Marine recovery aircraft engine cleaning equipment

Abstract

The present invention relates to the technical field of cleaning devices, and in particular to a marine recovery aircraft engine cleaning device, comprising a water tank, a first induction device, a second induction device and a diversion adapter section, wherein the first induction device and the second induction device are both used to induce liquid flow. In view of the technical problem that the prior art cannot effectively clean the interior and exterior of the entire engine at the same time, the present invention provides a marine recovery aircraft engine cleaning device, which uses a water tank to immerse the entire aircraft engine in liquid, and through the arrangement of the first induction device, the second induction device, the diversion adapter section and the water tank and other structures, the liquid flow in the water tank can be guided, thereby achieving full cleaning of the interior and exterior of the aircraft engine.

Description

Technical Field

[0001] The invention relates to the technical field of cleaning devices, and in particular to a cleaning device for marine recovered aircraft engines. Background Art

[0002] With the continuous development of drone technology, the application of drones is becoming more and more extensive. For example, in the military field, unmanned target aircraft suitable for low-altitude and high-speed flight are needed for training missions. Generally speaking, the target aircraft will fall directly into the seawater for recovery. However, since the air intake and tail nozzle of the aircraft engine are connected to the outside atmosphere, it is impossible to make a sealing design. When recovering in the ocean, it is inevitable to be immersed in seawater. Various salts and microorganisms in seawater will corrode engine parts. If they are not cleaned in time, the entire engine will be scrapped.

[0003] In the prior art, there is equipment for cleaning aircraft engines after flying or storing at the seaside. The main method is to clean the engine blades by spraying a solution with a nozzle, with the purpose of dealing with the corrosion of the engine blades by the salt in the air environment. However, the air environment has less salt, and the remaining salt on the aircraft engine is relatively less corrosive to other parts except the blades, so it is generally not cleaned, and the nozzle spray method cannot fully clean the remaining salt in the engine flow path. Obviously, this method is not suitable for cleaning the entire engine after it is immersed in seawater, and it is impossible to effectively clean the entire engine. The remaining salt will seriously corrode the inside of the engine, resulting in a significant reduction in the life of the engine. However, if the aircraft engine is completely disassembled before cleaning, it will be time-consuming and laborious. Summary of the invention

[0004] In view of the technical problem that the prior art cannot effectively clean the inside and outside of the entire engine at the same time, the present invention provides an ocean-recovered aircraft engine cleaning device, which utilizes a water tank to immerse the entire aircraft engine in liquid, and through the arrangement of a first actuating device, a second actuating device, a flow guide adapter section, a water tank and other structures, it can guide the flow of liquid in the water tank, thereby achieving sufficient cleaning of the inside and outside of the aircraft engine.

[0005] The technical solution provided by the present invention is: an ocean recovery aircraft engine cleaning equipment, comprising a water tank, a first induction device, a second induction device and a diversion transition section, wherein the first induction device and the second induction device are both used to induce liquid flow; the water tank is divided into a first zone, a second zone and a third zone by planes A1 and A2 perpendicular to the bottom surface, the first zone and the third zone gradually converge toward the second zone, so that the water tank forms a structure that gradually narrows from both ends to the middle, and the volume of the first zone is smaller than the volume of the third zone; an engine bracket is arranged in the second zone, the first induction device is arranged in the first zone, the second induction device is arranged in the third zone, the first induction device and the engine bracket are arranged in the first zone, and the second induction device is arranged in the third zone. Both are located on the center line C1, the second actuating device is symmetrically arranged with the center line C1 of the water tank as the symmetry axis, and the water outlet of the second actuating device is toward between the engine bracket and the inner wall of the water tank; the flow guide transition section is a hollow tube body, the inlet of the flow guide transition section is tightly connected with the outlet of the first actuating device, the outlet of the flow guide transition section is used to connect with the air inlet of the aircraft engine, the inner wall of the flow guide transition section is streamlined, and the inner diameter of the flow guide transition section gradually increases from the inlet to the outlet, and a spiral groove is arranged on the inner wall of the flow guide transition section, the spiral groove gradually twists from the inlet to the outlet, and the twisting direction of the spiral groove is consistent with the rotation direction of the rotor blade of the aircraft engine.

