Aircraft engine cleaning equipment and aircraft engines

Abstract

This invention relates to an aircraft engine cleaning device and an aircraft engine. The aircraft engine cleaning device includes a flow divider ring (10) and a conveying device (20). The flow divider ring (10) is located at the junction of the inner bypass duct (60) and the outer bypass duct (70) of the engine. The flow divider ring (10) has a receiving cavity (11) and a spraying part (12). The conveying device (20) communicates with the receiving cavity (11), and the receiving cavity (11) communicates with the spraying part (12) to convey the cleaning medium to the receiving cavity (11) through the conveying device (20) and spray it to the position to be cleaned on the engine through the spraying part (12). The aircraft engine includes the aircraft engine cleaning device. This invention integrates the cleaning device at least partially into the engine, which can avoid engine damage due to tooling misuse or operational errors. The built-in spraying structure allows the cleaning medium to accurately reach the position to be cleaned, thereby greatly improving the cleaning efficiency of the aircraft engine.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine technology, and more particularly to an aircraft engine cleaning device and an aircraft engine. Background Technology

[0002] Commercial aircraft engines are typically turbofan engines. As flight hours increase, impurities accumulate in the engine's airflow channels, leading to a decline in performance. Therefore, regularly cleaning the engine's airflow channels can improve engine efficiency, reduce fuel consumption, and extend engine life. Since aircraft engines cannot be frequently disassembled, wing cleaning is particularly important.

[0003] In related technologies, a specialized water spray fixture needs to be installed before performing on-wing cleaning on an aircraft engine. Different engine models require different water spray fixtures due to differences in size and structure, which complicates maintenance. Furthermore, traditional water spray fixtures mainly come in two forms: one is a large fixture installed in front of the engine fan, which requires precise positioning and the water jets are difficult to penetrate the internal ducts, resulting in low cleaning efficiency; the other is a water pipe with a curved hook end (also known as a J-hook), installed at the first stage stator blade of the supercharger stage behind the engine fan. Installing this type of fixture requires opening the engine nacelle, and if a fixture for a different engine model is used incorrectly or is improperly installed, it can easily collide with the first stage stator blade of the supercharger stage, causing engine damage.

[0004] It should be noted that the information disclosed in the background section of this invention is intended only to enhance the understanding of the overall background of this invention, and should not be construed as an admission or in any way implying that such information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] This invention provides an aircraft engine cleaning device and an aircraft engine, which can improve the cleaning efficiency of aircraft engines and avoid engine damage caused by misuse of tooling or operational errors.

[0006] To achieve the above objectives, according to one aspect of the present invention, an aircraft engine cleaning apparatus is provided, comprising:

[0007] A flow divider ring, located at the junction of the engine's inner and outer bypass ducts, includes a receiving cavity and an injection section; and

[0008] Conveying device;

[0009] The conveying device is connected to the receiving cavity, and the receiving cavity is connected to the spraying part, so that the cleaning medium is conveyed to the receiving cavity through the conveying device and sprayed to the position of the engine to be cleaned through the spraying part.

[0010] In some embodiments, the injection section is connected to the inner channel.

[0011] In some embodiments, the injection portion is disposed on the wall of the flow divider ring near the inner channel.

[0012] In some embodiments, the outlet section of the jet is inclined toward the air inlet away from the inner duct.

[0013] In some embodiments, the receiving cavity is an annular structure, and the diversion ring is provided with multiple injection sections, which are distributed circumferentially along the receiving cavity.

[0014] In some embodiments, the flow divider ring is provided with a plurality of injection sections, wherein the outlet diameter of the upper injection section is larger than the outlet diameter of the lower injection section.

[0015] In some embodiments, the end face of the air inlet of the diverter ring away from the inner duct is provided with an inlet, which connects the conveying device and the receiving cavity to convey the cleaning medium into the receiving cavity through the inlet.

[0016] In some embodiments, the aircraft engine cleaning equipment further includes a support plate and an outer casing fixedly connected to the support plate, with a conveying device at least partially disposed within the support plate, and the outer casing having an interface communicating between the conveying device and the outside of the engine.

