, it is described
It is in fluid communication with each other between air entraining pipe, bleed ring and diversion division, and the air entraining pipe is in fluid communication with the fan nacelle, it is described
Diversion division leads to the high-temperature region of the core nacelle.
It is preferred that the diversion division lead in the core nacelle into annex to be cooled down to it.
It is preferred that along the circumferentially disposed multiple pod apertures of the bleed ring or more mozzles, the multiple pod apertures or more
Root mozzle is oriented concentration cooling to many places high-temperature region respectively.
It is preferred that effective bleed area of effective bleed area≤air entraining pipe of the bleed ports of the fan nacelle
The exhaust of≤the core nacelle is sewed with effect leaving area, and the effective area sum of the mozzle is not less than the air entraining pipe
Effective bleed area, and the caliber of the mozzle are not more than the caliber of the bleed ring.
It is preferred that the mozzle number is N, and 4≤N≤8.
In above-mentioned cooling device, it is preferred that the air entraining device is provided with air entraining pipe, the air entraining pipe and the fan nacelle stream
Body connects, and the import section of the air entraining pipe and the exhaust outlet section formation angle α of the fan nacelle, and 30 °≤α≤
120°。
In above-mentioned cooling device, it is preferred that the air entraining device is provided with air entraining pipe, the air entraining pipe and the fan nacelle stream
Body connects, and the import section of the air entraining pipe and the exhaust outlet section formation angle α of the fan nacelle, 90 °≤α≤120 °.
The present invention is introduced into core nacelle, can realize core by carrying out secondary use to the cooling air-flow of fan nacelle
The cooling in cabin.Under ground run state, ambient windstream is led to by free convection from fan nacelle exhaust outlet into fan nacelle
Air cooling, finally discharged from fan nacelle air inlet.In other state of flights, ambient windstream is acted on from fan nacelle air inlet by punching press
Mouth enters, and is divided into two strands of left and right and cooling is aerated to fan nacelle, then by bleed under fan nacelle and core nacelle differential pressure action
Pipe introduces core nacelle, cooling is aerated to core nacelle, while area of Cang Nei localized hyperthermias can be determined under mozzle guiding
Cooled down to concentrating.So as to realize the ventilating and cooling of core nacelle, reduce the outer amount of air entrainment for containing runner, reduce the outer bleed loss contained,
The secondary use of fan nacelle ventilating and cooling air-flow is realized simultaneously.
Brief description of the drawings
Fig. 1 is the structural representation of the civilian fanjet provided with the cooling device according to the present invention, and it utilizes fan
Cabin cooling air-flow is to core nacelle ventilating and cooling, and arrow represents the flow direction of air-flow in figure；
The structural representation of air entraining device in Fig. 2 Fig. 1；
Fig. 3 is the circumferential structural representation of the air entraining device of the core nacelle in Fig. 1；
Fig. 4 is the structural representation of another embodiment of air entraining device；And
Fig. 5 is the exhaust outlet governor motion structural representation of air entraining device and fan nacelle.
Description of reference numerals：
0. fan is bored；1. inlet lip outer wall；2. inlet lip inwall；3. fan nacelle bleed ports；4. fan nacelle；5.
Fan fairing；6. fan nacelle fire wall；Contain outer wall outside 7.；8. by-pass air duct；Contain inwall outside 9.；10. core hood；Contain outside 11.
Outlet；12. into annex；13. core nacelle；14. mozzle；15. bleed ring；16. fan support plate；17. air entraining pipe；18. rotational pin；
19. fan nacelle exhaust outlet；20. spoiler；21. fan.
Embodiment
Presently preferred embodiments of the present invention is described in detail below with reference to accompanying drawing, to become apparent from understanding the present invention's
Objects, features and advantages.It should be understood that embodiment shown in the drawings does not limit the scope of the present invention, and it is simply
The connotation of explanation technical solution of the present invention.In accompanying drawing, identical element is indicated with same or analogous reference.
