CN215696661U - Aeroengine washs waste liquid collecting system and washs structure - Google Patents
Aeroengine washs waste liquid collecting system and washs structure Download PDFInfo
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- CN215696661U CN215696661U CN202121321107.8U CN202121321107U CN215696661U CN 215696661 U CN215696661 U CN 215696661U CN 202121321107 U CN202121321107 U CN 202121321107U CN 215696661 U CN215696661 U CN 215696661U
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Abstract
The utility model provides an aero-engine cleaning waste liquid collecting system and a cleaning structure. Aeroengine washs waste liquid collection system includes: the separation device comprises a shell and a flow guide pipe, wherein at least part of the flow guide pipe is positioned in the shell, and the separation device is provided with an inlet part, an air outlet part and a liquid outlet part; the axial line of the inlet part and the axial line of the guide pipe are arranged in a non-coincident manner, an opening of the guide pipe in the shell forms an air outlet part, and the pipe wall of the guide pipe in the shell and the shell form a guide structure; and the collecting device is positioned below the separating device. The aircraft engine water washing structure comprises an aircraft engine and the collecting device. The utility model can collect and clean waste liquid of the aircraft engine and separate impurities and dirt liquid droplets from the sprayed dirt fog and collect the impurities and the dirt liquid droplets.
Description
Technical Field
The utility model relates to the field of cleaning of aircraft engines, in particular to a cleaning waste liquid collecting system and a cleaning structure of an aircraft engine.
Background
The commercial aircraft engine adopts a turbofan engine, and as the flying hours of an aircraft increase, impurities can be attached to an air flow passage of the aircraft engine, so that the performance of the aircraft engine is reduced. The air passage of the aircraft engine is cleaned regularly, so that the working efficiency of the aircraft engine can be improved, the service life is prolonged, and the fuel consumption is reduced. The performance of a large number of commercial aircraft engines can be significantly upgraded after they have been cleaned by the cleaning system, but since aircraft engines cannot be frequently disassembled, it is important to clean the wings. The washing of the aero-engine refers to the washing of an aero-engine gas circuit, and mainly aims at the washing of an inner duct of the aero-engine.
When the wings of the aircraft engine are cleaned, the engine is started to run cold, namely, the starter is used for driving the aircraft engine to run, and oil injection and ignition are not carried out in the period. The water flow is sprayed into a main flow passage of the engine from the front end of the aircraft engine, and flows out and is sprayed out from an engine tail nozzle along with air flow sucked by cold running of the engine. The discharged sewage and the water mist carrying the pollutants can pollute an airport and damage the body of an operator. Therefore, the waste liquid generated during the washing of the aircraft engine needs to be collected, and particularly impurities and sewage droplets are separated from the sprayed water mist. Because the jet volume is large and the jet velocity is fast when the engine is washed with water, the waste liquid collection system should catch the waste water and reliably separate impurities and droplets of the waste water in the high velocity gas stream.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a cleaning waste liquid collecting system for an aircraft engine.
Another object of the present invention is to provide an aircraft engine washing arrangement.
According to one aspect of the utility model, an aircraft engine washing waste liquid collecting system comprises: a separation device comprising a housing and a draft tube at least partially within the housing, the separation device having an inlet portion for receiving a mixture of air and cleaning liquid, an air outlet portion for outputting separated air, and a liquid outlet portion for outputting separated liquid; the axis of the inlet part and the axis of the draft tube are arranged in a non-coincidence manner, the opening of the draft tube in the shell forms the air outlet part, and the tube wall of the draft tube in the shell and the shell form a flow guide structure; a collection device located below the separation device for receiving a stream of wash liquid and separated liquid output from the liquid outlet portion.
In an alternative embodiment, the housing comprises an annular section having a sidewall connected to the inlet portion and a conical section having a small end comprising the conical section
In an alternative embodiment, the flow guide pipe and the liquid outlet are respectively located at two ends of the housing in the axial direction.
In an alternative embodiment, the draft tube and the liquid outlet are located in the center of the housing.
In an alternative embodiment, the inlet section includes a constant cross-section and a flared section, the constant cross-section being connected to the housing.
In an alternative embodiment, the axis of the inlet portion is arranged perpendicular to the axis of the draft tube.
In an alternative embodiment, the collecting device is a mounting base of the aircraft engine washing waste liquid collecting system, and the separating device is mounted to the collecting device.
In an alternative embodiment, the collecting device is mobile.