[0017] In some embodiments, the aircraft engine cleaning equipment also includes a seal that can be opened and closed at the interface.

[0018] According to another aspect of the present invention, an aircraft engine is provided, comprising the aforementioned aircraft engine cleaning equipment.

[0019] Based on the above technical solution, the present invention provides a structure for containing and spraying cleaning media in a flow divider ring inside the aero engine, and provides a conveying device to deliver the cleaning media to the engine, thereby at least partially embedding the cleaning equipment inside the engine. Compared with the traditional fully externally mounted water washing fixture, this invention can avoid engine damage caused by misuse of the fixture or operational errors. The built-in spray structure allows the cleaning media to accurately reach the cleaning position, thereby greatly improving the cleaning efficiency of the aero engine. Attached Figure Description

[0020] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0021] Figure 1 A schematic diagram of one embodiment of the aircraft engine cleaning equipment of the present invention is shown;

[0022] Figure 2 A partial cross-sectional view of the flow divider ring is shown in one embodiment of the aircraft engine cleaning device of the present invention.

[0023] In the diagram: 10, flow divider ring; 11, receiving cavity; 12, injection section; 13, inlet; 20, conveying device; 30, support plate; 40, outer casing; 50, interface; 60, inner duct; 70, outer bypass duct. Detailed Implementation

[0024] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0025] In the description of this invention, it should be understood that the terms "center," "lateral," "longitudinal," "front," "rear," "left," "right," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0026] As mentioned above, the water washing equipment used in related technologies for on-wing cleaning of aircraft engines has many drawbacks. Therefore, this invention provides an aircraft engine cleaning device.

[0027] like Figure 1 and Figure 2 As shown, in some embodiments, the aircraft engine cleaning equipment includes a flow divider ring 10 and a conveying device 20. The flow divider ring 10 is disposed at the junction of the inner duct 60 and the outer duct 70 of the engine. The flow divider ring 10 is provided with a receiving cavity 11 and a spraying part 12. The conveying device 20 is connected to the receiving cavity 11, and the receiving cavity 11 is connected to the spraying part 12, so as to convey the cleaning medium to the receiving cavity 11 through the conveying device 20 and spray it to the position of the engine to be cleaned through the spraying part 12.

[0028] like Figure 2As shown, by setting the receiving cavity 11 inside the flow divider ring 10 and setting the spray section 12 on the flow divider ring 10 that communicates with the receiving cavity 11, the structure of the flow divider ring 10 is fully utilized. That is, while setting part of the cleaning equipment inside the engine, it does not increase the space occupied by the internal structure of the engine. Therefore, this setting can effectively avoid the situation where the tooling collides with the first stage moving blade of the booster stage during the cleaning operation due to misuse or improper installation of the J-type hook tooling, which would damage the engine.

[0029] like Figure 2 As shown, the receiving cavity 11 is a chamber structure with a certain capacity, which can be used to store a certain amount of cleaning medium. During the cleaning operation, the cleaning medium enters the receiving cavity 11 through the conveying device 20, allowing the cleaning medium to be stored in the receiving cavity 11 to a certain amount, so as to make full use of the potential energy of the cleaning medium, ensuring a sufficiently large spray volume and a sufficiently strong spray effect. Then, the cleaning medium is sprayed to the position to be cleaned on the engine through the spraying part 12. This overcomes the disadvantage of external tooling spraying where the cleaning medium is difficult to accurately reach the position to be cleaned, thereby significantly improving the cleaning efficiency of the engine.

[0030] In some embodiments, the spray section 12 is connected to the inner channel 60, so that the cleaning medium can directly enter the inner channel 60 through the spray section 12, thereby achieving cleaning of the inner channel 60.

[0031] Furthermore, by changing the position of the spray nozzle 12, cleaning of other parts of the engine can also be achieved.

[0032] In addition, the spray section 12 can be a through hole connecting the receiving cavity 11 and the inner channel 60, or it can be a dedicated nozzle or spray head, depending on actual needs.