Fig. 1 is shown in aircraft engine, is aerated the structural representation of cooling to core nacelle using fan nacelle cooling air-flow
Figure.As shown in figure 1, aircraft machine engine generally comprises core nacelle and fan nacelle, it is provided with core nacelle various into annex 12.Flying
During machine is run, it is necessary to be cooled down to fan nacelle and core nacelle especially during flight, so as to ensure fan nacelle and core
Heart cabin and various components therein, are such as cooled down into annex, to ensure its normal work.
In general, in existing aircraft, fan nacelle is provided with bleed ports 3 and exhaust outlet 19, for being cooled down to fan nacelle.
Specifically, during aircraft, surrounding air is flowed into because punching press is acted on from the bleed ports 3 of fan nacelle, and fan nacelle is aerated
Cooling, and cooling is aerated to it into fan nacelle through fan nacelle exhaust outlet 19 in ground parking state, ambient windstream.
Cooling for core nacelle, presently mainly passes through wind scoop（It is not shown）With bleed hole（It is not shown）Introduce environment gas
Body, to be cooled down to core nacelle.But there is such as cause outer the problems such as containing unnecessary aerodynamic loss for this type of cooling.
Applicant passes through the discovery that studies for a long period of time, during the flight of aircraft, after environmental gas is completed to the cooling of fan nacelle,
Though gas flow temperature has raised, temperature in core nacelle is still below, therefore, it is contemplated by the invention that one kind reuses this portion gas
Carry out the method in coolant core cabin.
This method includes：Exhaust outlet governor motion is set in the exhaust ports of fan nacelle, and causes the exhaust outlet regulation
Mechanism can switch between first position and the second place；Air entraining device is set, and the air entraining device can will come from the wind
The air-flow in fan cabin is guided to the core nacelle to be cooled down to the core nacelle；And in the first position so that described
Exhaust outlet governor motion closes the exhaust outlet of the fan nacelle, so that the air-flow from fan nacelle outflow draws via described
Device of air enters the core nacelle；In the second place so that the exhaust outlet governor motion does not block the fan nacelle
Exhaust outlet.
It is preferred that during aircraft flight, the exhaust outlet governor motion is placed on the first position, to pass through
State air entraining device and concentration cooling is oriented to the area of localized hyperthermia in the core nacelle.In aircraft floor dead ship condition, by institute
State exhaust outlet governor motion and be placed on the second place, ensure that exhaust outlet of the ambient windstream through the fan nacelle enters the wind
Fan cabin is aerated cooling to the fan nacelle.
It is preferred that exhaust outlet governor motion is spoiler, and the spoiler can rotate in the range of certain angle, from
And it can close or open（Do not block）The exhaust outlet of fan nacelle.
It is preferred that the entrance of the air entraining device and the fan nacelle are in fluid communication, and going out the air entraining device
Mouth is in fluid communication with the core nacelle.
Air entraining device can be provided with multiple outlets, the multiple to export the multiple high-temperature regions for respectively leading to the core nacelle, with
Cooling is oriented to the multiple high-temperature region respectively, so as to being cooled down at these regions into annex etc..Air entraining device can
Different structures is arranged as required into, is detailed further below.
Fig. 1 is shown according to above-mentioned principle, is aerated the method for cooling to core nacelle using the cooling gas of fan nacelle
The structural representation of one concrete application embodiment.As shown in figure 1, using the cooling gas of fan nacelle to aircraft engine core
The cooling device in cabin mainly includes being arranged on the spoiler 20 and air entraining device 100 at the exhaust outlet 19 of fan nacelle 4.Referring to Fig. 5,
Spoiler 20 is rotatably installed at the exhaust outlet 19 of fan nacelle 4 via rotational pin 18, so as to close the exhaust
Mouthfuls 19 and do not block and switch between the exhaust outlet 19.
Spoiler 20 is plate-like piece, is sized to close the exhaust outlet 19 of fan nacelle.It should be understood that spoiler
20 also can be other by that can be changed between the second place closed the first position of exhaust outlet 19 and do not block exhaust outlet 19
Exhaust outlet governor motion is formed.In the first position, the spoiler closes the exhaust outlet of the fan nacelle so that from described
The air-flow of fan nacelle outflow enters enters the core nacelle via the air entraining device.In the second place, the spoiler
The exhaust outlet of the fan nacelle is not blocked, so as to which surrounding air can enter fan nacelle by exhaust outlet, to be carried out to fan nacelle
Cooling.
