Aircraft engine runner cleaning device and method

Abstract

The invention discloses an aero-engine runner cleaning device and method.The cleaning device comprises a profiling supporting structure, a universal bearing, a water pipe and a support, the profiling supporting structure is installed at the lip position of an air inlet of an engine, the universal bearing is installed on the profiling supporting structure, one end of the water pipe penetrates through the universal bearing and is connected with a spray head, and the other end of the water pipe is connected with the support; and the bracket is arranged on the water pipe between the spray head and the universal bearing. When the cleaning device is used for cleaning the engine flow channel, the part including the spray head, the water pipe and the support extends into the engine air inlet channel, the profiling supporting structure is placed at an inlet of the engine air inlet channel, then the profiling supporting structure is fixed to the lip opening, and the engine flow channel can be cleaned after a water source is connected. The purpose of cleaning the flow channel of the engine in situ is achieved, part of performance of the engine can be rapidly recovered, operation is easy, and efficiency is high.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine service and support, and relates to a device and a cleaning method for cleaning a flow channel of an aircraft engine. Background Art

[0002] During the use of aircraft engines, thrust loss was found, which affected the flight range. Analysis showed that the contaminant particles adhered to the blade surface during use, resulting in reduced compressor efficiency and thrust. If the engine is disassembled, it will not only be time-consuming and labor-intensive, but also time-consuming.

[0003] Based on the above reasons, it is necessary to study an in-situ engine flow channel cleaning device and implementation method to realize engine flow channel cleaning, achieve the purpose of in-situ engine flow channel cleaning, and quickly restore engine performance loss. Summary of the invention

[0004] The present invention aims to provide an aircraft engine flow channel cleaning device and method, which can realize the engine on-wing flow channel cleaning and achieve the purpose of in-situ engine flow channel cleaning. It can not only quickly restore part of the engine performance, but also is simple to operate and highly efficient.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] An aircraft engine flow channel cleaning device, comprising:

[0007] A contoured support structure, wherein the contoured support structure comprises a support body, from which at least three support legs extend, a space is formed between the support legs and the support body that can accommodate the outer contour of the engine inlet lip, a through hole is formed on the support body, and through grooves are formed at the ends of the support legs;

[0008] A universal bearing, the universal bearing being installed in a through hole of the support body;

[0009] A water pipe, wherein the water pipe passes through the inner hole of the universal bearing, and one end of the water pipe is connected to the spray head, and the other end is connected to the water source;

[0010] The bracket is installed on the water pipe and is located between the spray head and the contoured support structure.

[0011] Furthermore, the support foot includes two sections, one section points from the engine air inlet lip to the center of the engine air inlet, and the other section extends from the engine air inlet lip close to the air inlet outer skin and is provided with a through groove that cooperates with the screws on the outer skin.

[0012] Furthermore, the contoured support structure is made of plastic.

[0013] Furthermore, the aircraft engine flow channel cleaning device also includes a gland, which is a hollow tube with a flange. The gland is installed in the through hole of the support body through its own flange, and the universal bearing is installed in the inner cavity of the gland.

[0014] Furthermore, the water pipe is formed by splicing multiple sections of pipes, wherein the pipe connected to the nozzle is curved, and the remaining pipes are straight pipes.

[0015] Furthermore, the pipelines are connected to each other via adapter nuts (threaded joints) and quick-plug joints.

[0016] Furthermore, the bracket is V-shaped, the apex of which is connected to the water pipe through a bracket flange, and handle balls are installed at its two ends.

[0017] A method for cleaning a flow passage of an aircraft engine, using the aforementioned flow passage cleaning device, and comprising the following steps:

[0018] S1, extending the flow channel cleaning device including the nozzle, the water pipe and the bracket into the engine intake channel, and placing the contoured support structure at the entrance of the engine intake channel;

[0019] S2, move the contoured support structure so that all the support feet are moved to the position with screws on the outer skin of the engine air inlet duct, remove the screws, align the notches of the support feet with the screw holes, and then re-install the screws to fix all the support feet to the outer skin of the engine air inlet duct;

[0020] S3, connect the water source to the water pipe at the universal bearing, and turn on the water source to clean the engine flow channel.

[0021] Furthermore, in S1, the nozzle is at least 150 mm away from the fairing cap and at least 250 mm away from the compressor blades.

[0022] Furthermore, the aircraft engine flow channel cleaning method also includes:

[0023] A sump for collecting cleaning waste water is installed at the interface between the engine air intake and the engine;

[0024] Open the engine outer skin and waterproof the generator;

[0025] Install a drainage pipe at the engine exhaust valve to drain the cleaning waste water.