[0033] In some embodiments, the injection section 12 is disposed on the wall of the diversion ring 10 near the inner channel 60.

[0034] By directly placing the spray section 12 on the wall of the diversion ring 10 near the inner channel 60, the cleaning medium can directly reach the inner channel 60 from the receiving cavity 11 through the spray section 12, without the need for a separate pipeline for conveying the cleaning medium. This simplifies the structure of the cleaning equipment to the greatest extent while achieving efficient cleaning of the inner channel 60.

[0035] In some embodiments, the outlet section of the jet section 12 is inclined toward the air inlet away from the inner duct 60.

[0036] During the cleaning operation, the engine is in a cold running state. The airflow is drawn into the engine through the air inlet of the inner duct 60. The outlet section of the spray section 12 is tilted away from the air inlet of the inner duct 60, so that the angle between the spray direction of the cleaning medium and the flow direction of the intake airflow is an acute angle. The cleaning medium can be carried into the inner duct 60 along with the intake airflow, thereby increasing the movement speed of the cleaning medium, expanding the coverage area of ​​the cleaning medium, and thus achieving a more thorough cleaning of the inner duct 60.

[0037] In some embodiments, the receiving cavity 11 has an annular structure, and the diversion ring 10 is provided with a plurality of injection sections 12, which are distributed circumferentially along the receiving cavity 11.

[0038] Specifically, the receiving cavity 11 is configured as a ring structure similar in shape to the flow divider ring 10. This serves two purposes: first, to ensure the uniformity of the overall structure and avoid affecting the performance of the flow divider ring 10 itself, and to allow the cleaning medium to be evenly distributed along the circumference of the flow divider ring 10; second, to fully utilize the internal space of the flow divider ring 10, accommodating as much cleaning medium as possible to fully utilize the potential energy accumulated in the cleaning medium. Furthermore, by providing multiple injection sections 12 distributed circumferentially along the receiving cavity 11, circumferential injection of the cleaning medium can be achieved, resulting in a more uniform distribution of the cleaning medium in the engine air passage, thereby improving cleaning efficiency.

[0039] In some embodiments, the flow divider ring 10 is provided with a plurality of injection sections 12, wherein the outlet diameter of the upper injection section 12 is larger than the outlet diameter of the lower injection section 12.

[0040] Due to the influence of gravity, the cleaning medium is more easily ejected through the lower spray section 12. Therefore, by setting the outlet diameter of the upper spray section 12 to be larger than that of the lower spray section 12, it can be ensured that multiple spray sections 12 can uniformly spray the cleaning medium along the circumference of the engine air passage during cleaning operations.

[0041] In some embodiments, the end face of the air inlet of the diversion ring 10 away from the inner channel 60 is provided with an inlet 13, which connects the conveying device 20 and the receiving cavity 11 to convey the cleaning medium into the receiving cavity 11 through the inlet 13.

[0042] like Figure 2 As shown, the end face of the air inlet of the flow divider ring 10 away from the inner channel 60 is the non-working surface of the flow divider ring 10. Therefore, setting the inlet of the cleaning medium on this end face will not affect the working performance of the flow divider ring 10 itself.

[0043] In some embodiments, the aircraft engine cleaning equipment further includes a support plate 30 and an outer casing 40 fixedly connected to the support plate 30. The conveying device 20 is at least partially disposed within the support plate 30, and the outer casing 40 is provided with an interface 50 that connects the conveying device 20 to the outside of the engine.

[0044] The conveying device 20 may include a channel within the support plate 30 that connects the receiving cavity 11 of the diversion ring 10 to the external space of the engine. This channel may be integrated with the support plate 30. Such an arrangement can reduce the overall weight of the engine, help reduce flight load, and eliminate the need to install the conveying channel inside the engine during cleaning operations, thereby simplifying the cleaning process.

[0045] By placing the conveying device 20 inside the support plate 30, the conveying device 20 can be placed inside the engine without the need for additional installation structures, thus avoiding any impact on the working performance of the engine air passage. Furthermore, by providing an interface 50 on the outer casing 40 that connects the conveying device 20 to the outside of the engine, it is possible to deliver the cleaning medium into the engine without opening the engine nacelle during cleaning operations.