The optional alternative structure of one of spoiler is the valve of venetian blind type（It is not shown）.The venetian blind type valve is installed
At the exhaust outlet 19 of fan nacelle.During aircraft, the venetian blind type valve is closed, so as to close the row of fan nacelle
Gas port 19 so that enter from the air-flow of fan nacelle outflow and enter core nacelle via air entraining device 100.And in ground parking shape
State, the venetian blind type valve are in open mode, and ambient windstream enters fan nacelle by free convection through fan nacelle exhaust outlet 19
It is aerated cooling.
It is preferred that spoiler 20 can be turned according to the instruction from engine control system by motor driven choked flow door
Axle rotates, so as to switch in spoiler between first position and the second place, i.e., close the exhaust outlet 19 with
Do not block and switch between the exhaust outlet 19.In its alternate embodiment, venetian blind type valve also can be according to from engine
The instruction of control system switches between open and close status, that is, is closing the exhaust outlet 19 with opening the exhaust outlet 19
Between switch.
Air entraining device 100 is made up of bleed ring 15, air entraining pipe 17 and mozzle 14, wherein air entraining pipe 17, bleed ring 15
And be in fluid communication with each other between mozzle 14, and the air entraining pipe 17 is in fluid communication with the fan nacelle 4, the mozzle 14
Lead to the high-temperature region of the core nacelle 13, with to being cooled down in the core nacelle 13 into annex to it.
Bleed ring 15 is fixedly mounted on core nacelle inwall by pipeline clamp and support and installed on side, its pipeline clamp and branch
Frame can carry out different designs according to being actually needed.Bleed ring can be fabricated to different shape as needed.Bleed shown in Fig. 2
Ring is annulus, but one of ordinary skill in the art will be understood that, bleed ring 15 can also be Q-RING, polygon ring, ellipse
Ring etc..Bleed ring 15 can connect to be formed in order to be installed in core nacelle by multiple pipeline sections by pipe joint.
Bleed ring 15 is provided with multiple gas outlets（It is not shown）, each gas outlet is in fluid communication with a mozzle 14.Go out
The quantity of gas port can correspondingly be set according to the quantity of mozzle 14.
More mozzles 14 are circumferentially disposed along the bleed ring 14, and the more mozzles are carried out to many places high-temperature region respectively
Orientation concentrates cooling.The quantity of mozzle can be set as needed, still, to ensure ventilating and cooling effect in core nacelle,
The choked flow for containing cooling air-flow outside core nacelle is acted in view of mozzle simultaneously, mozzle number N is preferably 4≤N≤8, week
Can be depending on temperature requirements in cabin to distribution mode.
Depending on structure arrangement of the length of mozzle 14 in core nacelle length, cabin into annex, the temperature requirement in cabin,
Orientation is needed to concentrate the region of cooling mozzle directly can be reached into the region in the range of allowing in space.
The import of air entraining pipe 17 is in fluid communication with fan nacelle, and outlet is in fluid communication with bleed ring 15.The specific shape of air entraining pipe
Shape can carry out respective design according to actual conditions.But to ensure not influenceing the ventilating and cooling effect under fan nacelle different conditions,
It is easier to realize the switching of air flow path, air entraining pipe import axial location is preferably located at fan nacelle exhaust ports, air entraining pipe import
Section and fan nacelle exhaust outlet section formation angle α, 30 °≤α≤120 °, but effect is preferable during 90 °≤α≤120 °, ensures gas
Stream smoothly enters core nacelle.
In addition, damming to be occurred without when ensureing that air-flow enters core nacelle, while core nacelle can be smoothly discharged, positioned at fan
The effective bleed area S of bleed ports in cabinEntranceThe effective bleed area S of≤air entraining pipe≤core nacelle exhaust is sewed with effect leaving area SOutlet,
Mozzle effective area sum SPipeThe effective bleed area S, mozzle caliber D of air entraining pipe should be not less thanPipeNo more than bleed endless tube
Footpath DRing。
One embodiment of the air entraining device 100 according to the present invention is described above in association with accompanying drawing.However, this area is general
Logical technical staff should be understood that after reading this description air entraining device 100 can also be can be by from the fan nacelle
Air-flow guides to the core nacelle other air entraining devices to be cooled down to the core nacelle.