[0026] The cleaning device of the present invention is relatively simple, easy to process, and convenient to operate in situ (without disassembling the engine). The cleaning device of the present invention and the cleaning method can fully achieve the cleaning effect of the traditional engine flow channel cleaning method. Through actual tests and simulation verification, the cleaning method of the present invention meets the requirements for engine performance recovery after repair. The cleaning method and device of the present invention have good application prospects and economic benefits.

[0027] Compared with the prior art, the present invention has the following characteristics:

[0028] (1) The contoured support structure makes full use of the screws on the outer skin of the air inlet, and can firmly install the cleaning device on the lip of the air inlet without damaging the outer skin; the contoured support structure itself is light in weight and easy to install, and there is no need to enter the interior of the air inlet to perform the fixing operation;

[0029] (2) Multiple pipes are assembled with adapter nuts and quick-connect connectors, which are convenient to carry and assemble on site. They are particularly suitable for in-situ cleaning work and can be extended according to the length of the air inlet duct to facilitate the introduction of the cleaning fluid into a specific location.

[0030] (3) The bracket is made of anodized aluminum to provide additional support for the cleaning device in the air inlet to offset the vibration during the cleaning process. Specifically, it provides tight lateral and longitudinal forces to prevent the cleaning device from slipping due to vibration during cold operation.

[0031] (4) The water pipe used for cleaning is connected to the contour support structure by a universal bearing to facilitate adjustment of the relative angle and prevent the water pipe from deforming or the contour support structure from damaging the outer skin and lip structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the aero-engine flow channel cleaning device of the present invention;

[0033] Figure 2 for Figure 1 Exploded diagram of

[0034] Figure 3 A schematic diagram of the state of cleaning the flow passage of an aircraft engine;

[0035] In the figure, 1-contact support structure, 2-pressure cover, 3-first transfer nut, 4-second transfer nut, 5-third transfer nut, 6-bracket flange, 7-fourth transfer nut, 8-bracket, 9-nylon gasket, 10-universal bearing, 11-first quick-connect connector, 12-second quick-connect connector, 13-handle ball, 14-elbow, 15-sprinkler, 16-first straight pipe, 17-second straight pipe. DETAILED DESCRIPTION

[0036] The present invention is further described below in conjunction with specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0037] like Figure 1 and Figure 2 As shown, in this embodiment, an aircraft engine flow channel cleaning device is designed, including a contoured support structure 1, a pressure cover 2, a first adapter nut 3, a second adapter nut 4, a third adapter nut 5, a bracket flange 6, a fourth adapter nut 7, a bracket 8, a nylon gasket 9, a universal bearing 10, a first quick-connect connector 11, a second quick-connect connector 12, a handle ball 13, a bent pipe 14, a nozzle 15, a first straight pipe 16 and a second straight pipe 17.

[0038] The contoured support structure 1 includes a support body, four support legs extend from the support body, a space is formed between the support legs and the support body to accommodate the outer contour of the engine air inlet lip, a through hole is opened on the support body, and a through slot is opened at the end of the support leg. The support leg includes two sections, one of which points from the engine air inlet lip to the center of the engine air inlet, and the other section extends from the engine air inlet lip close to the air inlet outer skin and is provided with a through slot that cooperates with the screws on the outer skin. Figure 2 Four supporting legs are shown, one of which is located above the other three.

[0039] The gland 2 is a hollow tube with a flange, and the gland 2 is installed in the through hole of the support body through its own flange, and the universal bearing 10 is installed in the inner cavity of the gland 2. The universal bearing 10 can ensure that the angle between the second straight tubes 17 is adjustable, thereby avoiding extrusion deformation between the contoured support structure 1 and the second straight tube 17, thereby damaging the air inlet lip or the outer skin.

[0040] The water pipe is composed of a first straight pipe 16, a second straight pipe 17 and a curved pipe 14, wherein one end of the second straight pipe 17 passes through the inner hole of the universal bearing 10 through the third transfer nut 5 and the second quick-plug connector 12, and then is connected to the second transfer nut 4, the nylon gasket 9 and the first transfer nut 3 in sequence, and the first transfer nut 3 is connected to the water source. The end of the curved pipe 14 is connected to the nozzle 15 through the fourth transfer nut 7. The curved pipe 14 is connected to the first straight pipe 16 through the transfer nut and the quick-plug connector, and the first straight pipe 16 is connected to the second straight pipe 17 through the third transfer nut 5 and the first quick-plug connector 11.