An aircraft engine washing arrangement according to another aspect of the utility model comprises an aircraft engine and a collection device as described above, the collection device having a collection area extending from below the aircraft engine to below the liquid outlet portion.
In an alternative embodiment, the axis of the aircraft engine coincides with the axis of the inlet portion.
The utility model has the beneficial effects that:
the separating device and the collecting device are arranged, so that waste liquid discharged when the aircraft engine is cleaned and impurities and dirty liquid droplets separated from sprayed dirty mist can be effectively collected, pollution to an airport and health damage to an operator are prevented.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent by describing in further detail embodiments of the present invention with reference to the attached drawings, in which:
FIG. 1 is a schematic view of an aircraft engine wash waste collection system;
FIG. 2 is a schematic cross-sectional view of a separation apparatus;
FIG. 3 is a schematic view of the inlet portion axis and the guide pipe axis.
Reference numerals:
1-aircraft engine, 101-aircraft engine axis;
2-cleaning fluid, 3-dirty fog and 4-dirty liquid;
5-an aeroengine cleaning waste liquid collecting system;
6-collecting device, 601-caster;
7-a separation device;
8-an air outlet;
9-shell, 901-ring section, 9011-ring section side wall, 902-taper section, 9021-taper section small end;
10-a flow guide pipe, 1001-a flow guide pipe axis, 1002-a pipe wall and 1003-a flow guide structure;
12-a liquid outlet portion;
11-a tail nozzle;
13-entry, 1301-entry axis, 1302-flared section, 1303-constant cross-section.
Detailed Description
Reference will now be made in detail to various embodiments of the utility model, examples of which are illustrated in the accompanying drawings and described below. While the utility model will be described in conjunction with the exemplary embodiments, it will be understood that this description is not intended to limit the utility model to those exemplary embodiments. On the contrary, the utility model is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents and other embodiments, which may be included within the spirit and scope of the utility model as defined by the appended claims.
In the following description of the embodiments, an orientation or positional relationship that is "axial," "downward," "front," "rear," or other orientation term indicates is based on the orientation or positional relationship shown in the drawings, is for convenience only to facilitate description of the utility model and to simplify description, and does not indicate or imply that the referenced device or component must have a particular orientation, be constructed and operated in a particular orientation, and is therefore not to be construed as limiting the utility model.
After the aircraft flies for a certain mileage, impurities can be attached to the air flow passage of the aircraft engine, so that the performance of the engine is reduced, and the working efficiency is influenced. Cleaning fluid 2 spouts into aeroengine 1's sprue from aeroengine 1's front end to along with aeroengine 1 cold-running inspiratory air current flows out and blowout from aeroengine 1 tail nozzle, and exhaust foul solution 4 and the dirty fog 3 that carries the pollutant can cause the pollution to the airport, cause certain harm to operator's health, provide an aeroengine washing waste liquid collecting system now, can collect foul solution 4 and carry out the residual liquid of exhaust gas collection after the gas-liquid separation to dirty fog 3.
In the following description, the cleaning liquid 2 is exemplified by water, but not limited thereto.
Referring to fig. 1 in conjunction with fig. 2, in one embodiment, an aircraft engine washing waste liquid collection system includes a separation device 7 and a collection device 6. The separation device 7 comprises a shell 9 and a flow guide pipe 10, wherein the flow guide pipe 10 is at least partially positioned in the shell 9, the separation device 7 is also provided with an inlet part 13, an air outlet part 8 and a liquid outlet part 12, the inlet part 13 is used for receiving a mixture of air and cleaning liquid, the air outlet part 8 is used for outputting separated air, and the liquid outlet part 12 is used for outputting separated liquid; in this case, as shown in fig. 3, the axis 1301 of the inlet part is arranged non-coincident with the axis 1001 of the draft tube, the air outlet part 8 is formed by an opening of the draft tube 10 in the housing 9, and the tube wall 1002 of the draft tube 10 in the housing 9 forms a flow guiding structure 1003. A collection device 6 is located below the separation device 7 for receiving the stream of dirty liquid 4 flowing from the jet nozzle of the aircraft engine 1 and the separated liquid output from the liquid outlet 12. Cleaning fluid 2 sprays into aeroengine 1 main flow path back and divide into dirty liquid 4 and the spun dirty fog 3 that flow out from aeroengine 1 exhaust nozzle, and dirty liquid 4 is collected by collection device 6, and dirty fog 3 gets into casing 9 through access portion 13 and is divided into gas, impurity and dirty liquid droplet through water conservancy diversion structure 1003, and gas is discharged by air outlet portion 8, and impurity and dirty liquid droplet flow out by liquid outlet portion 12 and are collected by collection device 6. In other alternative embodiments, the collecting means may be provided separately for the foreign matter and dirty liquid droplets discharged from the liquid outlet portion 12, instead of sharing the collecting means 6 with the dirty liquid 4.