As an alternate embodiment, Fig. 4 shows another air entraining device.The air entraining device is simultaneously not provided with mozzle, but directly
It is connected on bleed ring and opens up pod apertures, of water conservancy diversion aperture and pod apertures can be suitably increased for the position for needing special cooling
Number.
The present invention relates to a kind of method and cooling device for being aerated cooling to core nacelle using fan nacelle cooling air-flow,
The cooling means considers to carry out secondary use to the cooling air-flow of fan nacelle, is introduced into core nacelle and continues to cool down.Interviewed on ground
Under car state, ambient windstream is aerated cooling by free convection from fan nacelle exhaust outlet into fan nacelle, finally from fan
Cabin air inlet discharge, exhaust outlet governor motion is now placed on to the porch of air entraining device, ensures that air-flow smoothly enters fan
Cabin.In other state of flights, exhaust outlet governor motion is placed on fan nacelle exhaust outlet, ambient windstream is acted on from wind by punching press
Fan cabin air inlet to enter, be divided into two strands of left and right and cooling is aerated to fan nacelle, then in fan nacelle and core nacelle differential pressure action
Under core nacelle introduced by air entraining pipe, cooling is aerated to core nacelle, while can be to Cang Nei localized hyperthermias under mozzle guiding
Area is oriented concentration cooling.
The beneficial effect of the invention：
（1）Will complete to fan nacelle cooling air-flow by air entraining pipe introduce core nacelle core nacelle is aerated it is cold
But, reduce the outer amount of air entrainment for containing runner, reduce the outer bleed loss contained, while realize the secondary profit of fan nacelle ventilating and cooling air-flow
With.
（2）Can the region high to temperature requirement in cabin be oriented concentration cooling, ensure that pipeline and annex are just in core nacelle
Often work.
（3）The ventilating and cooling effect of fan nacelle under ground parking state can be ensured
Presently preferred embodiments of the present invention is described in detail above, it is understood that being said having read the above-mentioned of the present invention
After awarding content, those skilled in the art can make various changes or modifications to the present invention.These equivalent form of values equally fall within this
Apply for appended claims limited range.
Claims (15)
1. a kind of cooling means of aircraft engine core nacelle, the aircraft engine includes core nacelle and fan nacelle, the wind
Fan cabin is provided with bleed ports and exhaust outlet, it is characterised in that methods described includes：
Exhaust outlet governor motion is set in the exhaust ports of the fan nacelle, and enables the exhaust outlet governor motion the
Switch between one position and the second place；
Air entraining device is set, and the air entraining device can be guided the air-flow from the fan nacelle to the core nacelle with to institute
Core nacelle is stated to be cooled down；And
In the first position so that the exhaust outlet governor motion closes the exhaust outlet of the fan nacelle, so that from institute
The air-flow for stating fan nacelle outflow enters the core nacelle via the air entraining device；In the second place so that the exhaust
Mouth governor motion does not block the exhaust outlet of the fan nacelle.
2. according to the method for claim 1, it is characterised in that the exhaust outlet governor motion is spoiler, is flown in aircraft
Between the departure date, the spoiler is placed on the first position, with by the air entraining device to the part in the core nacelle
High-temperature region is oriented concentration cooling；And
In aircraft floor dead ship condition, the spoiler is placed on the second place, ensures ambient windstream through the fan
The exhaust outlet in cabin is aerated cooling into the fan nacelle to the fan nacelle.
3. according to the method for claim 1, it is characterised in that the exhaust outlet governor motion is venetian blind type valve,
During aircraft flight, the venetian blind type valve is placed into the first position, with by the air entraining device to the core
Area of localized hyperthermia in cabin is oriented concentration cooling；And
In aircraft floor dead ship condition, the venetian blind type valve is placed on the second place, ensures ambient windstream through institute
The exhaust outlet for stating fan nacelle is aerated cooling into the fan nacelle to the fan nacelle.