[0041] The bracket 8 is V-shaped, and the apex of the V-shape is connected to the water pipe through the bracket flange 6. The two ends are installed with handle balls 13, which serve as the contact point and support point between the elbow 14 and the inner wall of the air inlet. The bracket 8 is made of aluminum alloy, and the handle ball 13 is made of plastic. The bracket 8 is connected to the elbow 14 through the flange bracket 6. The flange bracket 6 is a disk with a partial flange structure. The apex of the V-shape of the bracket 8 is installed in the flange hole of the flange bracket 6 by screws.

[0042] The method for cleaning the flow passage of an aircraft engine using the above cleaning device specifically comprises the following steps:

[0043] S1, extend the flow channel cleaning device including the nozzle 15, the water pipe and the bracket 3 into the engine air inlet, wherein the nozzle 15 is at least 150 mm away from the fairing cap and at least 250 mm away from the compressor blades, and the contoured support structure 1 is placed at the entrance of the engine air inlet;

[0044] S2, move the contour support structure 1 so that all the support feet are moved to the position with screws on the outer skin of the engine air inlet duct, remove the screws, align the notches of the support feet with the screw holes, and then reset and install the screws to fix all the support feet to the outer skin of the engine air inlet duct;

[0045] S3, install a sump for collecting cleaning waste water at the interface between the engine air intake and the engine; open the engine outer skin and waterproof the generator; install a drainage pipe at the engine exhaust valve to drain the cleaning waste water to the sump;

[0046] S4, connect the water source to the water pipe at the universal bearing 10, and open the water source to clean the engine flow channel. Figure 3 Schematic diagram of the cleaning process.

[0047] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For ordinary technicians in the field of this technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. An aircraft engine flow channel cleaning device, characterized in that: include: A contour support structure (1), the contour support structure (1) comprising a support body, at least three support legs extending from the support body, a space capable of accommodating the outer contour of the engine air inlet lip is formed between the support legs and the support body, a through hole is formed on the support body, and through grooves are formed at the ends of the support legs; A universal bearing (10), wherein the universal bearing (10) is installed in a through hole of the support body; A water pipe, wherein the water pipe passes through the inner hole of the universal bearing (10), one end of the water pipe is connected to the spray head (15), and the other end is connected to a water source; A bracket (8) is mounted on the water pipe and is located between the spray head (15) and the contoured support structure (1).

2. The aircraft engine flow channel cleaning device according to claim 1, characterized in that: The support foot includes two sections, one of which points from the engine air inlet lip to the center of the engine air inlet, and the other extends from the engine air inlet lip close to the air inlet outer skin and is provided with a through groove that cooperates with the screws on the outer skin.

3. The aircraft engine flow channel cleaning device according to claim 1, characterized in that: The contoured support structure (1) is made of plastic.

4. The aircraft engine flow channel cleaning device according to claim 1, characterized in that: It also includes a gland (2), which is a hollow tube with a flange. The gland (2) is installed in the through hole of the support body through its own flange, and the universal bearing (10) is installed in the inner cavity of the gland (2).

5. The aircraft engine flow channel cleaning device according to claim 1, characterized in that: The water pipe is formed by splicing together multiple pipe sections, wherein the pipe connected to the nozzle (15) is curved, and the remaining pipes are straight pipes.

6. The aircraft engine flow channel cleaning device according to claim 5, characterized in that: The pipelines are connected to each other via adapter nuts and quick-plug connectors.

7. The aircraft engine flow channel cleaning device according to claim 1, characterized in that: The bracket (8) is V-shaped, the apex of which is connected to the water pipe via a bracket flange (6), and handle balls (13) are installed at its two ends.

8. A method for cleaning an aircraft engine flow channel, characterized in that: The flow channel cleaning device according to claim 1 is used, and includes the following steps: S1, extending the flow channel cleaning device including the nozzle (15), the water pipe and the bracket (3) into the engine air intake duct, and placing the contoured support structure (1) at the entrance of the engine air intake duct; S2, moving the contoured support structure (1) so that all the support legs are moved to the positions with screws on the outer skin of the engine air inlet duct, removing the screws, aligning the notches of the support legs with the screw holes, and then resetting and installing the screws to fix all the support legs to the outer skin of the engine air inlet duct; S3, connecting the water source to the water pipe at the universal bearing (10), and opening the water source to clean the engine flow channel.

9. The method for cleaning the flow passage of an aircraft engine according to claim 8, characterized in that: In S1, the nozzle (15) is at least 150 mm away from the fairing cap and at least 250 mm away from the compressor blades.

10. The method for cleaning the flow passage of an aircraft engine according to claim 8, characterized in that: Also includes: A sump for collecting cleaning waste water is installed at the interface between the engine air intake and the engine; Open the engine outer skin and waterproof the generator; Install a drainage pipe at the engine exhaust valve to drain the cleaning waste water.

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