[0006] Optionally, a center line C2 of each of the second actuating devices in the third zone is parallel to a tangent line T1 of an inner wall of an adjacent water tank.

[0007] Optionally, an angle β between a center line C2 of each of the second actuating devices in the third zone and a center line C1 of the water tank is 15-30°.

[0008] Optionally, 16 to 20 spiral grooves are evenly arranged along the circumferential direction in the flow guide transition section, and the depth of the spiral grooves is 15 to 20 mm.

[0009] Optionally, the outer wall of the diversion section is streamlined, and the diameter of the outer wall of the diversion section gradually increases from the inlet to the outlet, and the tangent T2 of the outer wall of the diversion section near the outlet points between the engine bracket and the inner wall of the water tank.

[0010] Optionally, a width D1 of an end portion of the water tank located in the first zone is smaller than a width D2 of an end portion of the water tank located in the third zone, and a length L1 of the first zone is smaller than a length L2 of the third zone.

[0011] Optionally, a guide platform is fixedly provided near the end of the third zone, and the cross-sectional width of the guide platform gradually increases from the first zone to the third zone. The outer walls on both sides of the guide platform have the same contour shape as the inner walls on both sides of the corresponding water tank.

[0012] Optionally, a first track is provided in the first zone, a third track is provided in the third zone, the trajectory of the third track is consistent with the inner wall contour of the adjacent water tank, load-bearing brackets are movably provided on the first track and the third track, the first actuating device and the second actuating device are respectively fixed on the load-bearing brackets in the first zone and the third zone, a second track is provided at the bottom of the water tank, and the engine bracket is movably provided on the second track.

[0013] Optionally, the first driving device and the second driving device are submersible mixers.

[0014] Optionally, it also includes a distilled water channel, a solvent filling channel and a sewage treatment device, the distilled water channel and the solvent filling channel are both connected to the water inlet of the water tank, the water outlet of the water tank is connected to the inlet of the sewage treatment device; the water inlet height of the water tank is lower than the water outlet height of the water tank. Beneficial Effects

[0015] The technical solution provided by the present invention has the following beneficial effects compared with the prior art: in order to address the technical problem that the prior art cannot effectively clean the inside and outside of the entire engine at the same time, the present invention utilizes a water tank to immerse the entire aircraft engine in liquid, and through the arrangement of the first actuating device, the second actuating device, the flow guide adapter section, the water tank and other structures, the flow of liquid in the water tank can be guided, thereby achieving sufficient cleaning of the inside and outside of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the structure of the marine recovery aircraft engine cleaning equipment proposed in an embodiment of the present invention.

[0017] Figure 2 This is a schematic diagram of the structure of a water tank proposed in an embodiment of the present invention.

[0018] Figure 3 This is a schematic diagram of the structure of the flow guide transition section proposed in an embodiment of the present invention.

[0019] Figure 4 This is a schematic cross-sectional structural diagram of the flow guide transition section proposed in an embodiment of the present invention.

[0020] Figure 5 This is a schematic cross-sectional view of the structure of an ocean recovery aircraft engine cleaning device proposed in an embodiment of the present invention.

[0021] Figure 6 This is a schematic diagram of an implementation of the marine recovery aircraft engine cleaning equipment proposed in an embodiment of the present invention. DETAILED DESCRIPTION

[0022] In order to further understand the content of the present invention, the present invention is described in detail in conjunction with the accompanying drawings and embodiments.

[0023] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It is understood that the specific embodiments described herein are only used to explain the relevant inventions, rather than to limit the invention. It should also be noted that, for the convenience of description, only the parts related to the invention are shown in the accompanying drawings. The words "first", "second", etc. described in the present invention are set for the convenience of describing the technical solution of the present invention, and have no specific limiting effect. They are all general references and do not constitute a limiting effect on the technical solution of the present invention. It should be noted that, in the absence of conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. In the description of the present invention, it should be noted that the orientation or position relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. is based on the orientation or position relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. Unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be a connection between the insides of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. Multiple technical solutions in the same embodiment, and multiple technical solutions in different embodiments, can be arranged and combined to form new technical solutions without contradictions or conflicts, all of which are within the scope of protection required by the present invention.