[0046] In some embodiments, the aircraft engine cleaning equipment also includes a seal that is closable at the interface 50.

[0047] A seal is used to open and close the interface 50. The seal can be a removable plug or an openable / closable valve. Before cleaning, the seal is opened or removed, and the interface 50 is connected to the work vehicle storing the cleaning medium to deliver the cleaning medium into the engine. After cleaning, the connection between the interface 50 and the work vehicle is disconnected, and the seal is closed or reinstalled into the interface 50 to seal the outer casing 40, thereby preventing backflow of airflow from the inner duct 60 through the injection section 12 on the flow divider ring 10 and avoiding any impact on engine operation.

[0048] The working process of one embodiment of the aircraft engine cleaning equipment of the present invention is described below:

[0049] like Figure 1 As shown, the aircraft engine cleaning equipment of the present invention includes a flow divider ring 10, a conveying device 20, a support plate 30, an outer casing 40, and an interface 50.

[0050] The flow divider ring 10 is located at the junction of the inner duct 60 and the outer duct 70 of the engine. The conveying device 20 is partially located inside the support plate 30. One end of the conveying device 20 is connected to the flow divider ring 10, and the other end is connected to the interface 50 on the outer casing 40. This enables the cleaning medium to enter the engine from the outside through the interface 50 and then enter the flow divider ring 10 through the conveying device 20.

[0051] Figure 2 A partial cross-sectional view of the flow divider ring 10 is shown. The outer diameter of the flow divider ring 10 gradually increases along the direction of engine intake, while the inner diameter of the flow divider ring 10 remains substantially constant along the direction of engine intake. (Refer to...) Figure 2 In the direction of the flow divider ring 10, the connection between its outer and inner surfaces is arc-shaped at the left end. The right end of the flow divider ring 10 has a surface perpendicular to its axis. The intake airflow of the engine flows from left to right, is separated by the left end of the flow divider ring 10, and then enters the outer bypass duct 70 and inner bypass duct 60 of the engine along the outer and inner surfaces of the flow divider ring 10, respectively. The flow divider ring 10 has a receiving cavity 11 inside, thus forming a hollow annular structure inside the flow divider ring 10. The wall surface of the flow divider ring 10 near the inner bypass duct 60 (i.e., the inner surface of the flow divider ring 10) is provided with an injection section 12. The right end face of the flow divider ring 10 is provided with an inlet 13. The conveying device 20 is connected to the receiving cavity 11, and the receiving cavity 11 is connected to the injection section 12.

[0052] Figure 2 The arrows in the diagram indicate the flow direction of the cleaning medium during the cleaning operation. The cleaning medium enters the receiving cavity 11 through the conveying device 20, and is then sprayed into the engine's internal passage 60 through the spraying part 12, thereby achieving the cleaning of the internal passage 60.

[0053] In this embodiment, the cleaning medium is water. Furthermore, the cleaning medium can be selected according to the actual situation, such as using an engine-specific cleaning agent or nanoparticles with cleaning properties.

[0054] When an aircraft engine undergoes a water washing operation, the engine is cold-running under the drive of the starter motor, such as... Figure 1 and Figure 2 As shown, the pressurized water enters the receiving cavity 11 through the conveying device 20, and is then sprayed into the engine's internal channel 60 from the spray section 12. The water flows towards the rear of the engine along with the air drawn in by the engine, carrying away the dirt in the internal channel 60. Finally, a portion of the wastewater flows out from the tail nozzle in streams, while another portion of the wastewater is sprayed out from the tail nozzle at a certain speed in the form of atomization from the rear of the engine.

[0055] Through the description of several embodiments of the aircraft engine cleaning equipment of the present invention, it can be seen that the aircraft engine cleaning equipment of the present invention has at least the following advantages:

[0056] (1) Compared with the large structure and size of the tooling installed in front of the engine fan, the aircraft engine cleaning equipment of the present invention occupies less space and has lower installation and positioning requirements. At the same time, it can ensure that the cleaning medium accurately reaches the position to be cleaned and has high cleaning efficiency.