Referring to fig. 2, in one embodiment, the housing 9 is comprised of an annular section 901 with a sidewall 9011 connected to the inlet portion 13 and a tapered section 902 with a small end 9021 of the liquid outlet portion 12. The dirty fog 3 enters the annular section 901 from the inlet part 13 to do circular motion and separates gas from dirty liquid droplets and impurities by means of centrifugal force, the impurities and the dirty liquid droplets slide into the wall surface of the conical section 902 from the wall surface of the annular section 901 by means of gravity, then slide out of the separation device from the liquid outlet part 12, and the gas is discharged out of the separation device through the guide pipe 10.
With continued reference to fig. 2, in one embodiment, the draft tube 10 and the liquid outlet 12 are located at opposite axial ends of the housing 9. So arrange, the density difference of utilization gas that can be better and impurity, foul solution droplet, through the action of gravity, gas upwards discharges, and impurity and foul solution droplet discharge downwards obtain better gas-liquid separation effect.
Referring to fig. 1 in conjunction with fig. 2, in one embodiment, the draft tube 10 and the liquid outlet 12 are located at the central axis of the housing 9, and the design is such that the circular motion of the dirty mist 3 after entering the annular section 901 is more regular, and the gas-liquid separation effect is better by means of centrifugal force, and the structure of this embodiment is easy to process.
Referring to FIG. 1, in one embodiment, the inlet portion 13 includes a flared section 1302 and a constant cross-section 1303, the constant cross-section 1303 being coupled to the housing 9. Flaring section 1302 can accomodate into a large amount of dirty fog 3, reduces dirty fog 3's hourglass collection rate, and dirty fog 3 gets into by flaring section 1302, and after the equal cross section 1303 rectification, get into water conservancy diversion structure 1003, compare in not the scattered indiscriminate fog flow of rectification, can be better do circular motion and reach better centrifugal effect, simple structure is compact simultaneously, is convenient for accomodate and clean aeroengine washing waste liquid collecting system.
Referring to fig. 3, in one embodiment, the axis 1301 of the inlet portion is arranged perpendicular to the axis 1001 of the draft tube. When the included angle between the inlet part axis 1301 and the guide pipe axis 1001 is a right angle, compared with other angles, the right angle can achieve the best gas-liquid separation effect of circular motion depending on centrifugal force.
Referring to fig. 1, in one embodiment, the collecting device 6 is a mounting base of the aircraft engine washing waste liquid collecting system 5, and the separating device 7 is mounted on the collecting device 6, so that an integrated structure of the collecting device 6 and the separating device 7 is realized, and the aircraft engine washing waste liquid collecting system 5 is convenient to store.
Referring to fig. 1, in one embodiment, the collection device 6 is mobile. Collection device 6 sets up to movable, and separator 7 installs in collection device 6 simultaneously, has realized aeroengine washing waste liquid collection system 5's moving as a whole transportation and has accomodate, and the difficult transport of unnecessary operating personnel uses manpower sparingly, the operation of being convenient for. In other alternative embodiments, the collecting device 6 is provided with casters 601 at the lower part thereof to facilitate easy movement of the collecting device 6.
With continued reference to fig. 1, in one embodiment, an aircraft engine washing arrangement comprises an aircraft engine 1 and a collection device 6 as described in any of the above embodiments, the collection area of the collection device 6 extending from below the aircraft engine 1 to below the liquid outlet section 12. The arrangement of the collecting device 6 realizes that the stranded dirty liquid 4 flowing out of the aircraft engine 1 and the impurities and the dirty liquid droplets separated from the separating device 7 can be collected at the same time, the collecting device does not need to be additionally arranged for the impurities and the dirty liquid droplets discharged from the separating device 7, the manufacturing cost is saved, and the storage cost is also saved.
Continuing to refer to fig. 1, in an embodiment, axis 101 of the aircraft engine coincides with axis 1301 of the inlet portion, at this time, inlet portion 13 is facing to the tail of the aircraft engine, and compared with other corresponding modes of aircraft engine axis 101 and inlet portion axis 1301, coincidence of aircraft engine axis 101 and inlet portion axis 1301 can realize maximum collection of dirty fog 3 blown out from aircraft engine 1, reduce the leakage rate of dirty fog 3, and reduce pollution.