[0024] Combined with Figure 1-6 This embodiment proposes a marine recovery aircraft engine cleaning device, including a water tank 10, a first induction device 11, a second induction device 12 and a diversion adapter section 13. Among them, the first induction device 11 and the second induction device 12 are both used to induce liquid flow. In this embodiment, the first induction device 11 and the second induction device 12 preferably use a submersible agitator. Optionally, in other embodiments, other types of pump bodies and other equipment can also be used.

[0025] The water tank 10 in this embodiment is divided into a first area 101, a second area 102 and a third area 103 by planes A1 and A2 perpendicular to the bottom surface. The first area 101 and the third area 103 gradually converge toward the second area 102, so that the water tank 10 has a structure that gradually narrows from both ends to the middle, and the volume of the first area 101 is smaller than the volume of the third area 103.

[0026] The engine bracket 25 is arranged in the second zone 102, the first priming device 11 is arranged in the first zone 101, and the second priming device 12 is arranged in the third zone 103. Further, the first priming device 11 and the engine bracket 25 are both located on the center line C1, the second priming device 12 is symmetrically arranged with the center line C1 of the water tank 10 as the symmetry axis, and the water outlet of the second priming device 12 faces between the engine bracket 25 and the inner wall of the water tank 10. In this embodiment, one first priming device 11 is arranged in the second zone 102, and two second priming devices 12 are arranged in the third zone 103.

[0027] In addition, the inlet of the flow guide transition section 13 is tightly connected with the outlet of the first driving device 11, and the outlet of the flow guide transition section 13 is used to connect with the engine air intake duct. The inner wall of the flow guide transition section 13 is streamlined, and the inner diameter of the flow guide transition section 13 gradually increases from the inlet to the outlet. A spiral groove 130 is provided on the inner wall of the flow guide transition section 13, and the spiral groove 130 gradually twists from the inlet to the outlet, and the twisting direction of the spiral groove 130 is consistent with the rotation direction of the rotor blade of the aircraft engine.

[0028] Based on the above structural description, the basic working principle of the marine recovery aircraft engine cleaning equipment of this embodiment is: distilled water or cleaning solvent is poured into the water tank 10, the aircraft engine is loaded on the engine bracket 25, the entire engine is immersed in the liquid in the water tank 10, and the first actuating device 11 and the second actuating device 12 are driven, that is, the submersible agitator is driven, so that the liquid in the water tank 10 is driven to flow, so as to fully clean the inside and outside of the aircraft engine.

[0029] Among them, the outlet of the first starting device 11 is connected to the guide adapter section 13, which is a hollow tube body, one end of which is connected to the outlet of the first starting device 11, for example, by a socket or abutment form, and the other end of the guide adapter section 13 is connected to the inlet of the aircraft engine, which can also be connected in the form of a socket or abutment.

[0030] The inner wall of the flow guide adapter section 13 is streamlined, which is conducive to the flow of liquid. The liquid flowing into the flow guide adapter section 13 will pass through the spiral groove 130, and the spiral groove 130 will gradually twist from the inlet to the outlet. It can be understood that the rotation direction of the rotor blades of the aircraft engine conforms to the heading, so the twisting rotation direction of the spiral groove 130 also needs to adapt to the direction of the channel. Generally speaking, the rotation direction of the spiral groove 130 twists clockwise along the heading. Thus, the spiral groove 130 can guide the liquid and achieve a pre-rotation effect. After the pre-rotated liquid enters the intake duct of the aircraft engine, it will drive the engine rotor to rotate. The setting of the spiral groove 130, on the one hand, ensures the circumferential uniformity of the fluid flow, and on the other hand, realizes the pre-rotation of the fluid, thereby reducing the concentrated impact on the engine rotor blades and reducing the possibility of damage to the rotor blades. In addition, in terms of cleaning effect, the pre-swirled liquid will further change its state after flowing through the rotor blades, such as slowing down or changing the flow direction due to driving the rotor blades, thereby further stirring the liquid in the flow channel, thereby fully cleaning the stains and salt stains remaining in the flow channel of the aircraft engine.