4. according to the method for claim 1, it is characterised in that by the entrance of the air entraining device and the fan nacelle fluid
Connection, and the outlet of the air entraining device and the core nacelle are in fluid communication.
5. according to the method for claim 1, it is characterised in that the air entraining device is provided with multiple outlets, it is the multiple go out
Mouth respectively leads to multiple high-temperature regions of the core nacelle, to be oriented cooling to the multiple high-temperature region respectively.
6. a kind of cooling device of aircraft engine core nacelle, the aircraft engine includes core nacelle and fan nacelle, the wind
Fan cabin is provided with bleed ports and exhaust outlet, it is characterised in that the cooling device includes：
The exhaust outlet governor motion of the exhaust ports of the fan nacelle is arranged on, the exhaust outlet governor motion can be at first
Put and switch between the second place；
Air entraining device, the air entraining device can be guided the air-flow from the fan nacelle to the core nacelle with to the core
Heart cabin is cooled down；And
In the first position, the exhaust outlet governor motion closes the exhaust outlet of the fan nacelle so that from the fan nacelle
The air-flow of outflow enters the core nacelle via the air entraining device；In the second place, the exhaust outlet governor motion is not
Block the exhaust outlet of the fan nacelle.
7. device according to claim 6, it is characterised in that the exhaust outlet governor motion is spoiler, the choked flow
Plate is rotatably installed on the exhaust ports of the fan nacelle via rotational pin, so as to close the exhaust outlet with not hiding
Keep off between the exhaust outlet and switching.
8. device according to claim 6, it is characterised in that the exhaust outlet governor motion is venetian blind type valve, institute
The exhaust ports that venetian blind type valve is installed on the fan nacelle are stated, so as to close the exhaust outlet and do not blocking described
Switch between exhaust outlet.
9. device according to claim 6, it is characterised in that the air entraining device is by air entraining pipe, bleed ring and water conservancy diversion
Portion is formed, and is in fluid communication with each other between the air entraining pipe, bleed ring and diversion division, and the air entraining pipe and the fan nacelle stream
Body connects, and the diversion division leads to the high-temperature region of the core nacelle.
10. device according to claim 9, it is characterised in that the diversion division lead in the core nacelle into annex
To be cooled down to it.
11. device according to claim 9, it is characterised in that along the circumferentially disposed multiple pod apertures or more of the bleed ring
Root mozzle, the multiple pod apertures or more mozzles are oriented concentration cooling to many places high-temperature region respectively.
12. device according to claim 11, it is characterised in that effective bleed face of the bleed ports of the fan nacelle
Effective leaving area of the exhaust seam of effective bleed area≤core nacelle of product≤air entraining pipe, and the mozzle
Effective area sum is not less than effective bleed area of the air entraining pipe, and the caliber of the mozzle is not more than the bleed
The caliber of ring.
13. device according to claim 11, it is characterised in that the mozzle number is N, and 4≤N≤8.
14. device according to claim 6, it is characterised in that the air entraining device is provided with air entraining pipe, the air entraining pipe with
The fan nacelle is in fluid communication, and the import section of the air entraining pipe and the exhaust outlet section of the fan nacelle form angle α, and
30°≤α≤120°。
15. device according to claim 6, it is characterised in that the air entraining device is provided with air entraining pipe, the air entraining pipe with
The fan nacelle is in fluid communication, and the import section of the air entraining pipe and the exhaust outlet section of the fan nacelle form angle α,
90°≤α≤120°。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410118225.7A CN104948286B (en) | 2014-03-27 | 2014-03-27 | The cooling means and cooling device in engine core cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410118225.7A CN104948286B (en) | 2014-03-27 | 2014-03-27 | The cooling means and cooling device in engine core cabin |
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| CN104948286B true CN104948286B (en) | 2018-01-09 |
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|---|---|---|---|---|
| CN106882390B (en) * | 2015-12-15 | 2020-06-19 | 中国航发商用航空发动机有限责任公司 | Aircraft air-entraining precooling regenerative system |
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