[0057] (2) Compared with water pipes with curved hook ends (also known as J-hooks), the aircraft engine cleaning equipment of the present invention does not require opening the nacelle for installation, which simplifies the operation process and avoids the situation where the tooling is mistakenly used for other types of engines or improperly installed, causing the tooling to collide with the first stage moving blade of the booster stage and causing engine damage. In addition, the number of water pipe outlets of J-hooks is small, resulting in a small spray range of cleaning fluid and incomplete cleaning of the engine. However, the aircraft engine cleaning equipment of the present invention can achieve circumferential uniform spraying of the cleaning medium by setting multiple spray sections distributed along the circumference of the flow divider ring, thereby achieving thorough and efficient cleaning of the engine's internal channels.

[0058] In summary, compared with traditional aircraft engine water washing spray fixtures, this invention reduces the positioning accuracy requirements for the cleaning equipment installation by at least partially integrating the aircraft engine cleaning equipment into the engine, simplifies the aircraft engine cleaning process, improves the efficiency of the cleaning operation, and avoids engine damage caused by misuse of the fixture or operational errors. While improving engine cleaning efficiency, it also greatly reduces engine maintenance costs.

[0059] Based on the aforementioned aircraft engine cleaning equipment, this invention also proposes an aircraft engine that includes the aforementioned aircraft engine cleaning equipment. The positive technical effects of the aircraft engine cleaning equipment in the various embodiments described above are also applicable to aircraft engines, and will not be repeated here.

[0060] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the present invention or equivalent substitutions can still be made to some technical features without departing from the principle of the present invention, and such modifications and equivalent substitutions should all be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. An aircraft engine cleaning device, characterized in that, include: A flow divider ring (10) is disposed at the junction of the inner bypass duct (60) and the outer bypass duct (70) of the engine. The flow divider ring (10) is provided with a receiving cavity (11) and an injection section (12). Conveying device (20); The conveying device (20) is connected to the receiving cavity (11), and the receiving cavity (11) is connected to the spraying part (12) so as to convey the cleaning medium through the conveying device (20) into the receiving cavity (11) and spray it through the spraying part (12) to the position of the engine to be cleaned.

2. The aircraft engine cleaning equipment according to claim 1, characterized in that, The injection section (12) is connected to the inner channel (60).

3. The aircraft engine cleaning equipment according to claim 1, characterized in that, The injection section (12) is disposed on the wall of the diversion ring (10) near the inner channel (60).

4. The aircraft engine cleaning equipment according to claim 1, characterized in that, The outlet section of the jet (12) is inclined toward the air inlet away from the inner channel (60).

5. The aircraft engine cleaning equipment according to claim 1, characterized in that, The receiving cavity (11) has an annular structure, and the diversion ring (10) is provided with a plurality of the injection parts (12), which are distributed circumferentially along the receiving cavity (11).

6. The aircraft engine cleaning equipment according to claim 1, characterized in that, The flow divider ring (10) is provided with a plurality of the injection sections (12), and the outlet diameter of the upper injection section (12) is larger than the outlet diameter of the lower injection section (12).

7. The aircraft engine cleaning equipment according to claim 1, characterized in that, The end face of the diversion ring (10) away from the air inlet of the inner channel (60) is provided with an inlet (13), the inlet (13) connecting the conveying device (20) and the receiving cavity (11) to convey the cleaning medium into the receiving cavity (11) through the inlet (13).

8. The aircraft engine cleaning equipment according to claim 1, characterized in that, It also includes a support plate (30) and an outer casing (40) fixedly connected to the support plate (30). The conveying device (20) is at least partially disposed within the support plate (30). The outer casing (40) is provided with an interface (50) connecting the conveying device (20) to the outside of the engine.

9. The aircraft engine cleaning equipment according to claim 8, characterized in that, It also includes a seal that is closable at the interface (50).

10. An aircraft engine, characterized in that, Includes the aircraft engine cleaning equipment as described in any one of claims 1 to 9.

Images