[0031] In addition, the inner diameter of the flow guide transition section 13 of the present embodiment gradually increases from the inlet to the outlet, which can gradually reduce the pressure and speed of the liquid in the process of flowing along the flow guide transition section 13. Obviously, the impact force of the liquid at the output end of the first actuator 11 will be relatively large, but the change in the inner diameter of the flow guide transition section 13 can make the impact force relatively reduced when the liquid contacts the rotor blades, thereby further reducing the concentrated impact on the engine rotor blades and reducing the possibility of damage to the rotor blades.

[0032] In a more preferred embodiment, there are 16 to 20 spiral grooves 130 evenly arranged along the circumference in the flow guide adapter section 13, and the depth of the spiral grooves 130 is 15 to 20 mm. If the number of spiral grooves 130 is too large, or the depth is too deep, it is easy to cause a large loss of kinetic energy of the liquid, which may affect the cleaning effect; if the number of spiral grooves 130 is too small or the depth is too shallow, it may not be possible to produce appropriate pre-swirl, and it may cause the impact force on the rotor blades to be too large. In short, this preferred setting method can better ensure the circumferential uniformity of fluid flow, form appropriate pre-swirl, reduce concentrated impact on the engine rotor blades, and reduce the possibility of damage to the rotor blades.

[0033] In addition, in another preferred embodiment, the outer wall of the diversion adapter section 13 is streamlined, and the outer wall diameter of the diversion adapter section 13 gradually increases from the inlet to the outlet, and the tangent T2 of the outer wall of the diversion adapter section 13 near the outlet points to between the engine bracket 25 and the inner wall of the water tank 10. Obviously, during the cleaning process, there will also be liquid flowing from the first area 101 to the third area 103 on the outer wall of the diversion adapter section 13, and this embodiment can guide the liquid flowing through the outer wall of the diversion adapter section 13, and the streamlined outer wall shape can reduce the kinetic energy loss of the liquid. Specifically, the tangent T2 of the outer wall of the diversion adapter section 13 near the outlet points to between the engine bracket 25 and the inner wall of the water tank 10, which can make the liquid flow through the outer wall of the diversion adapter section 13 intersect with the liquid flow generated by the second actuating device 12, thereby generating turbulence on the outside of the diversion adapter section 13, thereby further ensuring the cleaning effect.

[0034] For the liquid flowing through the interior of the aircraft engine, the amount of ocean salt or ocean impurities that are miscible with the liquid gradually increases along the direction of the liquid flow. Therefore, in the initial stage of cleaning, the concentration of ocean salt or ocean impurities at the outlet of the aircraft engine is much higher than that in other areas of the water tank 10. Due to the decrease in concentration difference, the cleaning effect near the outlet of the aircraft engine will be temporarily reduced. Although this situation only exists temporarily, due to the uncertainty of seawater impurities, impurities with low solubility may continue to adhere to the engine, and some insoluble solid impurities such as gravel and marine organisms may gather into agglomerates with the liquid flow, and will continue to move in the water tank 10 with the liquid flow, which may further damage the interior or exterior of the engine. Based on this, the second actuating device 12 in this embodiment can further overcome this defect.

[0035] The second priming device 12 in this embodiment will work synchronously with the first priming device 11 to fully stir the liquid flowing out of the aircraft engine outlet, so that it is fully mixed with the liquid in other areas of the water tank 10, and the local concentration at the aircraft engine outlet is reduced. At the same time, the water flow at the aircraft engine outlet will change sharply, thereby dispersing the impurities that have gathered into a mass, and preventing the impurities from further damaging the engine.

[0036] In addition, it can be understood that, since the water outlet of the second actuating device 12 of this embodiment is toward the space between the engine bracket 25 and the inner wall of the water tank 10, the second actuating device 12 of this embodiment can further drive the liquid in the water tank 10 to evenly wash the outer surface of the aircraft engine. And since the second actuating device 12 of this embodiment is symmetrically arranged with the center line C1 of the water tank 10 as the symmetry axis, it can ensure that the aircraft engine is evenly stressed when being washed by water flow, avoiding damage caused by unilateral stress.