In one embodiment shown in fig. 1, when the aircraft engine 1 is used for cleaning operation, the aircraft engine 1 is driven by a starter to perform cold operation, the cleaning liquid 2 is sprayed into a flow passage of the aircraft engine from the front part of the aircraft engine, part of the cleaning liquid flows out of a tail nozzle 11 in a jet manner to form dirty liquid 4, and part of the cleaning liquid is sprayed out of the tail nozzle 11 in a form of dirty mist 3 at a certain speed and backwards. The effluent liquid 4 enters a collection device 6. The dirty fog 3 enters the separator 7 from the inlet 13 and then enters the annular section 901 to flow circumferentially, and centrifugal force throws the dirt and liquid droplets onto the wall surface of the annular section 901 to form wall-hung dirty liquid. The wall-hanging dirty liquid flows by gravity downwardly through the conical section 902 below the annular section 9 out of the liquid outlet portion 12 and into the collection means 6. The cleaned air flows through the draft tube 10 in the center of the annular section 901 and is discharged from the air outlet 8.
In summary, the beneficial effects of the aero-engine washing waste liquid collecting system and the aero-engine washing structure described in the above embodiments include, but are not limited to, one or a combination of the following:
1. and collecting waste liquid generated during the cleaning of the aircraft engine, and impurities and dirt liquid droplets separated from the sprayed dirt mist.
2. The centrifugal force principle is utilized to separate gas from dirt liquid droplets and impurities, and the conical section is utilized to lead the dirt liquid on the wall surface of the annular section out of the separating device downwards by means of gravity.
3. The whole that is convenient for aeroengine washs waste liquid collecting system transports and accomodates, uses manpower sparingly.
4. The liquid jet from the aircraft engine and the impurities and dirt droplets separated from the separating device can be collected simultaneously.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the utility model, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (10)
1. An aeroengine washing waste liquid collection system characterized by comprising:
a separation device comprising a housing and a draft tube at least partially within the housing, the separation device having an inlet portion for receiving a mixture of air and cleaning liquid, an air outlet portion for outputting separated air, and a liquid outlet portion for outputting separated liquid; the axis of the inlet part and the axis of the draft tube are arranged in a non-coincidence manner, the opening of the draft tube in the shell forms the air outlet part, and the tube wall of the draft tube in the shell and the shell form a flow guide structure;
a collection device located below the separation device for receiving a stream of wash liquid and separated liquid output from the liquid outlet portion.
2. The aircraft engine washing waste liquid collection system of claim 1, wherein the housing is comprised of an annular section having a sidewall connected to the inlet section and a conical section having a small end comprising the conical section.
3. The aircraft engine washing waste liquid collection system according to claim 1, wherein the flow guide pipe and the liquid outlet portion are respectively located at both ends of the housing in the axial direction.
4. The aircraft engine washing waste liquid collection system of claim 1, wherein the draft tube, the liquid outlet portion are located in the center of the housing.
5. The aircraft engine washing waste liquid collection system of claim 1, wherein the inlet portion comprises a constant cross-section and a flared section, the constant cross-section being connected to the housing.
6. The aircraft engine washing waste liquid collection system of claim 1, wherein the axis of the inlet portion is arranged perpendicular to the axis of the draft tube.
7. The aircraft engine washing waste liquid collection system of claim 1, wherein the collection device is a mounting base of the aircraft engine washing waste liquid collection system, and the separation device is mounted to the collection device.
8. The aircraft engine washing waste liquid collection system of claim 7, wherein the collection device is mobile.
9. An aircraft engine washing arrangement comprising an aircraft engine and a collection device according to any of claims 1 to 8, the collection area of the collection device extending from below the aircraft engine to below the liquid outlet portion.
10. An aircraft engine washing arrangement according to claim 9, characterised in that the axis of the aircraft engine coincides with the axis of the inlet portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121321107.8U CN215696661U (en) | 2021-06-11 | 2021-06-11 | Aeroengine washs waste liquid collecting system and washs structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121321107.8U CN215696661U (en) | 2021-06-11 | 2021-06-11 | Aeroengine washs waste liquid collecting system and washs structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215696661U true CN215696661U (en) | 2022-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121321107.8U Active CN215696661U (en) | 2021-06-11 | 2021-06-11 | Aeroengine washs waste liquid collecting system and washs structure |
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| CN (1) | CN215696661U (en) |
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- 2021-06-11 CN CN202121321107.8U patent/CN215696661U/en active Active
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