[0037] In a preferred embodiment, the center line C2 of each second priming device 12 in the third zone 103 is parallel to the inner wall tangent T1 of the adjacent water tank 10. In combination with the aforementioned embodiment, since the inner wall of the water tank 10 is streamlined, its inner wall is generally composed of a curved surface, and the liquid in the water tank 10 will flow along the curved surface. In this embodiment, the second priming device 12 is set to be parallel to the inner wall tangent T1 of the adjacent water tank 10, which can guide the flow direction of the liquid, so that the outlet water flow of the second priming device 12 can flow along the inner wall of the water tank 10, thereby ensuring that the liquid flows to the outer wall of the aircraft engine, thereby achieving the cleaning of the outer wall of the aircraft engine.

[0038] And, in another preferred embodiment, the angle β between the center line C2 of each second priming device 12 in the third zone 103 and the center line C1 of the water tank 10 is 15-30°. In this case, the functionality of the second priming device 12 can be better realized, and the outlet flow directions of the second priming devices 12 in this embodiment will form a cross, so as to better realize the flushing of the outer shell of the aircraft engine.

[0039] In this embodiment, the aircraft engine is fixed in the second area 102 in the middle of the water tank 10, the first priming device 11 is arranged in the first area 101, the second priming device 12 is arranged in the third area 103, and the output end of the first priming device 11 of the second priming device 12, or the driving direction of the water flow, is opposite, thereby promoting the circulation of the liquid in the water tank 10. It can be imagined that the circulation of the liquid can be an internal circulation existing only in the water tank 10, or it can be connected to the outside to form other forms of flow paths.

[0040] For example, in one embodiment, it also includes a distilled water channel 30, a solvent filling channel 31 and a sewage treatment device 32, and the distilled water channel 30 and the solvent filling channel 31 are connected to the water inlet of the water tank 10, and the water outlet of the water tank 10 is connected to the inlet of the sewage treatment device 32. In this case, the sewage in the water tank 10 will flow to the sewage treatment device 32 and be purified, and at the same time, distilled water or cleaning solvent will continue to flow into the water tank 10, thereby ensuring that there is always a clean liquid source in the water tank 10 to improve the cleaning effect. In a further optimized form, the height of the water inlet of the water tank 10 should be lower than the height of the water outlet of the water tank 10, so that the flow direction of the clean liquid can fully pass through the entire aircraft engine. In addition, it is conceivable that the sewage treatment device 32 can be selected as a filtering distillation device, and the distilled water formed after the distillation device is treated can be returned to the water tank 10 and reused to save water resources.

[0041] The water tank 10 of this embodiment is divided into a first area 101, a second area 102 and a third area 103 by planes A1 and A2 perpendicular to the bottom surface. The first area 101 and the third area 103 gradually converge toward the second area 102, so that the water tank 10 forms a structure that gradually narrows from both ends to the middle. The volume of the first area 101 is smaller than that of the third area 103. The inner wall of the water tank 10 of this embodiment can be preferably as shown in the attached figure. Figure 1 , 2 The streamlined structure shown in FIG. 6 can improve the fluidity of the liquid, thereby ensuring the cleaning effect. Also, since the first area 101 and the third area 103 of the water tank 10 gradually converge toward the second area 102, the flow rate or pressure of the liquid flowing through the outside of the aircraft engine will change significantly, thereby increasing the impact force of the liquid flow on the outside of the aircraft engine, thereby further improving the cleaning effect on the outside of the aircraft engine. Among them, planes A1 and A2 can generally be regarded as the front and rear end surfaces of the engine.

[0042] The structural arrangement of the water tank 10 of this embodiment can increase the flow rate or pressure of the liquid flowing through the outer surface of the aircraft engine (depending on the circulation mode of the liquid) for the second zone 102, thereby improving the cleaning effect on the outer surface of the aircraft engine.

[0043] As for the third zone 103, the larger volume can more conveniently adapt to the setting of the second activating device 12 on the one hand, and on the other hand, it will form a dynamic pressure difference or flow rate difference between the first zone 101 and the third zone 103, thereby improving the mixing effect. The mixing effect here can be understood as the mixing of impurities such as salt mentioned above, and can also be understood as the mixing when distilled water and cleaning solvent are added simultaneously. And, this pressure difference or flow rate difference can obviously improve the flushing effect of the liquid in the water tank 10 on the aircraft engine, thereby fully cleaning the aircraft engine.

[0044] The difference in volume between the first area 101 and the third area 103 is achieved by controlling and changing the structure of the water tank 10. In one embodiment, the width D1 of the end of the water tank 10 located in the first area 101 is smaller than the width D2 of the end of the water tank 10 located in the third area 103, and the length L1 of the first area 101 is smaller than the length L2 of the third area 103. Thus, when the height of the water tank 10 remains unchanged, the volume of the first area 101 can be ensured to be smaller than that of the third area 103.

[0045] In other embodiments, a guide platform 14 is fixedly provided near the end in the third zone 103, and the cross-sectional width of the guide platform 14 gradually increases from the first zone 101 to the third zone 103, and the outer walls on both sides of the guide platform 14 are consistent with the contour shapes of the inner walls on both sides of the corresponding water tank 10. The setting of the guide platform 14 in this embodiment is mainly used to guide the liquid to flow to the second priming device 12, or to guide the liquid to flow to the inner wall of the water tank 10, thereby changing the direction of the water flow and ensuring that the water flow can flow toward the direction of the aircraft engine. Among them, the outer walls on both sides of the guide platform 14 are consistent with the contour shapes of the inner walls on both sides of the corresponding water tank 10, so that the flow path size between the outer wall of the guide platform 14 and the adjacent inner wall of the water tank 10 does not change, reducing the turbulence of the liquid, so that the second priming device 12 can be in a relatively good liquid environment condition, thereby ensuring the use effect and improving the service life.

[0046] In addition, since there are many types of aircraft engines with different sizes, in order to improve the practicality of the device, in one embodiment, a first track 21 is provided in the first area 101, a third track 23 is provided in the third area 103, the track of the third track 23 is consistent with the inner wall profile of the adjacent water tank 10, a bearing bracket 24 is movably provided on the first track 21 and the third track 23, the first motive device 11 and the second motive device 12 are respectively fixed on the bearing bracket 24 in the first area 101 and the third area 103, a second track 22 is provided at the bottom of the water tank 10, and an engine bracket 25 is movably provided on the second track 22. Therefore, the distance between the first motive device 11 and the engine can be adjusted through the first track 21 and the second track 22, so as to provide installation space for a suitable diversion adapter section 13. The trajectory of the third track 23 in this embodiment is consistent with the inner wall contour of the adjacent water tank 10. Compared with the linear track, this embodiment can ensure that the second actuating device 12 mounted thereon has a longer movable stroke, and can ensure that the output port of the second actuating device 12 is always facing the appropriate position, so that the liquid flow triggered by the second actuating device 12 can flow along the inner wall of the water tank 10 to the outside of the engine.

[0047] Based on all the above embodiments, it can be known that the marine recovery aircraft engine cleaning equipment cleans the aircraft engine by controlling the flow of liquid in the water tank 10. Specifically, through the structural design of the water tank 10, the layout design of the first actuating device 11 and the second actuating device 12, the structural design of the diversion adapter section 13 and the structural design of the diversion platform 14, etc., the liquid flowing through the inner and outer areas of the aircraft engine can produce an impact on the aircraft engine, and the liquid flow away from the aircraft engine can be fully rectified and combed to avoid kinetic energy loss of the liquid flow, and also avoid excessive turbulence of the liquid flow in the water tank 10 that cannot be efficiently cleaned.

[0048] In summary, in order to address the technical problem that the prior art cannot effectively clean the inside and outside of the entire engine at the same time, the marine recovery aircraft engine cleaning equipment of this embodiment uses a water tank 10 to immerse the entire aircraft engine in liquid, and through the arrangement of the first actuating device 11, the second actuating device 12, the guide adapter section 13 and the water tank 10 and other structures, it is possible to guide the flow of liquid in the water tank 10, thereby achieving sufficient cleaning of the inside and outside of the aircraft engine.

[0049] The present invention and its embodiments are described schematically above, which is not restrictive. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. Therefore, if a person skilled in the art is inspired by it and creatively designs a structure and an embodiment similar to the technical solution without departing from the purpose of the invention, they shall all fall within the protection scope of the present invention.

Claims

1. A marine recovery aircraft engine cleaning equipment, characterized in that: It comprises a water tank (10), a first inducing device (11), a second inducing device (12) and a flow-guiding transition section (13), wherein the first inducing device (11) and the second inducing device (12) are both used to induce liquid flow; The water tank (10) is divided into a first area (101), a second area (102) and a third area (103) by planes A1 and A2 perpendicular to the bottom surface; the first area (101) and the third area (103) gradually converge toward the second area (102), so that the water tank (10) forms a structure that gradually narrows from both ends to the middle; the volume of the first area (101) is smaller than the volume of the third area (103); An engine bracket (25) is arranged in the second area (102), the first actuating device (11) is arranged in the first area (101), the second actuating device (12) is arranged in the third area (103), the first actuating device (11) and the engine bracket (25) are both located on a center line C1, the second actuating device (12) is symmetrically arranged with the center line C1 of the water tank (10) as a symmetry axis, and a water outlet of the second actuating device (12) faces between the engine bracket (25) and the inner wall of the water tank (10); The flow guide adapter section (13) is a hollow tube body, the inlet of the flow guide adapter section (13) is tightly connected to the outlet of the first driving device (11), the outlet of the flow guide adapter section (13) is used to connect to the air intake of the aircraft engine, the inner wall of the flow guide adapter section (13) is streamlined, and the inner diameter of the flow guide adapter section (13) gradually increases from the inlet to the outlet, and a spiral groove (130) is provided on the inner wall of the flow guide adapter section (13), the spiral groove (130) gradually twists from the inlet to the outlet, and the twisting direction of the spiral groove (130) is consistent with the rotation direction of the rotor blade of the aircraft engine.

2. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: The center line C2 of each of the second actuating devices (12) in the third zone (103) is parallel to the tangent line T1 of the inner wall of the adjacent water tank (10).

3. The marine recovery aircraft engine cleaning equipment according to claim 1 or 2, characterized in that: The angle β between the center line C2 of each of the second actuating devices (12) in the third zone (103) and the center line C1 of the water tank (10) is 15-30 degrees.

4. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: There are 16 to 20 spiral grooves (130) evenly arranged along the circumferential direction in the flow guide transition section (13), and the depth of the spiral grooves (130) is 15 to 20 mm.

5. The marine recovery aircraft engine cleaning equipment according to claim 1 or 4, characterized in that: The outer wall of the flow guiding transition section (13) is streamlined, and the diameter of the outer wall of the flow guiding transition section (13) gradually increases from the inlet to the outlet, and a tangent line T2 of the outer wall of the flow guiding transition section (13) near the outlet points to between the engine bracket (25) and the inner wall of the water tank (10).

6. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: The width D1 of the end of the water tank (10) located in the first zone (101) is smaller than the width D2 of the end of the water tank (10) located in the third zone (103), and the length L1 of the first zone (101) is smaller than the length L2 of the third zone (103).

7. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: A guide platform (14) is fixedly arranged near the end of the third zone (103); the cross-sectional width of the guide platform (14) gradually increases from the first zone (101) to the third zone (103); and the outer walls on both sides of the guide platform (14) have the same contour shape as the inner walls on both sides of the corresponding water tank (10).

8. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: A first track (21) is arranged in the first area (101), a third track (23) is arranged in the third area (103), the track of the third track (23) is consistent with the inner wall contour of the adjacent water tank (10), a bearing bracket (24) is movably arranged on the first track (21) and the third track (23), the first actuating device (11) and the second actuating device (12) are respectively fixed on the bearing bracket (24) in the first area (101) and the third area (103), a second track (22) is arranged at the bottom of the water tank (10), and the engine bracket (25) is movably arranged on the second track (22).

9. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: The first actuating device (11) and the second actuating device (12) are submersible mixers.

10. The marine recovery aircraft engine cleaning equipment according to claim 1, characterized in that: It also comprises a distilled water channel (30), a solvent filling channel (31) and a sewage treatment device (32); the distilled water channel (30) and the solvent filling channel (31) are both connected to the water inlet of the water tank (10); the water outlet of the water tank (10) is connected to the inlet of the sewage treatment device (32); the height of the water inlet of the water tank (10) is lower than the height of the water outlet of the water tank (10).

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